View allAll Photos Tagged Manufacturing_process
Selective Laser Melting (SLM) is an additive manufacturing process that can be used for many different applications.
The SLM process starts by numerically slicing a 3D CAD model into a number of finite layers. For each sliced layer a laser scan path is calculated which defines both the boundary contour and some form of fill sequence, often a raster pattern. Each layer is then sequentially recreated by depositing powder layers, one on top of the other, and melting their surface by scanning a laser beam.
The powder is spread uniformly by a wiper. A high power-density fibre laser with a 40µm beam spot size fully melts the pre-deposited powder layer. The melted particles fuse and solidify to form a layer of the component.
For more information please visit www.twi-global.com/technologies/welding-surface-engineeri...
If you wish to use this image each use should be accompanied by the credit line and notice, "Courtesy of TWI Ltd".
American Apparel TR401W - Unisex Triblend ShortSleeve Track T-shirt Features:
• 4 oz., 50% polyester, 25% cotton, 25% rayon
• Tri-Oatmeal and Tri-Lieutenant are 50% polyester, 37% cotton, 13% rayon
• 30/1 singles
• Shoulder-to-shoulder tape and 7/8" seamed collar
• 1” blind-stitch sleeve hem
• 1” double-needle bottom hem
• Double-satin razor label
• Sideseamed
• American Apparel's manufacturing process utilizes 45% renewable energy
• American Apparel®, through Gildan’s Community Investment Program, supports education, the environment, humanitarian aid and active living in the communities we do business in
American Apparel triblend track t-shirt featuring a slim fit on our tri-blend, a super soft lightweight fabric for that worn-in vintage feel.
Check Americal Apparel AL1301 Cotton T-shirt: www.blanks.ca/american-apparel-tr401w-unisex-triblend-sho...
Buy blank Americal Apparel at wholesale prices: www.blanks.ca/brands/american-apparel.html
An old friend of mine who collects older trucks once said to me the thing that fascinated him the most was the amount of butts that have sat in them. While this isn't the oldest car I have ever inventoried, (a 79 Tbird has that honor) it still is a rite of passage experience to release the clutch and give an engine that is older than you some go juice. This 4x4 short bed came equipped with the bulletproof 4.9 inline 6 and even though it wasn't a 5.0 V8 she still sounds much much better than her grandchildren 26 years later. And that isn't the only change that has happened in 26 years. It is truly a shame the path the auto industry has taken today, trying to squeeze every last penny out of the manufacturing process. Ford, GM, Fiat/Chrysler and every other car company is guilty of this, and with Fords recent recall on rupturing brake lines goes to show how even simple safety is subject to capitalisms greed across the board. I am just happy that relics like these roam the pavement and can offer a short taste of "what once was".
The National Flag of India is a horizontal rectangular tricolour of deep saffron, white and India green; with the Ashoka Chakra, a 24-spoke wheel, in blue at its centre. It was adopted in its present form during a meeting of the Constituent Assembly held on 22 July 1947, when it became the official flag of the Dominion of India. The flag was subsequently retained as that of the Republic of India. In India, the term "tricolour" (Hindi: तिरंगा, Tirangā) almost always refers to the Indian national flag. The flag is based on the Swaraj flag, a flag of the Indian National Congress designed by Pingali Venkayya.
The flag, by law, is to be made of khadi, a special type of hand-spun cloth of cotton or silk made popular by Mahatma Gandhi. The manufacturing process and specifications for the flag are laid out by the Bureau of Indian Standards. The right to manufacture the flag is held by the Khadi Development and Village Industries Commission, who allocate it to the regional groups. As of 2009, the Karnataka Khadi Gramodyoga Samyukta Sangha was the sole manufacturer of the flag.
Usage of the flag is governed by the Flag Code of India and other laws relating to the national emblems. The original code prohibited use of the flag by private citizens except on national days such as the Independence day and the Republic Day. In 2002, on hearing an appeal from a private citizen, Naveen Jindal, the Supreme Court of India directed the Government of India to amend the code to allow flag usage by private citizens. Subsequently, the Union Cabinet of India amended the code to allow limited usage. The code was amended once more in 2005 to allow some additional use including adaptations on certain forms of clothing. The flag code also governs the protocol of flying the flag and its use in conjunction with other national and non-national flags.
* High Modulus Custom Carbon Racing Bicycle Frame
* Italian Bottom Bracket or BB30
* Tapered head tube/fork
* Best Road Bike Available in Formigli Collection
* 20% lighter 27% more rigid than Asiel
MSRP- $5999.99
The Asiel RF is our top of the line, flagship carbon racing frame. It is the result of 20 years of technological advancement, offering superior materials, manufacturing processes, and design. The Asiel RF is hand made with a tapered head tube/fork, BB30 bottom bracket (or Italian thread), and an integrated seat post. This makes for a no-compromises race frame that is unmatched in performance and is 20% lighter and 27% stiffer than the Asiel. A new paint scheme has also been developed to give this high caliber frame a unique and stunning look.
* FRAME Carbon with Carbon drop outs
* FORK Full Carbon Fork 1 1/2 to 1/ 1/8
* HEADSET Integrated *Dedda, Cane Creek or FSA headset included with frame purchase
* BOTTOM BRACKET Italian Thread OR BB30
* SEATPOST Integrated
Availble in one color scheme as shown.
The composite used to build the RF is an IM600 carbon fiber with a tensile strength equal to 48,000 lbs. Utilizing a special nanotechnology, Formigli optimizes the pre-impregnation of epoxy resin into the IM600 carbon fabric resulting in a final product that is 20% lighter and 27% more rigid and responsive than the Asiel.
Geometric Design
The Asiel RF was conceived with the vision to obtain a frame with maximum tensional stiffness. This was achieved through our research in tube design that optimizes the stresses of torque.
Looking at the rear of the frame, you can notice a significant drop in the seat-stays. This solution gave the frame more rigidity in the rear, thus obtaining a greater responsiveness in wheel traction. This drop can be felt especially in the hills and in sprints. It is most noticeable in low gears. Looking at the center of the frame, the bottom of the seat tube near the bottom bracket, the tube has a larger cross-section supporting the weight of the cyclist on a broader base. This gives the frame greater resistance and higher performance under stress.
We decided to build the Asiel RF with an internally integrated seat post with a slight rise of the seat post support and compensating the eventual rise with internal carbon plugs, shaped like the tube. The fork was designed with a tapered steering tube which provides a greater circumference to support the frame, improving the stability of the bike, as well as reducing the vibrations that are formed especially on high speed descents.
Fabric Composition
Layers: 6 layers + 3k cross weave (the upper, visible layer)
Laminate: Layered unidirectional and bidirectional oriented 12k
Resin: Epoxy
Fiber: Polyacrylonitrile (PAN)
Fabric: Preimpregnated fabric yarn (long fiber) molded with a vacuum sealing technique and chemically bonded 120°c.
Mechanical Properties
Tensile Strength: R. 220 Kgmmg
Modulus Elasticity: 38,000 Kgmmg
Fatigue: 100 million cycles/ 1400 MPa maxiumum load
Physical weight of carbon at 18°c is 1.86 kg/ dm3 (30% resin)
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Available at KGS Bikes kgsbikes.com with the added value of our BalancePoint™ positioning system to design your perfect custom bicycle.
As part of the required course knowledge pupils need to be able to outline the process involved in taking a square wooden blank and preparing it for turning between centres. These pictures depict that process chronologically.
Stage 1 * Preparation of wooden blank. Cut to size. Sand square. Mark across diagonals. Centre punch the centre point. Use spring dividers to mark circumference. Repeat on other end.
Stage 2 * Plane off corners down to circumference line. This takes cross section from square to octagon. This reduces force on cutting toll in initial prep of blank. Mount between fork [driven] centre and dead [or live ] centre at tailstock end. Apply grease a dead centre end. apply force from tailstock end to force fork into material at driven end. Adjust toolstock height to suit. Check for clearance.
Stage 3 * Roughout using scraper to diameter. Use combination of gouges and skew chisels to add beads and other decorative detailing as required. Ensure spindle speed is appropriate for material and cross section under consideration. Obey all safety instructions.
+++ DISCLAIMER +++
Nothing you see here is real, even though the conversion or the presented background story might be based historical facts. BEWARE!
Some background:
In the grand scope of World War 2 fighter aircraft there is a little-remembered French design designated the Arsenal "VG-33". The aircraft was born from a rather lengthy line of prototype developments put forth by the company in the years leading up to World War 2 and the VG-33 and its derivatives represented the culmination of this work before the German invasion rendered all further work moot.
The Arsenal de l'Aeronautique company was formed by the French government in 1936 ahead of World War 2. It began operations with dedicated design and development of a fast fighter type until the German conquer of France in 1940 after which the company then focused on engine production after 1945. Then followed a period of design and construction of gliders and missiles before being privatized in 1952 (as SFECMAS). The company then fell under the SNCAN brand label and became "Nord Aviation" in 1955.
The VG-33 was the result of the company's research. Work on a new fast fighter began by Arsenal engineers in 1936 and the line began with the original VG-30 prototype achieving first flight on October 1st, 1938. Named for engineer Vernisse (V) and designer Jean Gaultier (G), the VG-30 showcased a sound design with good performance and speed during the tests, certainly suitable for progression as a military fighter and with future potential.
Development continued into what became the VG-31 which incorporated smaller wings. The VG-32 then followed which returned to the full-sized wings and installed the American Allison V-1710-C15 inline supercharged engine of 1,054 horsepower. The VG-32 then formed the basis of the VG-33 which reverted to a Hispano-Suiza 12Y-31 engine and first flight was in early 1939, months ahead of the German invasion of Poland. Flight testing then spanned into August and serial production of this model was ordered.
The VG-33 was one of the more impressive prewar fighter ventures by the French that included the Dewoitine D.520, understood to be on par with the lead German fighter aircraft of the period - the famous Messerschmitt Bf 109.
Only about forty or so French Arsenal VG-33 fighters were completed before the Fall of France in 1940, with 160 more on order and in different states of completion. Despite the production contract, Arsenal' engineers continued work on the basic design for improved and specialized sub-types. The VG-34 appeared in early 1940 outfitted with the Hispano-Suiza 12Y-45 engine of 935 horsepower, which improved performance at altitude. An uprated engine was installed in VG-35 and VG-36, too. They utilized a Hispano-Suiza 12Y-51 engine of 1,000 horsepower with a revised undercarriage and radiator system.
VG-37 was a long-range version that was not furthered beyond the drawing board, but the VG-38 with a Hispano-Suiza 12Y-77 engine that featured two exhaust turbochargers for improved performance at high altitude, achived pre-production status with a series of about 10 aircraft. These were transferred to GC 1/3 for field trials in early 1940 and actively used in the defence against the German invasion.
The VG-39 ended the line as the last viable prototype model with its drive emerging from a Hispano-Suiza 12Z engine of 1,280 horsepower. A new three-machine-gun wing was installed for a formidable six-gun armament array. This model was also ordered into production as the VG-39bis and was to carry a 1,600 horsepower Hispano-Suiza 12Z-17 engine into service. However, the German invasion eliminated any further progress, and eventually any work on the Arsenal VG fighter family was abandoned, even though more designs were planned, e .g. the VG-40, which mounted a Rolls-Royce Merlin III, and the VG-50, featuring the newer Allison V-1710-39. Neither was built.
Anyway, the finalized VG-38 was an all-modern looking fighter design with elegant lines and a streamlined appearance. Its power came from an inline engine fitted to the front of the fuselage and headed by a large propeller spinner at the center of a three-bladed unit. The cockpit was held over midships with the fuselage tapering to become the tail unit.
The tail featured a rounded vertical tail fin and low-set horizontal planes in a traditional arrangement - all surfaces enlarged for improved high altitude performance.
The monoplane wing assemblies were at the center of the design in the usual way. The pilot's field of view was hampered by the long nose ahead, the wings below and the raised fuselage spine aft, even though the pilot sat under a largely unobstructed canopy utilizing light framing. The canopy opened to starboard.
A large air scoop for the radiator and air intercooler was mounted under the fuselage. As an unusual feature its outlet was located in a dorsal position, behind the cockpit. The undercarriage was of the typical tail-dragger arrangement of the period, retracting inwards. The tail wheel was retractable, too.
Construction was largely of wood which led to a very lightweight design that aided performance and the manufacture process. Unlike other fighters of the 1930s, the VG-38 was well-armed with a 20mm Hispano-Suiza cannon, firing through the propeller hub, complemented by 4 x 7.5mm MAC 1934 series machine guns in the wings, just like the VG-33.
The aircraft never saw combat action in the Battle of France. Its arrival was simply too late to have any effect on the outcome of the German plans. Therefore, with limited production and very limited combat service during the defence of Paris in May 1940, it largely fell into the pages of history with all completed models lost.
Specifications:
Crew: 1
Length: 28.05 ft (8.55 m)
Width: 35.43 ft (10.80 m)
Height: 10.83ft (3.30 m)
Weight: Empty 4,519 lb (2,050 kg), MTOW 5,853 lb (2,655 kg)
Maximum Speed: 398 mph (641 kmh at 10.000m)
Maximum Range: 746 miles (1,200 km)
Service Ceiling: 39,305 ft (12.000 m; 7.458 miles)
Powerplant:
1x Hispano-Suiza 12Y-77 V-12 liquid-cooled inline piston engine
with two Brown-Boveri exhaust turbochargers, developing 1,100 hp (820 kW).
Armament:
1x 20mm Hispano-Suiza HS.404 cannon, firing through the propeller hub
4x 7.5mm MAC 1934 machine guns in the outer wings
The kit and its assembly:
I found the VG-33 fascinating - an obscure and sleek fighter with lots of potential that suffered mainly from bad timing. There are actually VG-33 kits from Azur and Pegasus, but how much more fun is it to create your own interpretation of the historic events, esp. as a submission to a Battle of Britain Group Build at whatifmodelers.com?
I had this project on the whif agenda for a long time, and kept my eyes open for potential models. One day I encountered Amodel's Su-1 and Su-3 kits and was stunned by this aircraft's overall similarity to the VG-33. When I found the real VG-38 description I decided to convert the Su-3 into this elusive French fighter!
The Su-3 was built mainly OOB, it is a nice kit with much detail, even though it needs some work as a short run offering. I kept the odd radiator installation of the Suchoj aircraft, but changed the landing gear from a P-40 style design (retracting backwards and rotating 90°) into a conservative, inward retracting system. I even found forked gear struts in the spares box, from a Fiat G.50. The covers come from a Hawker Hurricane, and the wells were cut out from this pattern, while the rest of the old wells was filled with putty.
Further mods include the cleaned cowling (the Su-3's fuselage-mounted machine guns had to go), while machine guns in the wings were added. The flaps were lowered, too, and the small cockpit canopy cut in two pieces in, for an opened position - a shame you can hardly see anything from the neat interior. Two large antenna masts complete the French style.
Painting and markings:
Again, a rather conservative choice: typical French Air Force colors, in Khaki/Dark Brown/Blue Gray with light blue-gray undersides.
One very inspiring fact about the French tricolor-paint scheme is that no aircraft looked like the other – except for a few types, every aircraft had an individual scheme with more or less complexity or even artistic approach. Even the colors were only vaguely unified: Field mixes were common, as well as mods with other colors that were mixed into the basic three tones!
I settled for a scheme I found on a 1940 Curtiss 75, with clearly defined edges between the paint fields. Anything goes! I used French Khaki, Dark Blue Grey and Light Blue Grey (for the undersides) from Modelmaster's Authentic Enamels range, and Humbrol 170 (Brown Bess) for the Chestnut Brown. Interior surfaces were painted in dark grey (Humbrol 32) while the landing gear well parts of the wings were painted in Aluminum Dope (Humbrol 56).
The decals mainly come from a Hobby Boss Dewoitine D.520, but also from a PrintScale aftermarket sheet and the scrap box.
The kit was slightly weathered with a black ink wash and some dry-painting, more for a dramatic effect than simulating wear and tear, since any aircraft from the VG-33 family would only have had a very short service career.
Well, a travesty whif - and who would expect an obscure Soviet experimental fighter to perform as a lookalike for an even more obscure French experimental fighter? IMHO, it works pretty fine - conservative sould might fair over the spinal radiator outlet and open the dorsal installation, overall both aircraft are very similar in shape, size and layout. :D
+++ DISCLAIMER +++
Nothing you see here is real, even though the conversion or the presented background story might be based historical facts. BEWARE!
Some background:
In the grand scope of World War 2 fighter aircraft there is a little-remembered French design designated the Arsenal "VG-33". The aircraft was born from a rather lengthy line of prototype developments put forth by the company in the years leading up to World War 2 and the VG-33 and its derivatives represented the culmination of this work before the German invasion rendered all further work moot.
The Arsenal de l'Aeronautique company was formed by the French government in 1936 ahead of World War 2. It began operations with dedicated design and development of a fast fighter type until the German conquer of France in 1940 after which the company then focused on engine production after 1945. Then followed a period of design and construction of gliders and missiles before being privatized in 1952 (as SFECMAS). The company then fell under the SNCAN brand label and became "Nord Aviation" in 1955.
The VG-33 was the result of the company's research. Work on a new fast fighter began by Arsenal engineers in 1936 and the line began with the original VG-30 prototype achieving first flight on October 1st, 1938. Named for engineer Vernisse (V) and designer Jean Gaultier (G), the VG-30 showcased a sound design with good performance and speed during the tests, certainly suitable for progression as a military fighter and with future potential.
Development continued into what became the VG-31 which incorporated smaller wings. The VG-32 then followed which returned to the full-sized wings and installed the American Allison V-1710-C15 inline supercharged engine of 1,054 horsepower. The VG-32 then formed the basis of the VG-33 which reverted to a Hispano-Suiza 12Y-31 engine and first flight was in early 1939, months ahead of the German invasion of Poland. Flight testing then spanned into August and serial production of this model was ordered.
The VG-33 was one of the more impressive prewar fighter ventures by the French that included the Dewoitine D.520, understood to be on par with the lead German fighter aircraft of the period - the famous Messerschmitt Bf 109.
Only about forty or so French Arsenal VG-33 fighters were completed before the Fall of France in 1940, with 160 more on order and in different states of completion. Despite the production contract, Arsenal' engineers continued work on the basic design for improved and specialized sub-types. The VG-34 appeared in early 1940 outfitted with the Hispano-Suiza 12Y-45 engine of 935 horsepower, which improved performance at altitude. An uprated engine was installed in VG-35 and VG-36, too. They utilized a Hispano-Suiza 12Y-51 engine of 1,000 horsepower with a revised undercarriage and radiator system.
VG-37 was a long-range version that was not furthered beyond the drawing board, but the VG-38 with a Hispano-Suiza 12Y-77 engine that featured two exhaust turbochargers for improved performance at high altitude, achived pre-production status with a series of about 10 aircraft. These were transferred to GC 1/3 for field trials in early 1940 and actively used in the defence against the German invasion.
The VG-39 ended the line as the last viable prototype model with its drive emerging from a Hispano-Suiza 12Z engine of 1,280 horsepower. A new three-machine-gun wing was installed for a formidable six-gun armament array. This model was also ordered into production as the VG-39bis and was to carry a 1,600 horsepower Hispano-Suiza 12Z-17 engine into service. However, the German invasion eliminated any further progress, and eventually any work on the Arsenal VG fighter family was abandoned, even though more designs were planned, e .g. the VG-40, which mounted a Rolls-Royce Merlin III, and the VG-50, featuring the newer Allison V-1710-39. Neither was built.
Anyway, the finalized VG-38 was an all-modern looking fighter design with elegant lines and a streamlined appearance. Its power came from an inline engine fitted to the front of the fuselage and headed by a large propeller spinner at the center of a three-bladed unit. The cockpit was held over midships with the fuselage tapering to become the tail unit.
The tail featured a rounded vertical tail fin and low-set horizontal planes in a traditional arrangement - all surfaces enlarged for improved high altitude performance.
The monoplane wing assemblies were at the center of the design in the usual way. The pilot's field of view was hampered by the long nose ahead, the wings below and the raised fuselage spine aft, even though the pilot sat under a largely unobstructed canopy utilizing light framing. The canopy opened to starboard.
A large air scoop for the radiator and air intercooler was mounted under the fuselage. As an unusual feature its outlet was located in a dorsal position, behind the cockpit. The undercarriage was of the typical tail-dragger arrangement of the period, retracting inwards. The tail wheel was retractable, too.
Construction was largely of wood which led to a very lightweight design that aided performance and the manufacture process. Unlike other fighters of the 1930s, the VG-38 was well-armed with a 20mm Hispano-Suiza cannon, firing through the propeller hub, complemented by 4 x 7.5mm MAC 1934 series machine guns in the wings, just like the VG-33.
The aircraft never saw combat action in the Battle of France. Its arrival was simply too late to have any effect on the outcome of the German plans. Therefore, with limited production and very limited combat service during the defence of Paris in May 1940, it largely fell into the pages of history with all completed models lost.
Specifications:
Crew: 1
Length: 28.05 ft (8.55 m)
Width: 35.43 ft (10.80 m)
Height: 10.83ft (3.30 m)
Weight: Empty 4,519 lb (2,050 kg), MTOW 5,853 lb (2,655 kg)
Maximum Speed: 398 mph (641 kmh at 10.000m)
Maximum Range: 746 miles (1,200 km)
Service Ceiling: 39,305 ft (12.000 m; 7.458 miles)
Powerplant:
1x Hispano-Suiza 12Y-77 V-12 liquid-cooled inline piston engine
with two Brown-Boveri exhaust turbochargers, developing 1,100 hp (820 kW).
Armament:
1x 20mm Hispano-Suiza HS.404 cannon, firing through the propeller hub
4x 7.5mm MAC 1934 machine guns in the outer wings
The kit and its assembly:
I found the VG-33 fascinating - an obscure and sleek fighter with lots of potential that suffered mainly from bad timing. There are actually VG-33 kits from Azur and Pegasus, but how much more fun is it to create your own interpretation of the historic events, esp. as a submission to a Battle of Britain Group Build at whatifmodelers.com?
I had this project on the whif agenda for a long time, and kept my eyes open for potential models. One day I encountered Amodel's Su-1 and Su-3 kits and was stunned by this aircraft's overall similarity to the VG-33. When I found the real VG-38 description I decided to convert the Su-3 into this elusive French fighter!
The Su-3 was built mainly OOB, it is a nice kit with much detail, even though it needs some work as a short run offering. I kept the odd radiator installation of the Suchoj aircraft, but changed the landing gear from a P-40 style design (retracting backwards and rotating 90°) into a conservative, inward retracting system. I even found forked gear struts in the spares box, from a Fiat G.50. The covers come from a Hawker Hurricane, and the wells were cut out from this pattern, while the rest of the old wells was filled with putty.
Further mods include the cleaned cowling (the Su-3's fuselage-mounted machine guns had to go), while machine guns in the wings were added. The flaps were lowered, too, and the small cockpit canopy cut in two pieces in, for an opened position - a shame you can hardly see anything from the neat interior. Two large antenna masts complete the French style.
Painting and markings:
Again, a rather conservative choice: typical French Air Force colors, in Khaki/Dark Brown/Blue Gray with light blue-gray undersides.
One very inspiring fact about the French tricolor-paint scheme is that no aircraft looked like the other – except for a few types, every aircraft had an individual scheme with more or less complexity or even artistic approach. Even the colors were only vaguely unified: Field mixes were common, as well as mods with other colors that were mixed into the basic three tones!
I settled for a scheme I found on a 1940 Curtiss 75, with clearly defined edges between the paint fields. Anything goes! I used French Khaki, Dark Blue Grey and Light Blue Grey (for the undersides) from Modelmaster's Authentic Enamels range, and Humbrol 170 (Brown Bess) for the Chestnut Brown. Interior surfaces were painted in dark grey (Humbrol 32) while the landing gear well parts of the wings were painted in Aluminum Dope (Humbrol 56).
The decals mainly come from a Hobby Boss Dewoitine D.520, but also from a PrintScale aftermarket sheet and the scrap box.
The kit was slightly weathered with a black ink wash and some dry-painting, more for a dramatic effect than simulating wear and tear, since any aircraft from the VG-33 family would only have had a very short service career.
Well, a travesty whif - and who would expect an obscure Soviet experimental fighter to perform as a lookalike for an even more obscure French experimental fighter? IMHO, it works pretty fine - conservative sould might fair over the spinal radiator outlet and open the dorsal installation, overall both aircraft are very similar in shape, size and layout. :D
Discovery STO - 70 Ton, Single Stage to Orbit Fixed Wing Aircraft - Space Plane - Hypersonic Plane, U-TBCC / Unified Turbine Based Combined Cycle & Aerospike
Iteration 1, Mach 8-10 in amtmosphere, 195ft long, Heavy Lift Single Stage To Orbit Fixed Wing Aircraft. 70 TONS, ie 140,000 LBS, 60 ft X 15ft X 15ft payload bay. Up in the Falcon Heavy and Delta IV class, except not $400 million to launch giant payloads into orbit, but below $250 per lbs, or about $28 million to launch giant payloads, and normalized orbital flight, as normal as a 737 commercial flight. Load up, refuel, take off in an afternoon. I estimate this aircraft would cost about $750 million each for space capable. In atmosphere commercial, roughly $300 million each for a 200 passenger M8-10 (not designed yet)
--------------
www.ioaircraft.com/hypersonic/ranger.php
Drew Blair
www.linkedin.com/in/drew-b-25485312/
--------------
Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
-------------
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Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
Selective Laser Melting (SLM) is an additive manufacturing process that can be used for many different applications.
The SLM process starts by numerically slicing a 3D CAD model into a number of finite layers. For each sliced layer a laser scan path is calculated which defines both the boundary contour and some form of fill sequence, often a raster pattern. Each layer is then sequentially recreated by depositing powder layers, one on top of the other, and melting their surface by scanning a laser beam.
The powder is spread uniformly by a wiper. A high power-density fibre laser with a 40µm beam spot size fully melts the pre-deposited powder layer. The melted particles fuse and solidify to form a layer of the component.
For more information please visit www.twi-global.com/technologies/welding-surface-engineeri...
If you wish to use this image each use should be accompanied by the credit line and notice, "Courtesy of TWI Ltd".
Lancia Hyena:
Overview:
ManufacturerZagato on Lancia mechanicals
Also calledLancia Delta Zagato Hyena
Production1992–1996
24 made
AssemblyRho, Milan
DesignerMarco Pedracini at Zagato
Body and chassis
ClassSports car
Body style2-door coupé
LayoutTransverse front-engine, four-wheel drive
RelatedLancia Delta Integrale "Evoluzione"
Powertrain
Engine2.0 L I4 (turbocharged petrol)
Transmission5-speed manual
The Lancia Hyena was a 2-door coupé made in small numbers by Italian coachbuilder Zagato on the basis of the Delta HF Integrale "Evoluzione".
History:
The Hyena was born thanks to the initiative of Dutch classic car restorer and collector Paul V.J. Koot, who desired a coupé version of the multiple World Rally Champion HF Integrale. He turned to Zagato, where Hyena was designed in 1990 by Marco Pedracini. A first prototype was introduced at the Brussels Motor Show in January 1992.
Decision was taken to put the Hyena into limited production. Fiat refused to participate in the project supplying bare HF Integrale chassis, which complicated the manufacturing process: the Hyena had to be produced from fully finished HF Integrales, privately purchased at Lancia dealers. Koot's Lusso Service took care of procuring and stripping the donor cars in the Netherlands; they were then sent to Zagato in Milan to have the new body built and for final assembly. All of this made the Hyena very expensive to build and they were sold for around 140,000 Swiss francs or $75,000 (£49,430).
A production run of 75 examples was initially planned, but only 25 Hyenas were completed between 1992 and 1993.
Specifications:
The Zagato bodywork made use of aluminium alloys and composite materials; the interior featured new dashboard, console and door cards made entirely from carbon fibre. Thanks to these weight saving measures the Hyena was some 150 kilograms (330 lb) lighter than the original HF Integrale, about 15% of its overall weight. The two-litre turbo engine was upgraded from 205 to 250 PS (184 kW), and the car could accelerate from 0–100 km in 5.4 seconds.
[Text from Wikipedia]
en.wikipedia.org/wiki/Lancia_Delta#Lancia_Hyena
This miniland-scale Lego Lancia Hyena (1992 - Zagato) has been created for Flickr LUGNuts' 92nd Build Challenge, - "Stuck in the 90's", - all about vehicles from the decade of the 1990s.
Soda Springs (Geyser) is a group of thousands of natural carbonated springs in the area of Soda Springs, Idaho. The springs were a landmark on the Oregon Trail.
“Past volcanic activity has shaped the landscape, and the residual geothermal activity has caused the numerous hot bubbling springs that gave it its name. Geothermal activity hundreds of feet below the ground heats water and mixes in carbon dioxide gas. Soda Springs gets its name from the naturally carbonated water. The resulting increased pressure contributes to the number of springs and was the cause of the geyser.”
The Oregon Trail passed through Soda Springs. At the time it was known as the "Oasis of Soda Springs". Between Fort Laramie and Fort Boise, Soda Springs was a major landmark Soda Springs is the second oldest settlement in Idaho. Sulphur Springs was the first hot spring that the Oregon Trail immigrants encountered in the soda springs area. Pyramid springs was discovered by fur trappers and pioneers, they discovered the springs by noticing mounds of soda formed rock and clay Johnkirk Townsends said in his diary, “Our encampment on the 8th was near what are called the’White Clay pits,” still on Bear River. The soil is soft chalk, white and tenacious: and in the vicinity are several springs of strong super carbonated water which bubble up with all the activity of artificial fountains. The taste was very agreeable and refreshing, resembling Saratoga water but not so saline. The whole plain to the hills is having depressions on their summits from which once issued streams of water. The extent of these eruptions, at some former period, must have been very great. At about half a mile distant, is an eruptive thermal spring of the temperature of 90 [degrees], and near this is an opening in the earth front which a stream of gas issues without water.”
This spring was known for its excellent water quality. Fred J. Kiesel of Ogden Utah heard of the excellent water and set up a bottling plant with W.J. Clark of Butte, MT. The product name was "Idanha." The natural mineral company was incorporated in 1887 and began distributing it around the nation and the globe. The water became so prestigious that it took first place at the Chicago's World Fair in 1893, and again in the World's Fair in Paris, France.
On November 30, 1937, a well drilling operation while attempting to build a natural hot springs swimming pool was surprised when it unintentionally released Soda Springs’s famous captive geyser, which surprised everyone by shooting 100 feet into the air. It has been capped and a timer activates it once every hour. The water is approximately 72 degrees Fahrenheit. There is now a park and a visitor center at the site.In addition to its captive geyser, Soda Springs also boasts a man-made lava flow, from the dumping of molten rock left over from Monsanto's phosphate mining and manufacturing process one mile north of the town.
en.wikipedia.org/wiki/Soda_Springs_Geyser
en.wikipedia.org/wiki/Wikipedia:Text_of_Creative_Commons_...
(En) Founded in 1906, the Coking Plant of Anderlues was specialized in the production of coke for industrial use.
Coke was obtained by distillation of coal in furnaces and, thanks to its superior fuel coal properties, it was used afterwards to feed the blast furnaces in the steel manufacturing process.
Closed and abandoned since 2002, the site has since undergone many losses and damages, not including an important pollution. While some buildings have now been demolished, there are however still some important parts of the former coking plant.
Among them, the former coal tower, next to the imposing "battery" of 38 furnaces, where the coke was produced. Besides them, we still can see the administrative buildings, the power station with its cooling tower, and buildings for the by-products, which were obtained by recovering the tar and coal gas. There are also a gasometer north side, the coal tip east side and a settling basin south side.
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(Fr) Fondées en 1906, les Cokeries d'Anderlues étaient spécialisées dans la fabrication de coke à usage industriel.
Le coke était obtenu par distillation de la houille dans des fours et, grâce à ses propriétés combustibles supérieures au charbon, il servait par après à alimenter les hauts-fourneaux dans le processus de fabrication de l'acier.
Fermé et laissé à l'abandon depuis 2002, le site a depuis lors subi de nombreuses pertes et dégradations, sans compter la pollution qui y règne. Si certains bâtiments (comme l'ancien lavoir à charbon) ont aujourd'hui été démolis, on retrouve encore toutefois certaines parties importantes de cette ancienne cokerie.
Parmi celles-ci, l'ancienne tour à charbon suivie de près par l'imposante "batterie" de 38 fours, où était produit le coke. A côté d'eux, on découvre également les bâtiments administratifs, la centrale électrique avec sa tour de refroidissement, ainsi que les bâtiments des sous-produits, lesquels étaient obtenus par récupération du goudron et du gaz de houille. Et en périphérie, on retrouve un gazomètre côté nord, le terril à l'est et un bassin de décantation côté sud.
Image depicting mineral ore specimen with many narrow veins of asbestiform serpentine, also known as chrysotile (white asbestos), within associated rock matrix. In this example, several seams of crystalline chrysotile show reflective characteristics and become more visible at certain angles to light source.
Used in thousands of products and material applications, the asbestos ore was first mined from geological deposits, then crushed to access the fibrous mineral within the rock. The crushed ore was then further milled and refined to recover asbestos fiber for later addition in material manufacturing processes.
Chrysotile material can easily split into countless "fibers", a characteristic somewhat unique to asbestos minerals. However, asbestos fibers can further sub-divide into such small, microscopic particles that they practically become "invisible" and can become airborne. Inhalation exposures to microscopic airborne asbestos particles have been well documented to cause serious respiratory diseases leading to fatalities.
Selective Laser Melting (SLM) is an additive manufacturing process that can be used for many different applications.
The SLM process starts by numerically slicing a 3D CAD model into a number of finite layers. For each sliced layer a laser scan path is calculated which defines both the boundary contour and some form of fill sequence, often a raster pattern. Each layer is then sequentially recreated by depositing powder layers, one on top of the other, and melting their surface by scanning a laser beam.
The powder is spread uniformly by a wiper. A high power-density fibre laser with a 40µm beam spot size fully melts the pre-deposited powder layer. The melted particles fuse and solidify to form a layer of the component.
For more information please visit www.twi-global.com/technologies/welding-surface-engineeri...
If you wish to use this image each use should be accompanied by the credit line and notice, "Courtesy of TWI Ltd".
The United States Astronaut Hall of Fame, located inside the Kennedy Space Center Visitor Complex Heroes & Legends building on Merritt Island, Florida, honors American astronauts and features the world's largest collection of their personal memorabilia, focusing on those astronauts who have been inducted into the Hall. Exhibits include Wally Schirra's Sigma 7 space capsule from the fifth crewed Mercury mission and the Gemini IX spacecraft flown by Gene Cernan and Thomas P. Stafford in 1966.
In the 1980s, the six then-surviving Mercury Seven astronauts conceived of establishing a place where US space travelers could be remembered and honored, along the lines of halls of fame for other fields. The Mercury Seven Foundation and Astronaut Scholarship Foundation were formed, and have a role in the ongoing operations of the Hall of Fame. The foundation's first executive director was former Associated Press space reporter Howard Benedict.
The Astronaut Hall of Fame was opened on October 29, 1990, by the U.S. Space Camp Foundation, which was the first owner of the facility. It was located next to the Florida branch of Space Camp.
The Hall of Fame closed for several months in 2002 when U.S. Space Camp Foundation's creditors foreclosed on the property due to low attendance and mounting debt. That September, an auction was held and the property was purchased by Delaware North Park Services on behalf of NASA and the property was added to the Kennedy Space Center Visitor Complex. The Hall of Fame re-opened December 14, 2002.
The Hall of Fame, which was originally located just west of the NASA Causeway, closed to the public on November 2, 2015, in preparation for its relocation to the Kennedy Space Center Visitor Complex 6 miles (9.7 km) to the east on Merritt Island. Outside of the original building was a full-scale replica of a Space Shuttle orbiter named Inspiration (originally named "Shuttle To Tomorrow" where visitors could enter and view a program). Inspiration served only as an outdoor, full scale, static display which visitors could not enter. After the Hall of Fame was transferred to the KSC Visitor Complex, Inspiration was acquired by LVX System and was placed in storage at the Shuttle Landing Facility at the Kennedy Space Center; in 2016, the shuttle was loaded on to a barge to be taken for refurbishment before going on an educational tour.
The building was purchased at auction by visitor complex operator Delaware North and renamed the ATX Center, and for a time housed educational programs including Camp Kennedy Space Center and the Astronaut Training Experience. Those programs have since been moved to the KSC Visitor Complex, and as of December 2019, the structure was being offered for lease. In July 2020, Lockheed Martin announced it would lease the building to support work on the NASA Orion crew capsule.
Inductees into the Hall of Fame are selected by a blue ribbon committee of former NASA officials and flight controllers, historians, journalists, and other space authorities (including former astronauts) based on their accomplishments in space or their contributions to the advancement of space exploration. Except for 2002, inductions have been held every year since 2001.
As its inaugural class in 1990, the Hall of Fame inducted the United States' original group of astronauts: the Mercury Seven. In addition to being the first American astronauts, they set several firsts in American spaceflight, both auspicious and tragic. Alan Shepard was the first American in space and later became one of the twelve people to walk on the Moon. John Glenn was the first American to orbit the Earth and after his induction went on, in 1998, to become the oldest man to fly in space, aged 77. Gus Grissom was the first American to fly in space twice and was the commander of the ill-fated Apollo 1, which resulted in the first astronaut deaths directly related to preparation for spaceflight.
Thirteen astronauts from the Gemini and Apollo programs were inducted in the second class of 1993. This class included the first and last humans to walk on the Moon, Neil Armstrong and Eugene Cernan; Ed White, the first American to walk in space (also killed in the Apollo 1 accident); Jim Lovell, commander of the famously near-tragic Apollo 13; and John Young, whose six flights included a moonwalk and command of the first Space Shuttle mission.
The third class was inducted in 1997 and consisted of the 24 additional Apollo, Skylab, and ASTP astronauts. Notable members of the class were Roger Chaffee, the third astronaut killed in the Apollo 1 fire and the only unflown astronaut in the Hall; Harrison Schmitt, the first scientist and next-to-last person to walk on the Moon; and Jack Swigert and Fred Haise, the Apollo 13 crewmembers not previously inducted.
The philosophy regarding the first three groups of inductees was that all astronauts who flew in NASA's "pioneering" programs (which would include Mercury, Gemini, Apollo, Apollo Applications Program (Skylab), and Apollo-Soyuz Test Project) would be included simply by virtue of their participation in a spaceflight in these early programs. The first group (the inaugural class of 1990) would only include the original Mercury astronauts (most of whom would go on to fly in later programs). The second group of inductees would include those astronauts who began their spaceflight careers during Gemini (all of whom would go on to fly in later programs). The third group of inductees would include those astronauts who began their spaceflight careers during Apollo, Skylab, and ASTP (some of whom would go on to fly in the Space Shuttle program). Since it would not be practical (or meaningful) to induct all astronauts who ever flew in space, all subsequent inductees (Space Shuttle program and beyond) are considered based on their accomplishments and contributions to the human spaceflight endeavor which would set them apart from their peers.
Over four dozen astronauts from the Space Shuttle program have been inducted since 2001. Among these are Sally Ride, the first American woman in space; Story Musgrave, who flew six missions in the 1980s and 90s; and Francis Scobee, commander of the ill-fated final Challenger mission.
The 2010 class consisted of Guion Bluford Jr., Kenneth Bowersox, Frank Culbertson and Kathryn Thornton. The 2011 inductees were Karol Bobko and Susan Helms. The 2012 inductees were Franklin Chang-Diaz, Kevin Chilton and Charles Precourt. Bonnie Dunbar, Curt Brown and Eileen Collins were inducted in 2013, and Shannon Lucid and Jerry Ross comprised the 2014 class.
Those inducted in 2015 were John Grunsfeld, Steven Lindsey, Kent Rominger, and Rhea Seddon. In 2016, inductees included Brian Duffy and Scott E. Parazynski. Ellen Ochoa and Michael Foale were announced as the 2017 class of the United States Astronaut Hall of Fame. Scott Altman and Thomas Jones followed in 2018. The 2019 inductees were James Buchli and Janet L. Kavandi.
Michael López-Alegría, Scott Kelly and Pamela Melroy were the 2020 inductees, inducted in a November 2021 ceremony. The 2022 inductees were Christopher Ferguson, David Leestma, and Sandra Magnus. Roy Bridges Jr. and Mark Kelly were the 2023 inductees.
The Hall of Heroes is composed of tributes to the inductees. Among the Hall of Fame's displays is Sigma 7, the Mercury spacecraft piloted by Wally Schirra which orbited the Earth six times in 1962, and the Gemini 9A capsule flown by Gene Cernan and Thomas P. Stafford in 1966. An Astronaut Adventure room includes simulators for use by children.
The spacesuit worn by Gus Grissom during his 1961 Liberty Bell 7 Mercury flight is on display and has been the subject of a dispute between NASA and Grissom's heirs and supporters since 2002. The spacesuit, along with other Grissom artifacts, were loaned to the original owners of the Hall of Fame by the Grissom family when it opened. After the Hall of Fame went into bankruptcy and was taken over by a NASA contractor in 2002, the family requested that all their items be returned. All of the items were returned to Grissom's family except the spacesuit, because both NASA and the Grissoms claim ownership of it. NASA claims Grissom checked out the spacesuit for a show and tell at his son's school, and then never returned it, while the Grissoms claim Gus rescued the spacesuit from a scrap heap.
The John F. Kennedy Space Center (KSC, originally known as the NASA Launch Operations Center), located on Merritt Island, Florida, is one of the National Aeronautics and Space Administration's (NASA) ten field centers. Since December 1968, KSC has been NASA's primary launch center of human spaceflight. Launch operations for the Apollo, Skylab and Space Shuttle programs were carried out from Kennedy Space Center Launch Complex 39 and managed by KSC.[4] Located on the east coast of Florida, KSC is adjacent to Cape Canaveral Space Force Station (CCSFS). The management of the two entities work very closely together, share resources and operate facilities on each other's property.
Though the first Apollo flights and all Project Mercury and Project Gemini flights took off from the then-Cape Canaveral Air Force Station, the launches were managed by KSC and its previous organization, the Launch Operations Directorate. Starting with the fourth Gemini mission, the NASA launch control center in Florida (Mercury Control Center, later the Launch Control Center) began handing off control of the vehicle to the Mission Control Center in Houston, shortly after liftoff; in prior missions it held control throughout the entire mission.
Additionally, the center manages launch of robotic and commercial crew missions and researches food production and In-Situ Resource Utilization for off-Earth exploration. Since 2010, the center has worked to become a multi-user spaceport through industry partnerships, even adding a new launch pad (LC-39C) in 2015.
There are about 700 facilities and buildings grouped across the center's 144,000 acres (580 km2). Among the unique facilities at KSC are the 525-foot (160 m) tall Vehicle Assembly Building for stacking NASA's largest rockets, the Launch Control Center, which conducts space launches at KSC, the Operations and Checkout Building, which houses the astronauts dormitories and suit-up area, a Space Station factory, and a 3-mile (4.8 km) long Shuttle Landing Facility. There is also a Visitor Complex open to the public on site.
Since 1949, the military had been performing launch operations at what would become Cape Canaveral Space Force Station. In December 1959, the Department of Defense transferred 5,000 personnel and the Missile Firing Laboratory to NASA to become the Launch Operations Directorate under NASA's Marshall Space Flight Center.
President John F. Kennedy's 1961 goal of a crewed lunar landing by 1970 required an expansion of launch operations. On July 1, 1962, the Launch Operations Directorate was separated from MSFC to become the Launch Operations Center (LOC). Also, Cape Canaveral was inadequate to host the new launch facility design required for the mammoth 363-foot (111 m) tall, 7,500,000-pound-force (33,000 kN) thrust Saturn V rocket, which would be assembled vertically in a large hangar and transported on a mobile platform to one of several launch pads. Therefore, the decision was made to build a new LOC site located adjacent to Cape Canaveral on Merritt Island.
NASA began land acquisition in 1962, buying title to 131 square miles (340 km2) and negotiating with the state of Florida for an additional 87 square miles (230 km2). The major buildings in KSC's Industrial Area were designed by architect Charles Luckman. Construction began in November 1962, and Kennedy visited the site twice in 1962, and again just a week before his assassination on November 22, 1963.
On November 29, 1963, the facility was given its current name by President Lyndon B. Johnson under Executive Order 11129. Johnson's order joined both the civilian LOC and the military Cape Canaveral station ("the facilities of Station No. 1 of the Atlantic Missile Range") under the designation "John F. Kennedy Space Center", spawning some confusion joining the two in the public mind. NASA Administrator James E. Webb clarified this by issuing a directive stating the Kennedy Space Center name applied only to the LOC, while the Air Force issued a general order renaming the military launch site Cape Kennedy Air Force Station.
Located on Merritt Island, Florida, the center is north-northwest of Cape Canaveral on the Atlantic Ocean, midway between Miami and Jacksonville on Florida's Space Coast, due east of Orlando. It is 34 miles (55 km) long and roughly six miles (9.7 km) wide, covering 219 square miles (570 km2). KSC is a major central Florida tourist destination and is approximately one hour's drive from the Orlando area. The Kennedy Space Center Visitor Complex offers public tours of the center and Cape Canaveral Space Force Station.
The KSC Industrial Area, where many of the center's support facilities are located, is 5 miles (8 km) south of LC-39. It includes the Headquarters Building, the Operations and Checkout Building and the Central Instrumentation Facility. The astronaut crew quarters are in the O&C; before it was completed, the astronaut crew quarters were located in Hangar S[39] at the Cape Canaveral Missile Test Annex (now Cape Canaveral Space Force Station). Located at KSC was the Merritt Island Spaceflight Tracking and Data Network station (MILA), a key radio communications and spacecraft tracking complex.
Facilities at the Kennedy Space Center are directly related to its mission to launch and recover missions. Facilities are available to prepare and maintain spacecraft and payloads for flight. The Headquarters (HQ) Building houses offices for the Center Director, library, film and photo archives, a print shop and security. When the KSC Library first opened, it was part of the Army Ballistic Missile Agency. However, in 1965, the library moved into three separate sections in the newly opened NASA headquarters before eventually becoming a single unit in 1970. The library contains over four million items related to the history and the work at Kennedy. As one of ten NASA center libraries in the country, their collection focuses on engineering, science, and technology. The archives contain planning documents, film reels, and original photographs covering the history of KSC. The library is not open to the public but is available for KSC, Space Force, and Navy employees who work on site. Many of the media items from the collection are digitized and available through NASA's KSC Media Gallery or through their more up-to-date Flickr gallery.
A new Headquarters Building was completed in 2019 as part of the Central Campus consolidation. Groundbreaking began in 2014.
The center operated its own 17-mile (27 km) short-line railroad. This operation was discontinued in 2015, with the sale of its final two locomotives. A third had already been donated to a museum. The line was costing $1.3 million annually to maintain.
The Kennedy Space Center Visitor Complex, operated by Delaware North since 1995, has a variety of exhibits, artifacts, displays and attractions on the history and future of human and robotic spaceflight. Bus tours of KSC originate from here. The complex also includes the separate Apollo/Saturn V Center, north of the VAB and the United States Astronaut Hall of Fame, six miles west near Titusville. There were 1.5 million visitors in 2009. It had some 700 employees.
It was announced on May 29, 2015, that the Astronaut Hall of Fame exhibit would be moved from its current location to another location within the Visitor Complex to make room for an upcoming high-tech attraction entitled "Heroes and Legends". The attraction, designed by Orlando-based design firm Falcon's Treehouse, opened November 11, 2016.
In March 2016, the visitor center unveiled the new location of the iconic countdown clock at the complex's entrance; previously, the clock was located with a flagpole at the press site. The clock was originally built and installed in 1969 and listed with the flagpole in the National Register of Historic Places in January 2000. In 2019, NASA celebrated the 50th anniversary of the Apollo program, and the launch of Apollo 10 on May 18. In summer of 2019, Lunar Module 9 (LM-9) was relocated to the Apollo/Saturn V Center as part of an initiative to rededicate the center and celebrate the 50th anniversary of the Apollo Program.
The John F. Kennedy Space Center (KSC, originally known as the NASA Launch Operations Center), located on Merritt Island, Florida, is one of the National Aeronautics and Space Administration's (NASA) ten field centers. Since December 1968, KSC has been NASA's primary launch center of American spaceflight, research, and technology. Launch operations for the Apollo, Skylab and Space Shuttle programs were carried out from Kennedy Space Center Launch Complex 39 and managed by KSC. Located on the east coast of Florida, KSC is adjacent to Cape Canaveral Space Force Station (CCSFS). The management of the two entities work very closely together, share resources and operate facilities on each other's property.
Though the first Apollo flights and all Project Mercury and Project Gemini flights took off from the then-Cape Canaveral Air Force Station, the launches were managed by KSC and its previous organization, the Launch Operations Directorate. Starting with the fourth Gemini mission, the NASA launch control center in Florida (Mercury Control Center, later the Launch Control Center) began handing off control of the vehicle to the Mission Control Center in Houston, shortly after liftoff; in prior missions it held control throughout the entire mission.
Additionally, the center manages launch of robotic and commercial crew missions and researches food production and in-situ resource utilization for off-Earth exploration. Since 2010, the center has worked to become a multi-user spaceport through industry partnerships, even adding a new launch pad (LC-39C) in 2015.
There are about 700 facilities and buildings grouped throughout the center's 144,000 acres (580 km2). Among the unique facilities at KSC are the 525-foot (160 m) tall Vehicle Assembly Building for stacking NASA's largest rockets, the Launch Control Center, which conducts space launches at KSC, the Operations and Checkout Building, which houses the astronauts dormitories and suit-up area, a Space Station factory, and a 3-mile (4.8 km) long Shuttle Landing Facility. There is also a Visitor Complex on site that is open to the public.
Since 1949, the military had been performing launch operations at what would become Cape Canaveral Space Force Station. In December 1959, the Department of Defense transferred 5,000 personnel and the Missile Firing Laboratory to NASA to become the Launch Operations Directorate under NASA's Marshall Space Flight Center.
President John F. Kennedy's 1961 goal of a crewed lunar landing by 1970 required an expansion of launch operations. On July 1, 1962, the Launch Operations Directorate was separated from MSFC to become the Launch Operations Center (LOC). Also, Cape Canaveral was inadequate to host the new launch facility design required for the mammoth 363-foot (111 m) tall, 7,500,000-pound-force (33,000 kN) thrust Saturn V rocket, which would be assembled vertically in a large hangar and transported on a mobile platform to one of several launch pads. Therefore, the decision was made to build a new LOC site located adjacent to Cape Canaveral on Merritt Island.
NASA began land acquisition in 1962, buying title to 131 square miles (340 km2) and negotiating with the state of Florida for an additional 87 square miles (230 km2). The major buildings in KSC's Industrial Area were designed by architect Charles Luckman. Construction began in November 1962, and Kennedy visited the site twice in 1962, and again just a week before his assassination on November 22, 1963.
On November 29, 1963, the facility was named by President Lyndon B. Johnson under Executive Order 11129. Johnson's order joined both the civilian LOC and the military Cape Canaveral station ("the facilities of Station No. 1 of the Atlantic Missile Range") under the designation "John F. Kennedy Space Center", spawning some confusion joining the two in the public mind. NASA Administrator James E. Webb clarified this by issuing a directive stating the Kennedy Space Center name applied only to the LOC, while the Air Force issued a general order renaming the military launch site Cape Kennedy Air Force Station.
Located on Merritt Island, Florida, the center is north-northwest of Cape Canaveral on the Atlantic Ocean, midway between Miami and Jacksonville on Florida's Space Coast, due east of Orlando. It is 34 miles (55 km) long and roughly six miles (9.7 km) wide, covering 219 square miles (570 km2). KSC is a major central Florida tourist destination and is approximately one hour's drive from the Orlando area. The Kennedy Space Center Visitor Complex offers public tours of the center and Cape Canaveral Space Force Station.
From 1967 through 1973, there were 13 Saturn V launches, including the ten remaining Apollo missions after Apollo 7. The first of two uncrewed flights, Apollo 4 (Apollo-Saturn 501) on November 9, 1967, was also the first rocket launch from KSC. The Saturn V's first crewed launch on December 21, 1968, was Apollo 8's lunar orbiting mission. The next two missions tested the Lunar Module: Apollo 9 (Earth orbit) and Apollo 10 (lunar orbit). Apollo 11, launched from Pad A on July 16, 1969, made the first Moon landing on July 20. The Apollo 11 launch included crewmembers Neil Armstrong, Michael Collins, and Buzz Aldrin, and attracted a record-breaking 650 million television viewers. Apollo 12 followed four months later. From 1970 to 1972, the Apollo program concluded at KSC with the launches of missions 13 through 17.
On May 14, 1973, the last Saturn V launch put the Skylab space station in orbit from Pad 39A. By this time, the Cape Kennedy pads 34 and 37 used for the Saturn IB were decommissioned, so Pad 39B was modified to accommodate the Saturn IB, and used to launch three crewed missions to Skylab that year, as well as the final Apollo spacecraft for the Apollo–Soyuz Test Project in 1975.
As the Space Shuttle was being designed, NASA received proposals for building alternative launch-and-landing sites at locations other than KSC, which demanded study. KSC had important advantages, including its existing facilities; location on the Intracoastal Waterway; and its southern latitude, which gives a velocity advantage to missions launched in easterly near-equatorial orbits. Disadvantages included: its inability to safely launch military missions into polar orbit, since spent boosters would be likely to fall on the Carolinas or Cuba; corrosion from the salt air; and frequent cloudy or stormy weather. Although building a new site at White Sands Missile Range in New Mexico was seriously considered, NASA announced its decision in April 1972 to use KSC for the shuttle. Since the Shuttle could not be landed automatically or by remote control, the launch of Columbia on April 12, 1981 for its first orbital mission STS-1, was NASA's first crewed launch of a vehicle that had not been tested in prior uncrewed launches.
In 1976, the VAB's south parking area was the site of Third Century America, a science and technology display commemorating the U.S. Bicentennial. Concurrent with this event, the U.S. flag was painted on the south side of the VAB. During the late 1970s, LC-39 was reconfigured to support the Space Shuttle. Two Orbiter Processing Facilities were built near the VAB as hangars with a third added in the 1980s.
KSC's 2.9-mile (4.7 km) Shuttle Landing Facility (SLF) was the orbiters' primary end-of-mission landing site, although the first KSC landing did not take place until the tenth flight, when Challenger completed STS-41-B on February 11, 1984; the primary landing site until then was Edwards Air Force Base in California, subsequently used as a backup landing site. The SLF also provided a return-to-launch-site (RTLS) abort option, which was not utilized. The SLF is among the longest runways in the world.
On October 28, 2009, the Ares I-X launch from Pad 39B was the first uncrewed launch from KSC since the Skylab workshop in 1973.
Beginning in 1958, NASA and military worked side by side on robotic mission launches (previously referred to as unmanned), cooperating as they broke ground in the field. In the early 1960s, NASA had as many as two robotic mission launches a month. The frequent number of flights allowed for quick evolution of the vehicles, as engineers gathered data, learned from anomalies and implemented upgrades. In 1963, with the intent of KSC ELV work focusing on the ground support equipment and facilities, a separate Atlas/Centaur organization was formed under NASA's Lewis Center (now Glenn Research Center (GRC)), taking that responsibility from the Launch Operations Center (aka KSC).
Though almost all robotics missions launched from the Cape Canaveral Space Force Station (CCSFS), KSC "oversaw the final assembly and testing of rockets as they arrived at the Cape." In 1965, KSC's Unmanned Launch Operations directorate became responsible for all NASA uncrewed launch operations, including those at Vandenberg Space Force Base. From the 1950s to 1978, KSC chose the rocket and payload processing facilities for all robotic missions launching in the U.S., overseeing their near launch processing and checkout. In addition to government missions, KSC performed this service for commercial and foreign missions also, though non-U.S. government entities provided reimbursement. NASA also funded Cape Canaveral Space Force Station launch pad maintenance and launch vehicle improvements.
All this changed with the Commercial Space Launch Act of 1984, after which NASA only coordinated its own and National Oceanic and Atmospheric Administration (NOAA) ELV launches. Companies were able to "operate their own launch vehicles" and utilize NASA's launch facilities. Payload processing handled by private firms also started to occur outside of KSC. Reagan's 1988 space policy furthered the movement of this work from KSC to commercial companies. That same year, launch complexes on Cape Canaveral Air Force Force Station started transferring from NASA to Air Force Space Command management.
In the 1990s, though KSC was not performing the hands-on ELV work, engineers still maintained an understanding of ELVs and had contracts allowing them insight into the vehicles so they could provide knowledgeable oversight. KSC also worked on ELV research and analysis and the contractors were able to utilize KSC personnel as a resource for technical issues. KSC, with the payload and launch vehicle industries, developed advances in automation of the ELV launch and ground operations to enable competitiveness of U.S. rockets against the global market.
In 1998, the Launch Services Program (LSP) formed at KSC, pulling together programs (and personnel) that already existed at KSC, GRC, Goddard Space Flight Center, and more to manage the launch of NASA and NOAA robotic missions. Cape Canaveral Space Force Station and VAFB are the primary launch sites for LSP missions, though other sites are occasionally used. LSP payloads such as the Mars Science Laboratory have been processed at KSC before being transferred to a launch pad on Cape Canaveral Space Force Station.
On 16 November 2022, at 06:47:44 UTC the Space Launch System (SLS) was launched from Complex 39B as part of the Artemis 1 mission.
As the International Space Station modules design began in the early 1990s, KSC began to work with other NASA centers and international partners to prepare for processing before launch onboard the Space Shuttles. KSC utilized its hands-on experience processing the 22 Spacelab missions in the Operations and Checkout Building to gather expectations of ISS processing. These experiences were incorporated into the design of the Space Station Processing Facility (SSPF), which began construction in 1991. The Space Station Directorate formed in 1996. KSC personnel were embedded at station module factories for insight into their processes.
From 1997 to 2007, KSC planned and performed on the ground integration tests and checkouts of station modules: three Multi-Element Integration Testing (MEIT) sessions and the Integration Systems Test (IST). Numerous issues were found and corrected that would have been difficult to nearly impossible to do on-orbit.
Today KSC continues to process ISS payloads from across the world before launch along with developing its experiments for on orbit. The proposed Lunar Gateway would be manufactured and processed at the Space Station Processing Facility.
The following are current programs and initiatives at Kennedy Space Center:
Commercial Crew Program
Exploration Ground Systems Program
NASA is currently designing the next heavy launch vehicle known as the Space Launch System (SLS) for continuation of human spaceflight.
On December 5, 2014, NASA launched the first uncrewed flight test of the Orion Multi-Purpose Crew Vehicle (MPCV), currently under development to facilitate human exploration of the Moon and Mars.
Launch Services Program
Educational Launch of Nanosatellites (ELaNa)
Research and Technology
Artemis program
Lunar Gateway
International Space Station Payloads
Camp KSC: educational camps for schoolchildren in spring and summer, with a focus on space, aviation and robotics.
The KSC Industrial Area, where many of the center's support facilities are located, is 5 miles (8 km) south of LC-39. It includes the Headquarters Building, the Operations and Checkout Building and the Central Instrumentation Facility. The astronaut crew quarters are in the O&C; before it was completed, the astronaut crew quarters were located in Hangar S at the Cape Canaveral Missile Test Annex (now Cape Canaveral Space Force Station). Located at KSC was the Merritt Island Spaceflight Tracking and Data Network station (MILA), a key radio communications and spacecraft tracking complex.
Facilities at the Kennedy Space Center are directly related to its mission to launch and recover missions. Facilities are available to prepare and maintain spacecraft and payloads for flight. The Headquarters (HQ) Building houses offices for the Center Director, library, film and photo archives, a print shop and security. When the KSC Library first opened, it was part of the Army Ballistic Missile Agency. However, in 1965, the library moved into three separate sections in the newly opened NASA headquarters before eventually becoming a single unit in 1970. The library contains over four million items related to the history and the work at Kennedy. As one of ten NASA center libraries in the country, their collection focuses on engineering, science, and technology. The archives contain planning documents, film reels, and original photographs covering the history of KSC. The library is not open to the public but is available for KSC, Space Force, and Navy employees who work on site. Many of the media items from the collection are digitized and available through NASA's KSC Media Gallery Archived December 6, 2020, at the Wayback Machine or through their more up-to-date Flickr gallery.
A new Headquarters Building was completed in 2019 as part of the Central Campus consolidation. Groundbreaking began in 2014.
The center operated its own 17-mile (27 km) short-line railroad. This operation was discontinued in 2015, with the sale of its final two locomotives. A third had already been donated to a museum. The line was costing $1.3 million annually to maintain.
The Neil Armstrong Operations and Checkout Building (O&C) (previously known as the Manned Spacecraft Operations Building) is a historic site on the U.S. National Register of Historic Places dating back to the 1960s and was used to receive, process, and integrate payloads for the Gemini and Apollo programs, the Skylab program in the 1970s, and for initial segments of the International Space Station through the 1990s. The Apollo and Space Shuttle astronauts would board the astronaut transfer van to launch complex 39 from the O&C building.
The three-story, 457,000-square-foot (42,500 m2) Space Station Processing Facility (SSPF) consists of two enormous processing bays, an airlock, operational control rooms, laboratories, logistics areas and office space for support of non-hazardous Space Station and Shuttle payloads to ISO 14644-1 class 5 standards. Opened in 1994, it is the largest factory building in the KSC industrial area.
The Vertical Processing Facility (VPF) features a 71-by-38-foot (22 by 12 m) door where payloads that are processed in the vertical position are brought in and manipulated with two overhead cranes and a hoist capable of lifting up to 35 short tons (32 t).
The Hypergolic Maintenance and Checkout Area (HMCA) comprises three buildings that are isolated from the rest of the industrial area because of the hazardous materials handled there. Hypergolic-fueled modules that made up the Space Shuttle Orbiter's reaction control system, orbital maneuvering system and auxiliary power units were stored and serviced in the HMCF.
The Multi-Payload Processing Facility is a 19,647 square feet (1,825.3 m2) building used for Orion spacecraft and payload processing.
The Payload Hazardous Servicing Facility (PHSF) contains a 70-by-110-foot (21 by 34 m) service bay, with a 100,000-pound (45,000 kg), 85-foot (26 m) hook height. It also contains a 58-by-80-foot (18 by 24 m) payload airlock. Its temperature is maintained at 70 °F (21 °C).[55]
The Blue Origin rocket manufacturing facility is located immediately south of the KSC visitor complex. Completed in 2019, it serves as the company's factory for the manufacture of New Glenn orbital rockets.
Launch Complex 39 (LC-39) was originally built for the Saturn V, the largest and most powerful operational launch vehicle until the Space Launch System, for the Apollo crewed Moon landing program. Since the end of the Apollo program in 1972, LC-39 has been used to launch every NASA human space flight, including Skylab (1973), the Apollo–Soyuz Test Project (1975), and the Space Shuttle program (1981–2011).
Since December 1968, all launch operations have been conducted from launch pads A and B at LC-39. Both pads are on the ocean, 3 miles (4.8 km) east of the VAB. From 1969 to 1972, LC-39 was the "Moonport" for all six Apollo crewed Moon landing missions using the Saturn V, and was used from 1981 to 2011 for all Space Shuttle launches.
Human missions to the Moon required the large three-stage Saturn V rocket, which was 363 feet (111 meters) tall and 33 feet (10 meters) in diameter. At KSC, Launch Complex 39 was built on Merritt Island to accommodate the new rocket. Construction of the $800 million project began in November 1962. LC-39 pads A and B were completed by October 1965 (planned Pads C, D and E were canceled), the VAB was completed in June 1965, and the infrastructure by late 1966.
The complex includes: the Vehicle Assembly Building (VAB), a 130,000,000 cubic feet (3,700,000 m3) hangar capable of holding four Saturn Vs. The VAB was the largest structure in the world by volume when completed in 1965.
a transporter capable of carrying 5,440 tons along a crawlerway to either of two launch pads;
a 446-foot (136 m) mobile service structure, with three Mobile Launcher Platforms, each containing a fixed launch umbilical tower;
the Launch Control Center; and
a news media facility.
Launch Complex 48 (LC-48) is a multi-user launch site under construction for small launchers and spacecraft. It will be located between Launch Complex 39A and Space Launch Complex 41, with LC-39A to the north and SLC-41 to the south. LC-48 will be constructed as a "clean pad" to support multiple launch systems with differing propellant needs. While initially only planned to have a single pad, the complex is capable of being expanded to two at a later date.
As a part of promoting commercial space industry growth in the area and the overall center as a multi-user spaceport, KSC leases some of its properties. Here are some major examples:
Exploration Park to multiple users (partnership with Space Florida)
Shuttle Landing Facility to Space Florida (who contracts use to private companies)
Orbiter Processing Facility (OPF)-3 to Boeing (for CST-100 Starliner)
Launch Complex 39A, Launch Control Center Firing Room 4 and land for SpaceX's Roberts Road facility (Hanger X) to SpaceX
O&C High Bay to Lockheed Martin (for Orion processing)
Land for FPL's Space Coast Next Generation Solar Energy Center to Florida Power and Light (FPL)
Hypergolic Maintenance Facility (HMF) to United Paradyne Corporation (UPC)
The Kennedy Space Center Visitor Complex, operated by Delaware North since 1995, has a variety of exhibits, artifacts, displays and attractions on the history and future of human and robotic spaceflight. Bus tours of KSC originate from here. The complex also includes the separate Apollo/Saturn V Center, north of the VAB and the United States Astronaut Hall of Fame, six miles west near Titusville. There were 1.5 million visitors in 2009. It had some 700 employees.
It was announced on May 29, 2015, that the Astronaut Hall of Fame exhibit would be moved from its current location to another location within the Visitor Complex to make room for an upcoming high-tech attraction entitled "Heroes and Legends". The attraction, designed by Orlando-based design firm Falcon's Treehouse, opened November 11, 2016.
In March 2016, the visitor center unveiled the new location of the iconic countdown clock at the complex's entrance; previously, the clock was located with a flagpole at the press site. The clock was originally built and installed in 1969 and listed with the flagpole in the National Register of Historic Places in January 2000. In 2019, NASA celebrated the 50th anniversary of the Apollo program, and the launch of Apollo 10 on May 18. In summer of 2019, Lunar Module 9 (LM-9) was relocated to the Apollo/Saturn V Center as part of an initiative to rededicate the center and celebrate the 50th anniversary of the Apollo Program.
Historic locations
NASA lists the following Historic Districts at KSC; each district has multiple associated facilities:
Launch Complex 39: Pad A Historic District
Launch Complex 39: Pad B Historic District
Shuttle Landing Facility (SLF) Area Historic District
Orbiter Processing Historic District
Solid Rocket Booster (SRB) Disassembly and Refurbishment Complex Historic District
NASA KSC Railroad System Historic District
NASA-owned Cape Canaveral Space Force Station Industrial Area Historic District
There are 24 historic properties outside of these historic districts, including the Space Shuttle Atlantis, Vehicle Assembly Building, Crawlerway, and Operations and Checkout Building.[71] KSC has one National Historic Landmark, 78 National Register of Historic Places (NRHP) listed or eligible sites, and 100 Archaeological Sites.
Further information: John F. Kennedy Space Center MPS
Other facilities
The Rotation, Processing and Surge Facility (RPSF) is responsible for the preparation of solid rocket booster segments for transportation to the Vehicle Assembly Building (VAB). The RPSF was built in 1984 to perform SRB operations that had previously been conducted in high bays 2 and 4 of the VAB at the beginning of the Space Shuttle program. It was used until the Space Shuttle's retirement, and will be used in the future by the Space Launch System[75] (SLS) and OmegA rockets.
DigiCrafted
How can traditional textile craft soften the digital aesthetic of 3D printed textiles ?
New advances in 3D printing technology allow for the design of complex geometry and structures that would be impossible to produce with traditional manufacturing processes. Such technology promotes a rather homogeneous digital aesthetic. This is especially true for 3D printed textiles, often developed with an engineering approach rather than textile design perspective.
The aim of this project is to explore the yet undefined space where traditional textiles and additive technologies are combined; using traditional craft techniques. This introduces a new visual language that challenges and softens the digital aesthetic associated with 3D printed surfaces.
Combining labour-intensive needlecraft and textile manipulation techniques with 3-D printed elements, Digicrafted looks into new design possibilities for hybrid design connecting the digital and the handmade.
In 1880 having been taught the use of simple lathes and machinery by his uncle,
and encouraged by William Morris, William Arthur Smith Benson began metalwork production
in Fulham, London. As his business grew Benson closely followed developments in technology, mastering all the processes of casting, turning, folding and riveting many variations of interchangeable components. He opened a showroom in Bond Street in 1887 displaying
light fittings, fireplace accessories, plant stands and hollow-ware, in silver, copper, brass,
iron and polished steel, patenting many of his popular designs to protect them from the
array of sub-standard copies that flooded the market.
WAS Benson was at the forefront of electric installation in homes all over Britain, advising on suitable lighting schemes and installation. In 1893 he electrified Philip Webb’s latest architectural commission, Standen, near East Grinstead, Sussex, now owned by the National Trust.
His metalwork and lighting designs reached iconic status, sold in galleries throughout Europe,
and in 1896 when William Morris died it was Benson with a colleague who bought Morris & Co and ran it alongside his own company until he resigned in 1917.
Benson attracted much acclaim for his metalwork designs and manufacturing processes.
The Studio Magazine of Decorative Arts, The Magazine of Art, and Herman Muthesius in
Das Englische Haus, were among the many who applauded his innovations.
Lancia Hyena:
Overview:
ManufacturerZagato on Lancia mechanicals
Also calledLancia Delta Zagato Hyena
Production1992–1996
24 made
AssemblyRho, Milan
DesignerMarco Pedracini at Zagato
Body and chassis
ClassSports car
Body style2-door coupé
LayoutTransverse front-engine, four-wheel drive
RelatedLancia Delta Integrale "Evoluzione"
Powertrain
Engine2.0 L I4 (turbocharged petrol)
Transmission5-speed manual
The Lancia Hyena was a 2-door coupé made in small numbers by Italian coachbuilder Zagato on the basis of the Delta HF Integrale "Evoluzione".
History:
The Hyena was born thanks to the initiative of Dutch classic car restorer and collector Paul V.J. Koot, who desired a coupé version of the multiple World Rally Champion HF Integrale. He turned to Zagato, where Hyena was designed in 1990 by Marco Pedracini. A first prototype was introduced at the Brussels Motor Show in January 1992.
Decision was taken to put the Hyena into limited production. Fiat refused to participate in the project supplying bare HF Integrale chassis, which complicated the manufacturing process: the Hyena had to be produced from fully finished HF Integrales, privately purchased at Lancia dealers. Koot's Lusso Service took care of procuring and stripping the donor cars in the Netherlands; they were then sent to Zagato in Milan to have the new body built and for final assembly. All of this made the Hyena very expensive to build and they were sold for around 140,000 Swiss francs or $75,000 (£49,430).
A production run of 75 examples was initially planned, but only 25 Hyenas were completed between 1992 and 1993.
Specifications:
The Zagato bodywork made use of aluminium alloys and composite materials; the interior featured new dashboard, console and door cards made entirely from carbon fibre. Thanks to these weight saving measures the Hyena was some 150 kilograms (330 lb) lighter than the original HF Integrale, about 15% of its overall weight. The two-litre turbo engine was upgraded from 205 to 250 PS (184 kW), and the car could accelerate from 0–100 km in 5.4 seconds.
[Text from Wikipedia]
en.wikipedia.org/wiki/Lancia_Delta#Lancia_Hyena
This miniland-scale Lego Lancia Hyena (1992 - Zagato) has been created for Flickr LUGNuts' 92nd Build Challenge, - "Stuck in the 90's", - all about vehicles from the decade of the 1990s.
It is chilly and rainy in Arizona for Super Bowl 48 but BMW turned up the heat with their all-electric i3 and hybrid i8 sports car. To add additional flavor to the recipe New England Patriots’ starting corner Kyle Arrington and wife VaShonda Arrington joined the experience for the energetic weekend festivities.
Kyle spent a few days in both vehicles during his activities, which included stops at the Nike Football Super Bowl Hospitality Gifting Suite at the immaculate Scottsdale Resort & Conference Center, the NFL Experience, family outings and dinner with his spouse. Vashonda’s centerpiece moment was raising funds for the Off the Field Player’s Wives Association’s “14th Annual Super Bowl Fashion Show” held at the upscale Scottsdale Fashion Mall. The wives, kids and a handful of former NFL players walked the runway with grace and style. Guests included Holly Robinson Peete, Antonio Cromardie, Steve Young, Kevin Hart and many more. She enjoyed the earthly interior of the i3 and spoke passionately about the need regarding increased sustainability in the world.
The mind is driven by thoughts and fueled by inventive answers. The i3 is 100% pure electric and the i8 is a plug-in hybrid sports car, which means its power is sourced from both gasoline and electricity. The i8 is comprised of a Life module and a Drive module. The 3-liter gasoline motor is placed in the rear and the smaller electric engine is housed up front. In addition, the i8 is essentially an AWD vehicle channeling traction from both axles simultaneously but doesn’t utilize the company’s hallmark xDrive system. A few common i8 performance specs include:
•0 to 60 mph = 4.2 seconds
•Top speed = 155 mph (electronically limited)
•Electric only top speed = 75 mph
•Pure electric range = 22 miles
Born electric, the i3 is engineered with BMW’s LifeDrive architecture, which is also structured into two categories, the Life Module and the Drive Module. Comprised of high-strength carbon, the Life Module protects and provides comfort for the driver and passengers. The second platform, the Drive Module, encompasses the electric drive system, the suspension and the HVAC. Since the car is lighter, the liquid-cooled lithium-ion battery (developed in-house by BMW) is smaller and only needs three hours for a full stage-2 (240-volt) charge. Additionally, BMW attempts to use as much renewable energy as possible for the manufacturing process of the carbon fiber i3.
The journey continues towards educating the world on the benefits of going green. BMW is both an innovator and leader in this technology category and has already spearheaded a positive movement. Expect more BMW i products down the line since they have only just begun.
STS028-078-036 Omaha, Nebraska, and Council Bluffs, Iowa, U.S.A. August 1989
Visible in this northeast-looking, low-oblique photograph are Omaha on the west bank of the Missouri River and Council Bluffs on the east bank. Omaha, the largest city in Nebraska, sits in the heart of the United States farming region and is one of the largest livestock markets and meat processing centers in the world. Much of the city’s industry is devoted to food processing and the manufacture of farm machinery, fertilizers, computer components, telephone equipment, furniture, clothing, insecticides, soap, cans, chemicals, paint, oil refinery equipment, and airplane and automobile parts. It is the home of many insurance companies and a center for medical research and treatment. Council Bluffs, an important trade and industrial center, manufactures processed foods, cast iron pipes, farm equipment, electronic equipment, and fabricated metals. The confluence of the Missouri River and Platte River is discernible south of Omaha.
As part of the required course knowledge pupils need to be able to outline the process involved in taking a square wooden blank and preparing it for turning between centres. These pictures depict that process chronologically.
Stage 1 * Preparation of wooden blank. Cut to size. Sand square. Mark across diagonals. Centre punch the centre point. Use spring dividers to mark circumference. Repeat on other end.
Stage 2 * Plane off corners down to circumference line. This takes cross section from square to octagon. This reduces force on cutting toll in initial prep of blank. Mount between fork [driven] centre and dead [or live ] centre at tailstock end. Apply grease a dead centre end. apply force from tailstock end to force fork into material at driven end. Adjust toolstock height to suit. Check for clearance.
Stage 3 * Roughout using scraper to diameter. Use combination of gouges and skew chisels to add beads and other decorative detailing as required. Ensure spindle speed is appropriate for material and cross section under consideration. Obey all safety instructions.
The Sochi 2014 medals are being manufactured by the experts at Adamas, a Sochi 2014 Supplier and Russia’s leading jeweler. Each medal takes up to 18 hours to be created and the latest design and technology processes have been used in the manufacturing process.
BlueEdge - Mach 8-10 Hypersonic Commercial Aircraft, 220 Passenger Hypersonic Commercial Plane - Imaginactive Media Release ICAO
Courtesy of Imaginactive, ICAO, Charles Bombardier, and Martin Rico. Media Release of High Quality Renderings for mainstream media.
IO Aircraft: www.ioaircraft.com/hypersonic/blueedge.php
Imaginactive: imaginactive.org/2019/02/blue-edge/
Martin Rico, Industrial Graphics Designed: www.linkedin.com/in/mjrico/
Seating: 220 | Crew 2+4
Length: 195ft | Span: 93ft
Engines: 4 U-TBCC (Unified Turbine Based Combined Cycle) +1 Aerospike for sustained 2G acceleration to Mach 10.
Fuel: H2 (Compressed Hydrogen)
Cruising Altitude: 100,000-125,000ft
Airframe: 75% Proprietary Composites
Operating Costs, Similar to a 737. $7,000-$15,000hr, including averaged maintenence costs
Iteration 3 (Full release of IT3, Monday January 14, 2019)
IO Aircraft www.ioaircraft.com
Drew Blair www.linkedin.com/in/drew-b-25485312/
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Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
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Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
Officials ceremonially cut the ribbon officially opening the Vandenberg Air Force Base education center Feb. 27. Cutting the ribbon are (L to R): Chief Master Sgt. Ryan Petersen, 30th Space Wing command chief; Col. Keith Balts, 30th Space Wing commander; Col. Kim Colloton, U.S. Army Corps of Engineers Los Angeles District commander; Lt. Col. Gregory Marty, 30th Force Support Squadron commander; Barbara Bennie, Force Development Flight chief; and Col. Brent McArthur, 30th Space Wing vice commander.
VANDENBERG AIR FORCE BASE, Calif.--Officials cut the ribbon Feb. 27 ceremonially opening a brand new education center that will help Airmen stationed at this central coast base achieve their personal and professional education goals.
The $14.2 million center replaced a 60-year-old elementary school campus, which had been used as the education center for more than 40 years.
"We hear the dollar value, and I just can't stress how precious those dollars are in today's fiscal environment," said Col. Keith Balts, 30th Space Wing commander. "The fact that we get to do military construction at all, especially something for the quality of our Airmen and their families, says a lot about the importance we place on education."
One of the center's first customers was Senior Airman Antoine Marshall, 30th Force Support Squadron, who joined the Air Force four years ago with an associate degree in criminal justice.
"I just took the analyzing and interpreting literature CLEP (College Level Examination Program) exam," said Marshall, who's pursuing a bachelor's degree in organizational management. "It was my first one--I passed it. I'm extremely happy!"
The 38,384-square-foot facility includes 20 classrooms, computer lab, testing center, and 75-seat auditorium, as well as offices for various colleges and universities serving the Vandenberg community.
"I think the facility is great," said Marshall. "Overall, it provides a better environment to work and study, and it's just comfortable."
The design-build project was constructed by Corps contractor Teehee-Straub, a joint-venture team from Oceanside, Calif.
"The design was quite extensive, just due to the detail and the location," said Keith Hamilton, project executive for Teehee-Straub. "The site work was very challenging, and I think that was something that brought a lot of character to this building."
Teehee-Straub's 21st century design included sustainable development and energy efficiencies, such as light pollution reduction and water use reduction.
"This is a sustainable building," said Col. Kim Colloton, U.S. Army Corps of Engineers Los Angeles District commander. "We can build our buildings smartly, so they can do more; it's more [money] that can go back into the base."
During construction, 75 percent of the construction and demolition debris was diverted from landfills and redirected back to the manufacturing process as reusable and recyclable material. Walk-off mats, exhaust systems and filtered heating and cooling improves indoor air quality. Low-flow fixtures and faucets, high-efficiency drip irrigation and drought-tolerant landscaping reduce potable water use by more than 40 percent. All are efficiencies the contractor believes will achive a LEED Silver rating (Leadership in Energy & Environmental Design, a Green Building Council rating system).
"We're just proud to be part of this," said Teehee-Straub managing partner Richard Straub. "The Corps of Engineers is one of our favorite customers, and we love supporting the Air Force in doing a job that will educate a lot of servicemen."
It is chilly and rainy in Arizona for Super Bowl 48 but BMW turned up the heat with their all-electric i3 and hybrid i8 sports car. To add additional flavor to the recipe New England Patriots’ starting corner Kyle Arrington and wife VaShonda Arrington joined the experience for the energetic weekend festivities.
Kyle spent a few days in both vehicles during his activities, which included stops at the Nike Football Super Bowl Hospitality Gifting Suite at the immaculate Scottsdale Resort & Conference Center, the NFL Experience, family outings and dinner with his spouse. Vashonda’s centerpiece moment was raising funds for the Off the Field Player’s Wives Association’s “14th Annual Super Bowl Fashion Show” held at the upscale Scottsdale Fashion Mall. The wives, kids and a handful of former NFL players walked the runway with grace and style. Guests included Holly Robinson Peete, Antonio Cromardie, Steve Young, Kevin Hart and many more. She enjoyed the earthly interior of the i3 and spoke passionately about the need regarding increased sustainability in the world.
The mind is driven by thoughts and fueled by inventive answers. The i3 is 100% pure electric and the i8 is a plug-in hybrid sports car, which means its power is sourced from both gasoline and electricity. The i8 is comprised of a Life module and a Drive module. The 3-liter gasoline motor is placed in the rear and the smaller electric engine is housed up front. In addition, the i8 is essentially an AWD vehicle channeling traction from both axles simultaneously but doesn’t utilize the company’s hallmark xDrive system. A few common i8 performance specs include:
•0 to 60 mph = 4.2 seconds
•Top speed = 155 mph (electronically limited)
•Electric only top speed = 75 mph
•Pure electric range = 22 miles
Born electric, the i3 is engineered with BMW’s LifeDrive architecture, which is also structured into two categories, the Life Module and the Drive Module. Comprised of high-strength carbon, the Life Module protects and provides comfort for the driver and passengers. The second platform, the Drive Module, encompasses the electric drive system, the suspension and the HVAC. Since the car is lighter, the liquid-cooled lithium-ion battery (developed in-house by BMW) is smaller and only needs three hours for a full stage-2 (240-volt) charge. Additionally, BMW attempts to use as much renewable energy as possible for the manufacturing process of the carbon fiber i3.
The journey continues towards educating the world on the benefits of going green. BMW is both an innovator and leader in this technology category and has already spearheaded a positive movement. Expect more BMW i products down the line since they have only just begun.
VANDENBERG AIR FORCE BASE, Calif.--Officials cut the ribbon Feb. 27 ceremonially opening a brand new education center that will help Airmen stationed at this central coast base achieve their personal and professional education goals.
The $14.2 million center replaced a 60-year-old elementary school campus, which had been used as the education center for more than 40 years.
"We hear the dollar value, and I just can't stress how precious those dollars are in today's fiscal environment," said Col. Keith Balts, 30th Space Wing commander. "The fact that we get to do military construction at all, especially something for the quality of our Airmen and their families, says a lot about the importance we place on education."
One of the center's first customers was Senior Airman Antoine Marshall, 30th Force Support Squadron, who joined the Air Force four years ago with an associate degree in criminal justice.
"I just took the analyzing and interpreting literature CLEP (College Level Examination Program) exam," said Marshall, who's pursuing a bachelor's degree in organizational management. "It was my first one--I passed it. I'm extremely happy!"
The 38,384-square-foot facility includes 20 classrooms, computer lab, testing center, and 75-seat auditorium, as well as offices for various colleges and universities serving the Vandenberg community.
"I think the facility is great," said Marshall. "Overall, it provides a better environment to work and study, and it's just comfortable."
The design-build project was constructed by Corps contractor Teehee-Straub, a joint-venture team from Oceanside, Calif.
"The design was quite extensive, just due to the detail and the location," said Keith Hamilton, project executive for Teehee-Straub. "The site work was very challenging, and I think that was something that brought a lot of character to this building."
Teehee-Straub's 21st century design included sustainable development and energy efficiencies, such as light pollution reduction and water use reduction.
"This is a sustainable building," said Col. Kim Colloton, U.S. Army Corps of Engineers Los Angeles District commander. "We can build our buildings smartly, so they can do more; it's more [money] that can go back into the base."
During construction, 75 percent of the construction and demolition debris was diverted from landfills and redirected back to the manufacturing process as reusable and recyclable material. Walk-off mats, exhaust systems and filtered heating and cooling improves indoor air quality. Low-flow fixtures and faucets, high-efficiency drip irrigation and drought-tolerant landscaping reduce potable water use by more than 40 percent. All are efficiencies the contractor believes will achive a LEED Silver rating (Leadership in Energy & Environmental Design, a Green Building Council rating system).
"We're just proud to be part of this," said Teehee-Straub managing partner Richard Straub. "The Corps of Engineers is one of our favorite customers, and we love supporting the Air Force in doing a job that will educate a lot of servicemen."
Silver 1oz Ingot .925 Purity Sterling Silver
Sterling silver is an alloy of silver containing 92.5% by mass of silver and 7.5% by mass of other metals, usually copper. The sterling silver standard has a minimum millesimal fineness of 925.
Fine silver, for example 99.9% pure silver, is generally too soft for producing functional objects; therefore, the silver is usually alloyed with copper to give it strength while preserving the ductility and appearance of the precious metal. Other metals can replace the copper, usually with the intention of improving various properties of the basic sterling alloy such as reducing casting porosity, eliminating firescale, and increasing resistance to tarnish. These replacement metals include germanium, zinc and platinum, as well as a variety of other additives, including silicon and boron. Alloys such as argentium silver have appeared in recent decades.
History
Norman silver pennies changed designs every three years. This two-star design (possible origin of the word "sterling"), issued by William the Conqueror, is from 1077-1080.
The sterling alloy originated in continental Europe and was being used for commerce as early as the 12th century in the area that is now northern Germany.
In England the composition of sterling silver was subject to official assay at some date before 1158, during the reign of Henry II, but its purity was probably regulated from centuries earlier, in Saxon times. A piece of sterling silver dating from Henry II's reign was used as a standard in the Trial of the Pyx until it was deposited at the Royal Mint in 1843. It bears the royal stamp ENRI. REX ("King Henry") but this was added later, in the reign of Henry III. The first legal definition of sterling silver appeared in 1275, when a statute of Edward I specified that 12 ounces of silver for coinage should contain 11 ounces 2 1⁄4 pennyweights of silver and 17 3⁄4 pennyweights of alloy, with 20 pennyweights to the Troy ounce.
In Colonial America, sterling silver was used for currency and general goods as well. Between 1634 and 1776, some 500 silversmiths created items in the “New World” ranging from simple buckles to ornate Rococo coffee pots. Although silversmiths of this era were typically familiar with all precious metals, they primarily worked in sterling silver. The colonies lacked an assay office during this time (the first would be established in 1814), so American silversmiths adhered to the standard set by the London Goldsmiths Company: sterling silver consisted of 91.5 - 92.5% by weight silver and 8.5-7.5 wt% copper. Stamping each of their pieces with their personal maker's mark, colonial silversmiths relied upon their own status to guarantee the quality and composition of their products.
Colonial silversmiths used many of the techniques developed by those in Europe. Casting was frequently the first step in manufacturing silver pieces, as silver workers would melt down sterling silver into easily manageable ingots. Occasionally, they would create small components (e.g. teapot legs) by casting silver into iron or graphite molds, but it was rare for an entire piece to be fabricated via casting. Next, silversmiths would forge the ingots into the shapes they desired, often hammering the thinned silver against specially shaped dies to "mass produce" simple shapes like the oval end of a spoon. This process occurred at room temperature, and thus is called “cold-working”.The repeated strikes of the hammer work hardened (sterling) silver, causing it to become brittle and difficult to manipulate. To combat work-hardening, silversmiths would anneal their pieces—heat it to a dull red and then quench it in water--to relieve the stresses in the material and return it to a more ductile state. Hammering required more time than all other silver manufacturing processes, and therefore accounted for the majority of labor costs. Silversmiths would then seam parts together to create incredibly complex and artistic items, sealing the gaps with a solder of 80 wt% silver and 20 wt% bronze. Finally, they would file and polish their work to remove all seams, finishing off with engraving and a maker’s mark.
The American revolutionary Paul Revere was regarded as one of the best silversmiths from this “Golden Age of American Silver.” Following the Revolutionary War, Revere acquired and made use of a silver rolling mill from England. Not only did the rolling mill increase his rate of production—hammering and flattening silver took most of a silversmith’s time—he was able to roll and sell silver of appropriate, uniform thickness to other silversmiths. He retired a wealthy artisan, his success partly due to this strategic investment: although he is celebrated for his beautiful hollowware, Revere made his fortune primarily on low-end goods produced by the mill, such as flatware. With the onset of the first Industrial Revolution, many smiths followed suit and silversmithing as an artistic occupation eventually dwindled.
From about 1840 to 1940 in the United States and Europe, sterling silver cutlery (US: 'flatware') became de rigueur when setting a proper table. There was a marked increase in the number of silver companies that emerged during that period. The height of the silver craze was during the 50-year period from 1870 to 1920. Flatware lines during this period sometimes included up to 100 different types of pieces.
A number of factors converged to make sterling fall out of favor around the time of World War II. The cost of labor rose (sterling pieces were all still mostly handmade, with only the basics being done by machine). Only the wealthy could afford the large number of servants required for fancy dining with ten courses. And changes in aesthetics resulted in people desiring simpler dinnerware that was easier to clean.
BlueEdge - Mach 8-10 Hypersonic Commercial Aircraft, 220 Passenger Hypersonic Commercial Plane - Imaginactive Media Release ICAO
Courtesy of Imaginactive, ICAO, Charles Bombardier, and Martin Rico. Media Release of High Quality Renderings for mainstream media.
IO Aircraft: www.ioaircraft.com/hypersonic/blueedge.php
Imaginactive: imaginactive.org/2019/02/blue-edge/
Martin Rico, Industrial Graphics Designed: www.linkedin.com/in/mjrico/
Seating: 220 | Crew 2+4
Length: 195ft | Span: 93ft
Engines: 4 U-TBCC (Unified Turbine Based Combined Cycle) +1 Aerospike for sustained 2G acceleration to Mach 10.
Fuel: H2 (Compressed Hydrogen)
Cruising Altitude: 100,000-125,000ft
Airframe: 75% Proprietary Composites
Operating Costs, Similar to a 737. $7,000-$15,000hr, including averaged maintenence costs
Iteration 3 (Full release of IT3, Monday January 14, 2019)
IO Aircraft www.ioaircraft.com
Drew Blair www.linkedin.com/in/drew-b-25485312/
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Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
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Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
BlueEdge - Mach 8-10 Hypersonic Commercial Aircraft, 220 Passenger Hypersonic Commercial Plane - Imaginactive Media Release ICAO
Courtesy of Imaginactive, ICAO, Charles Bombardier, and Martin Rico. Media Release of High Quality Renderings for mainstream media.
IO Aircraft: www.ioaircraft.com/hypersonic/blueedge.php
Imaginactive: imaginactive.org/2019/02/blue-edge/
Martin Rico, Industrial Graphics Designed: www.linkedin.com/in/mjrico/
Seating: 220 | Crew 2+4
Length: 195ft | Span: 93ft
Engines: 4 U-TBCC (Unified Turbine Based Combined Cycle) +1 Aerospike for sustained 2G acceleration to Mach 10.
Fuel: H2 (Compressed Hydrogen)
Cruising Altitude: 100,000-125,000ft
Airframe: 75% Proprietary Composites
Operating Costs, Similar to a 737. $7,000-$15,000hr, including averaged maintenence costs
Iteration 3 (Full release of IT3, Monday January 14, 2019)
IO Aircraft www.ioaircraft.com
Drew Blair www.linkedin.com/in/drew-b-25485312/
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hypersonic plane, hypersonic aircraft, Imaginactive, ICAO, International Civil Aviation Orginization, Charles Bombardier, Martin Rico, hypersonic commercial plane, hypersonic commercial aircraft, hypersonic airline, tbcc, glide breaker, fighter plane, hyperonic fighter, boeing phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, defense science, missile defense agency, aerospike, hydrogen, hydrogen storage, hydrogen fueled, hydrogen aircraft, virgin airlines, united airlines, sas, finnair ,emirates airlines, ANA, JAL, airlines, military, physics, airline, british airways, air france
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Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
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Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
The winch and cable for a sill box. A relic of the 1940s when Northwich was home to a thriving soda-ash industry based on locally produced salt. As a result of the manufacture process a sludge like lime waste product was produced and as storage become an increasing problem the Neumann Flashes were identified as a suitable storage area. As the level of the sediment increased then the winch was used to raise the sill box.
en.wikipedia.org/wiki/History_of_Northwich#Chemical_industry
Title: This 121 1/2 foot tower atop the St. Thomas Assembly Plant performed an important function in the automobile manufacturing process. It also provided an ideal place for Ford to hang its shingle, in this case a large blue and white 'oval.' By day and when illuminated at night, the tower and sign could be seen for miles. This June 1968 photograph shows the sign being hoisted into position. The Ford St. Thomas Assembly Plant will close on September 15, 2011 after nearly 44 years in operation.
Creator(s): St. Thomas Times-Journal
Bygone Days Publication Date: September 13, 2011
Original Publication Date: June 5, 1968
Reference No.: C8 Sh4 B2 F1 49a
Credit: Elgin County Archives, St. Thomas Times-Journal fonds
One of the problems with my old MacBook Pro was the unresponsive keyboard/trackpad due to the improper installation of the flex cable in the manufacturing process. This is a common problem with old MacBook Pros.
Apple Store quoted me $400-1,000 for the fix, so I decided to fix this by myself. The replacement cable was just $20.
After the fix, my old MacBook Pro runs flawlessly :-)
The sculptor Kai Nielsen visited Kähler for the first time in 1921. Only three years before his death.
During those three years, he was very productive, but many of his works were discarded due to his extreme self-criticism. His ambition was to achieve broad reach. He would rather sell his works and produce thousands of copies than have them on display in a museum.
He produced a number of small figures, which were copies of his larger sculptures in order to disseminate knowledge of his art. This was also a good idea in terms of his earnings.
Kai Nielsen teamed with Thirslund and organised a large production of figures in 1922. These figures were made in old bronze moulds, which had previously been used to cast bronze sculptures.
The names of these figures were just as creative as the manufacturing process: ”Dovendyret”, ”Susanne i badet”, ”Prinsessen på ærten”, ”Eva på æblet”, ”Nina på kuglen” and ”Globetrotteren”, ("Sloth", "Susanna in the bath", "Princess and the Pea", "Eve at the apple", "Nina on the ball" and "Globetrotting") just to mention a few.
The figures became very popular in Denmark and abroad. After a trip to Denmark, a dealer brought ”Prinsessen på ærten” (Princess and the Pea) back with him to San Francisco and put it on display at his shop. However, a US women’s organisation was strongly opposed to ”Princess and the Pea” as they believed that the figure thrust her abdomen forward.
Even though Kai Nielsen’s objective was to bring art to the people, the question is whether he was actually known for this work. Most people will probably remember him for his large sculptures such as ”Vandmoderen” (Water Mother), which is located in the winter garden at the Glyptothek in Copenhagen.
With thanks to:
It is chilly and rainy in Arizona for Super Bowl 48 but BMW turned up the heat with their all-electric i3 and hybrid i8 sports car. To add additional flavor to the recipe New England Patriots’ starting corner Kyle Arrington and wife VaShonda Arrington joined the experience for the energetic weekend festivities.
Kyle spent a few days in both vehicles during his activities, which included stops at the Nike Football Super Bowl Hospitality Gifting Suite at the immaculate Scottsdale Resort & Conference Center, the NFL Experience, family outings and dinner with his spouse. Vashonda’s centerpiece moment was raising funds for the Off the Field Player’s Wives Association’s “14th Annual Super Bowl Fashion Show” held at the upscale Scottsdale Fashion Mall. The wives, kids and a handful of former NFL players walked the runway with grace and style. Guests included Holly Robinson Peete, Antonio Cromardie, Steve Young, Kevin Hart and many more. She enjoyed the earthly interior of the i3 and spoke passionately about the need regarding increased sustainability in the world.
The mind is driven by thoughts and fueled by inventive answers. The i3 is 100% pure electric and the i8 is a plug-in hybrid sports car, which means its power is sourced from both gasoline and electricity. The i8 is comprised of a Life module and a Drive module. The 3-liter gasoline motor is placed in the rear and the smaller electric engine is housed up front. In addition, the i8 is essentially an AWD vehicle channeling traction from both axles simultaneously but doesn’t utilize the company’s hallmark xDrive system. A few common i8 performance specs include:
•0 to 60 mph = 4.2 seconds
•Top speed = 155 mph (electronically limited)
•Electric only top speed = 75 mph
•Pure electric range = 22 miles
Born electric, the i3 is engineered with BMW’s LifeDrive architecture, which is also structured into two categories, the Life Module and the Drive Module. Comprised of high-strength carbon, the Life Module protects and provides comfort for the driver and passengers. The second platform, the Drive Module, encompasses the electric drive system, the suspension and the HVAC. Since the car is lighter, the liquid-cooled lithium-ion battery (developed in-house by BMW) is smaller and only needs three hours for a full stage-2 (240-volt) charge. Additionally, BMW attempts to use as much renewable energy as possible for the manufacturing process of the carbon fiber i3.
The journey continues towards educating the world on the benefits of going green. BMW is both an innovator and leader in this technology category and has already spearheaded a positive movement. Expect more BMW i products down the line since they have only just begun.
Editor's Note: This image is one of a series showing engineering technology at NASA's Marshall Space Flight Center in Huntsville, Ala.
Caption: At the unveiling of the new Tank Dome Manufacturing Process are, from left: Marshall Center Deputy Gene Goldman;Lesa Rowe, Director of Langley Research Center, Hampton, Va.; Dr. Axel Roenneke, head of Strategy, Business Development and Sale for MT Aerospace , Augsburg, Germany; Dr. Ray O. Johnson, Vice President of Technology for Lockheed Martin Space Systems, Denver; Diane Hope, Program Element Manager for the Exploration Technology Development Porgram at Langley; Dr. Sandeep Shah, Manufacturing and Assembly Subsystem Manager for the upper state project at Marshall; Louis F. Lollar, Contract Technical Manager for the Exploration of Advanced Capabilities at Marshall; and Dr. Raymond "Corky" Clinton, Acting Manager for the Science & Mission Systems Office at Marshall.
Credit: NASA/MSFC/D. Higginbotham
Discovery STO - 70 Ton, Single Stage to Orbit Fixed Wing Aircraft - Space Plane - Hypersonic Plane, U-TBCC / Unified Turbine Based Combined Cycle & Aerospike
Iteration 1, Mach 8-10 in amtmosphere, 195ft long, Heavy Lift Single Stage To Orbit Fixed Wing Aircraft. 70 TONS, ie 140,000 LBS, 60 ft X 15ft X 15ft payload bay. Up in the Falcon Heavy and Delta IV class, except not $400 million to launch giant payloads into orbit, but below $250 per lbs, or about $28 million to launch giant payloads, and normalized orbital flight, as normal as a 737 commercial flight. Load up, refuel, take off in an afternoon. I estimate this aircraft would cost about $750 million each for space capable. In atmosphere commercial, roughly $300 million each for a 200 passenger M8-10 (not designed yet)
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www.ioaircraft.com/hypersonic/ranger.php
Drew Blair
www.linkedin.com/in/drew-b-25485312/
--------------
Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
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tbcc, glide breaker, fighter plane, hyperonic fighter, stealth fighter, boeing phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, defense science, missile defense agency, aerospike, vtol, vertical take off, air taxi, personal air vehicle, boeing go fly prize, go fly prize,
Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
Lego is a line of plastic construction toys manufactured by the Lego Group, a privately held company based in Billund, Denmark. Lego consists of variously colored interlocking plastic bricks made of acrylonitrile butadiene styrene that accompany an array of gears, figurines called minifigures, and various other parts. Its pieces can be assembled and connected in many ways to construct objects, including vehicles, buildings, and working robots. Anything constructed can be taken apart again, and the pieces reused to make new things.
The Lego Group began manufacturing the interlocking toy bricks in 1949. Moulding is done in Denmark, Hungary, Mexico, and China. Brick decorations and packaging are done at plants in the former three countries and in the Czech Republic. Annual production of the bricks averages approximately 36 billion, or about 1140 elements per second.
Films, games competitions, and eight Legoland amusement parks have been developed under the brand. One of Europe's biggest companies, Lego is the largest toy manufacturer in the world by sales. As of July 2015, 600 billion Lego parts had been produced.
History
The Lego Group began in the workshop of Ole Kirk Christiansen (1891–1958), a carpenter from Billund, Denmark, who began making wooden toys in 1932. In 1934, his company came to be called "Lego", derived from the Danish phrase leg godt which means "play well". In 1947, Lego expanded to begin producing plastic toys. In 1949 the business began producing, among other new products, an early version of the now familiar interlocking bricks, calling them "Automatic Binding Bricks". These bricks were based on the Kiddicraft Self-Locking Bricks, invented by Hilary Page in 1939 and patented in the United Kingdom in 1940 before being displayed at the 1947 Earl's Court Toy Fair. Lego had received a sample of the Kiddicraft bricks from the supplier of an injection-molding machine that it purchased. The bricks, originally manufactured from cellulose acetate, were a development of the traditional stackable wooden blocks of the time.
The Lego Group's motto, "only the best is good enough" (Danish: det bedste er ikke for godt, literally "the best isn't excessively good") was created in 1936. Christiansen created the motto, still used today, to encourage his employees never to skimp on quality, a value he believed in strongly. By 1951, plastic toys accounted for half of the company's output, even though the Danish trade magazine Legetøjs-Tidende ("Toy Times"), visiting the Lego factory in Billund in the early 1950s, wrote that plastic would never be able to replace traditional wooden toys. Although a common sentiment, Lego toys seem to have become a significant exception to the dislike of plastic in children's toys, due in part to the high standards set by Ole Kirk.
By 1954, Christiansen's son, Godtfred, had become the junior managing director of the Lego Group. It was his conversation with an overseas buyer that led to the idea of a toy system. Godtfred saw the immense potential in Lego bricks to become a system for creative play, but the bricks still had some problems from a technical standpoint: Their locking ability was still limited, and they were not yet versatile. In 1958, the modern brick design was developed; it took five years to find the right material for it, ABS (acrylonitrile butadiene styrene) polymer. A patent application for the modern Lego brick design was filed in Denmark on 28 January 1958 and in various other countries in the subsequent few years.
The Lego Group's Duplo product line was introduced in 1969 and is a range of blocks whose lengths measure twice the width, height, and depth of standard Lego blocks and are aimed towards younger children. In 1978, Lego produced the first minifigures, which have since become a staple in most sets.
In May 2011, Space Shuttle Endeavour mission STS-134 brought 13 Lego kits to the International Space Station, where astronauts built models to see how they would react in microgravity, as a part of the Lego Bricks in Space program. In May 2013, the largest model ever created, made of over 5 million bricks, was displayed in New York City; a one-to-one scale model of a Star Wars X-wing fighter. Other record breakers include a 34-metre (112 ft) tower and a 4 km (2.5 mi) railway.
In February 2015, marketing consulting company Brand Finance ranked Lego as the "world's most powerful brand", overtaking Ferrari.
Lego bricks have acquired a reputation for causing extreme pain when stepped on.
Design
Lego pieces of all varieties constitute a universal system. Despite variations in the design and the purposes of individual pieces over the years, each remains compatible in some way with existing pieces. Lego bricks from 1958 still interlock with those made presently, and Lego sets for young children are compatible with those made for teenagers. Six bricks of 2 × 4 studs can be combined in 915,103,765 ways.
Each piece must be manufactured to an exacting degree of precision. When two pieces are engaged, they must fit firmly, yet be easily disassembled. The machines that manufacture Lego bricks have tolerances as small as 10 micrometres.
Primary concept and development work for the toy takes place at the Billund headquarters, where the company employs approximately 120 designers. The company also has smaller design offices in the UK, Spain, Germany, and Japan which are tasked with developing products aimed specifically at their respective national markets. The average development period for a new product is around twelve months, split into three stages. The first is to identify market trends and developments, including contact by the designers directly with the market; some are stationed in toy shops close to holidays, while others interview children. The second stage is the design and development of the product based on the results of the first stage. As of September 2008 the design teams use 3D modelling software to generate CAD drawings from initial design sketches. The designs are then prototyped using an in-house stereolithography machine. These prototypes are presented to the entire project team for comment and testing by parents and children during the "validation" process. Designs may then be altered in accordance with the results from the focus groups. Virtual models of completed Lego products are built concurrently with the writing of the user instructions. Completed CAD models are also used in the wider organisation for marketing and packaging.
Lego Digital Designer is an official piece of Lego software for Mac OS X and Windows which allows users to create their own digital Lego designs. The program once allowed customers to order custom designs with a service to ship physical models from Digital Designer to consumers; the service ended in 2012.
Manufacturing
Since 1963, Lego pieces have been manufactured from acrylonitrile butadiene styrene (ABS). As of September 2008, Lego engineers use the NX CAD/CAM/CAE PLM software suite to model the elements. The software allows the parts to be optimised by way of mould flow and stress analysis. Prototype moulds are sometimes built before the design is committed to mass production. The ABS plastic is heated to 232 °C (450 °F) until it reaches a dough-like consistency. It is then injected into the moulds using forces of between 25 and 150 tonnes and takes approximately 15 seconds to cool. The moulds are permitted a tolerance of up to twenty micrometres to ensure the bricks remain connected. Human inspectors check the output of the moulds to eliminate significant variations in colour or thickness. According to the Lego Group, about eighteen bricks out of every million fail to meet the standard required.
Lego factories recycle all but about 1 percent of their plastic waste from the manufacturing process. If the plastic cannot be re-used in Lego bricks, it is processed and sold on to industries that can make use of it. Lego, in 2018, set a self-imposed 2030 deadline to find a more eco-friendly alternative to the ABS plastic.
Manufacturing of Lego bricks occurs at several locations around the world. Moulding is done in Billund, Denmark; Nyíregyháza, Hungary; Monterrey, Mexico; and most recently in Jiaxing, China. Brick decorations and packaging are done at plants in the former three countries and in Kladno in the Czech Republic. The Lego Group estimates that in five decades it has produced 400 billion Lego blocks. Annual production of the bricks averages approximately 36 billion, or about 1140 elements per second. According to an article in BusinessWeek in 2006, Lego could also be considered the world's number-one tyre manufacturer; the factory produces about 306 million small rubber tyres a year. The claim was reiterated in 2012.
In December 2012, the BBC's More or Less radio program asked the Open University's engineering department to determine "how many Lego bricks, stacked one on top of the other, it would take for the weight to destroy the bottom brick?" Using a hydraulic testing machine, members of the department determined the average maximum force a 2×2 Lego brick can stand is 4,240 newtons. Since an average 2×2 Lego brick has a mass of 1.152 grams (0.0406 oz), according to their calculations it would take a stack of 375,000 bricks to cause the bottom brick to collapse, which represents a stack 3,591 metres (11,781 ft) in height.
Private tests have shown several thousand assembly-disassembly cycles before the bricks begin to wear out, although Lego tests show fewer cycles.
In 2018, Lego announced that it will be using bio-derived polyethylene to make its botanical elements (parts such as leaves, bushes and trees). The New York Times reported the company's footprint that year was "about a million tons of carbon dioxide each year" and that it was investing about 1 billion kroner and hiring 100 people to work on changes. The paper reported that Lego's researchers "have already experimented with around 200 alternatives." In 2020, Lego announced that it would cease packaging its products in single-use plastic bags and would instead be using recyclable paper bags. In 2021, the company said it would aim to produce its bricks without using crude oil, by using recycled polyethylene terephthalate bottles, but in 2023 it reversed this decision, having found that this did not reduce its carbon dioxide emissions.
Set themes
Since the 1950s, the Lego Group has released thousands of sets with a variety of themes, including space, pirates, trains, (European) castle, dinosaurs, undersea exploration, and wild west, as well as wholly original themes like Bionicle and Hero Factory. Some of the classic themes that continue to the present day include Lego City (a line of sets depicting city life introduced in 1973) and Lego Technic (a line aimed at emulating complex machinery, introduced in 1977).
Over the years, the company has licensed themes from numerous cartoon and film franchises and some from video games. These include Batman, Indiana Jones, Pirates of the Caribbean, Harry Potter, Star Wars, Marvel, and Minecraft. Although some of these themes, Lego Star Wars and Lego Indiana Jones, had highly successful sales, the company expressed in 2015 a desire to rely more upon their own characters and classic themes and less upon such licensed themes. Some sets include references to other themes such as a Bionicle mask in one of the Harry Potter sets. Discontinued sets may become a collectable and command value on the black market.
For the 2012 Summer Olympics in London, Lego released a special Team GB Minifigures series exclusively in the United Kingdom to mark the opening of the games. For the 2016 Summer Olympics and 2016 Summer Paralympics in Rio de Janeiro, Lego released a kit with the Olympic and Paralympic mascots Vinicius and Tom.
One of the largest commercially produced Lego sets was a minifig-scaled edition of the Star Wars Millennium Falcon. Designed by Jens Kronvold Fredericksen, it was released in 2007 and contained 5,195 pieces. It was surpassed by a 5,922-piece Taj Mahal. A redesigned Millennium Falcon retook the top spot in 2017 with 7,541 pieces. Since then, the Millennium Falcon has been superseded by the Lego Art World Map at 11,695 pieces, the Lego Titanic at 9,090 pieces, and the Lego Architect Colosseum at 9,036 pieces.
In 2022, Lego introduced its Eiffel Tower. The set consists of 10,000 parts and reaches a height of 149 cm, which makes it the tallest set and tower but the second in number of parts after the World Map.
Robotics themes
Main articles: Lego Mindstorms, Lego Mindstorms NXT, Lego Mindstorms NXT 2.0, and Lego Mindstorms EV3
The company also initiated a robotics line of toys called 'Mindstorms' in 1999, and has continued to expand and update this range ever since. The roots of the product originate from a programmable brick developed at the MIT Media Lab, and the name is taken from a paper by Seymour Papert, a computer scientist and educator who developed the educational theory of constructionism, and whose research was at times funded by the Lego Group.
The programmable Lego brick which is at the heart of these robotics sets has undergone several updates and redesigns, with the latest being called the 'EV3' brick, being sold under the name of Lego Mindstorms EV3. The set includes sensors that detect touch, light, sound and ultrasonic waves, with several others being sold separately, including an RFID reader.
The intelligent brick can be programmed using official software available for Windows and Mac computers, and is downloaded onto the brick via Bluetooth or a USB cable. There are also several unofficial programs and compatible programming languages that have been made to work with the brick, and many books have been written to support this community.
There are several robotics competitions which use the Lego robotics sets. The earliest is Botball, a national U.S. middle- and high-school competition stemming from the MIT 6.270 Lego robotics tournament. Other Lego robotics competitions include FIRST LEGO League Discover for children ages 4–6, FIRST LEGO League Explore for students ages 6–9 and FIRST Lego League Challenge for students ages 9–16 (age 9–14 in the United States, Canada, and Mexico). These programs offer real-world engineering challenges to participants. FIRST LEGO League Challenge uses LEGO-based robots to complete tasks, FIRST LEGO League Explore participants build models out of Lego elements, and FIRST LEGO League Discover participants use Duplo. In its 2019–2020 season, there were 38,609 FIRST LEGO League Challenge teams and 21,703 FIRST LEGO League Explore teams around the world. The international RoboCup Junior football competition involves extensive use of Lego Mindstorms equipment which is often pushed to its extreme limits.
The capabilities of the Mindstorms range have now been harnessed for use in Iko Creative Prosthetic System, a prosthetic limbs system designed for children. Designs for these Lego prosthetics allow everything from mechanical diggers to laser-firing spaceships to be screwed on to the end of a child's limb. Iko is the work of the Chicago-based Colombian designer Carlos Arturo Torres, and is a modular system that allows children to customise their own prosthetics with the ease of clicking together plastic bricks. Designed with Lego's Future Lab, the Danish toy company's experimental research department, and Cirec, a Colombian foundation for physical rehabilitation, the modular prosthetic incorporates myoelectric sensors that register the activity of the muscle in the stump and send a signal to control movement in the attachment. A processing unit in the body of the prosthetic contains an engine compatible with Lego Mindstorms, the company's robotics line, which lets the wearer build an extensive range of customised, programmable limbs.
In popular culture
Lego's popularity is demonstrated by its wide representation and usage in many cultural works, including books, films, and art. It has even been used in the classroom as a teaching tool. In the US, Lego Education North America is a joint venture between Pitsco, Inc. and the educational division of the Lego Group.
In 1998, Lego bricks were one of the original inductees into the National Toy Hall of Fame at The Strong in Rochester, New York.
"Lego" is commonly used as a mass noun ("some Lego") or, in American English, as a countable noun with plural "Legos", to refer to the bricks themselves, but as is common for trademarks, Lego group insists on the name being used as an adjective when referring to a product (as in "LEGO bricks").
It is chilly and rainy in Arizona for Super Bowl 48 but BMW turned up the heat with their all-electric i3 and hybrid i8 sports car. To add additional flavor to the recipe New England Patriots’ starting corner Kyle Arrington and wife VaShonda Arrington joined the experience for the energetic weekend festivities.
Kyle spent a few days in both vehicles during his activities, which included stops at the Nike Football Super Bowl Hospitality Gifting Suite at the immaculate Scottsdale Resort & Conference Center, the NFL Experience, family outings and dinner with his spouse. Vashonda’s centerpiece moment was raising funds for the Off the Field Player’s Wives Association’s “14th Annual Super Bowl Fashion Show” held at the upscale Scottsdale Fashion Mall. The wives, kids and a handful of former NFL players walked the runway with grace and style. Guests included Holly Robinson Peete, Antonio Cromardie, Steve Young, Kevin Hart and many more. She enjoyed the earthly interior of the i3 and spoke passionately about the need regarding increased sustainability in the world.
The mind is driven by thoughts and fueled by inventive answers. The i3 is 100% pure electric and the i8 is a plug-in hybrid sports car, which means its power is sourced from both gasoline and electricity. The i8 is comprised of a Life module and a Drive module. The 3-liter gasoline motor is placed in the rear and the smaller electric engine is housed up front. In addition, the i8 is essentially an AWD vehicle channeling traction from both axles simultaneously but doesn’t utilize the company’s hallmark xDrive system. A few common i8 performance specs include:
•0 to 60 mph = 4.2 seconds
•Top speed = 155 mph (electronically limited)
•Electric only top speed = 75 mph
•Pure electric range = 22 miles
Born electric, the i3 is engineered with BMW’s LifeDrive architecture, which is also structured into two categories, the Life Module and the Drive Module. Comprised of high-strength carbon, the Life Module protects and provides comfort for the driver and passengers. The second platform, the Drive Module, encompasses the electric drive system, the suspension and the HVAC. Since the car is lighter, the liquid-cooled lithium-ion battery (developed in-house by BMW) is smaller and only needs three hours for a full stage-2 (240-volt) charge. Additionally, BMW attempts to use as much renewable energy as possible for the manufacturing process of the carbon fiber i3.
The journey continues towards educating the world on the benefits of going green. BMW is both an innovator and leader in this technology category and has already spearheaded a positive movement. Expect more BMW i products down the line since they have only just begun.
This is a Screen Porch in Gaithersburg, Maryland that features Fiberon Horizon decking and Shoreline white vinyl handrails. The balusters in the handrails are deckorators black aluminum. This is an example of a low maintenance screen room with plenty of space to entertain family and friends.
Invest in Low-Maintenance Decking
If you’re planning to invest in a beautiful deck, then a low-maintenance, high-enjoyment life is certainly your goal. Typical wood decks need to be cleaned, stained, and cared for to ensure their longevity. No doubt you’ve wondered if there are other options that will minimize caretaking responsibilities and expand your leisure time.
We recommend Fiberon Horizon Decking as an alternative to traditional wood decking. You want longevity? Fiberon Horizon Decking is covered by a 25-year performance and stain-and-fade warranty. Horizon is also imbued with PermaTech Innovation, a cutting-edge technology that offers unrivaled resistance to stains, scratches, splinters, fading, decay, termites, and mold – everything you want in a deck but never thought you could have. The performance and durability of your deck will easily match its beauty when you opt for this modified composite decking.
To satisfy the green-friendly component, Horizon is produced in an energy-efficient, virtually waste-free manufacturing process and composed of over 50 percent recycled materials. But that doesn’t mean you’re limited in the colors of decking. Staining your Horizon deck is unnecessary as this product is available in six rich, fade-resistant shades – ipe, rosewood, Tudor brown, castle gray, bronze, and slate – and composed of exotic, hardwood tones with natural-looking grain patterns.
Make an error in installation? Flip the board and start again – Horizon boards have been engineered to be reversible; their design offers identical grains on both sides, therefore creating less scrap. Another bonus: Horizon railing is available to complement the decking, and also features a smooth, low-maintenance exterior to protect against the elements, from sunlight to snow.
Fiberon began as a manufacturer of wood-plastic composite decking, intending to conquer the market of alternative decking materials. After a few key acquisitions, Fiberon established itself as a leader in this marketplace and continue to innovate, notably with their Horizon decking and its traditional composite decking core for strength and unprecedented surface material that resists wear and tear.
Outdoor living is growing in popularity – an outdoor leisure space is practically as integral a feature to a home as a kitchen, particularly for resale value. Now you can have the recreation area you want, without any added drudgery.
www.designbuildersmd.com/en_us/blog/low-maintenance-decki...
designbuildersmd.blogspot.com/2011/12/low-maintenance-dec...
In the heart of Old Town, historic factory is among the oldest in Grasse ... Indeed the current premises sheltered from their beginning in 1782, a perfume factory. In 1926, after the famous painter Jean Honoré Fragonard, it takes the name of Parfumerie Fragonard. Since then, every day, we produce are our perfumes, cosmetics and soaps in a respectful environment of tradition. We would be happy to welcome you and offer you a guided tour during which you will discover the different manufacturing processes and packaging our products. At the end of your visit, you can admire 3000 years of history of perfume through our private museum.
Dedicated to the perfume and aromatic plants, Flower Factory is surrounded by a beautiful garden scented plants ... the gates of Grasse, this contemporary factory opened in 1986 is equipped with very modern machinery for the manufacture and packaging of our products.
WORKSHOP ODOR "Perfumer's Apprentice"
Available on the French Riviera and Paris, in factories, workshops Perfumers Apprentice can discover the expertise of Perfumer: the history of perfume, raw materials and different extraction methods.
Experience unforgettable sense centered on the composition of a toilet water (100 ml) in aromatic notes of citrus and orange blossom, by assembling the different species made available. A fun and exciting experience in the world of perfumery, which proposes the course led by the teacher, the bottle and its bag, apron "apprentice" printed Fragonard, the diploma signed by the teacher and the summary of the composition .
One of our guides will accompany you as a result of the workshop for a visit "Prestige" from our factory.
Located in one of the oldest houses in the historic center of the city, this perfume offers original creations of Didier Gaglewski.
Didier Gaglewski, "nose" in Grasse, began offering its achievements in the framework Living in Provence and in Paris, Germany and Switzerland. Both "artisan", "artist", he decided to offer his achievements directly driven by the idea that the quality, originality and respect perfume composition will dress with fun, humor and quality its customers.
Requiring each of its perfumes, made in the privacy of his laboratory, took several months of research. In partnership with Michelle Cavalier and the "garden of La Bastide," Didier Gaglewski also remains closer to the flowers and working the land. Try to trace extraction techniques inherited from the past and plants specific to the region perfumes seduce and make a very personal and authentic. This atypical creator is distinguished by its compositions made in Grasse basin, its choice to favor natural raw materials and the search for sobriety.
Front satisfaction and customer demands wishing to regain the proposed perfumes, shop in Grasse, 12 rue of the Oratory, just steps from the International Perfume Museum to discover the scents and recent creations.
The country house of Aromas
Based in Saint Cézaire on Siagne in the Pays de Grasse, the Bastide aromas manufactures and packages fragrances since 1995.
Saint Cézaire on Siagne is a typical Provencal village a few kilometers from Grasse, the world capital of perfumery.
The homemade studio human scale can meet all your demands. The 100% handmade is carried out in the workshop without intermediary, under the control of a chemist.
La Bastide des Aromas, respects the traditions of the Grasse region and offers the exclusive fragrances custom made in the workshop on-site, high quality, with particular stress on the fragrance concentration, her outfit and originality.
Io Aircraft - www.ioaircraft.com
Drew Blair
www.linkedin.com/in/drew-b-25485312/
io aircraft, phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air-Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, defense science, missile defense agency, aerospike,
Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
New Iteration - Grey Hawk - Mach 8-10 - 7th / 8th Gen Hypersonic Super Fighter Aircraft, IO Aircraft www.ioaircraft.com
New peek, very little is posted or public. Grey Hawk - Mach 8-10 Hypersonic 7th/8th Gen Super Fighter. This is not a graphics design, but ready to be built this moment. Heavy CFD, Design Work, Systems, etc.
All technologies developed and refined. Can out maneuver an F22 or SU-35 all day long subsonically, and no missile on earth could catch it. Lots of details omitted intentionally, but even internal payload capacity is double the F-22 Raptor. - www.ioaircraft.com/hypersonic.php
Length: 60'
Span: 30'
Engines: 2 U-TBCC (Unified Turbine Based Combined Cycle)
2 360° Thrust Vectoring Center Turbines
Fuel: Kero / Hydrogen
Payload: Up to 4 2,000 LBS JDAM's Internally
Up to 6 2,000 LBS JDAM's Externally
Range: 5,000nm + Aerial Refueling Capable
www.ioaircraft.com/hypersonic.php
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Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
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Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
It is chilly and rainy in Arizona for Super Bowl 48 but BMW turned up the heat with their all-electric i3 and hybrid i8 sports car. To add additional flavor to the recipe New England Patriots’ starting corner Kyle Arrington and wife VaShonda Arrington joined the experience for the energetic weekend festivities.
Kyle spent a few days in both vehicles during his activities, which included stops at the Nike Football Super Bowl Hospitality Gifting Suite at the immaculate Scottsdale Resort & Conference Center, the NFL Experience, family outings and dinner with his spouse. Vashonda’s centerpiece moment was raising funds for the Off the Field Player’s Wives Association’s “14th Annual Super Bowl Fashion Show” held at the upscale Scottsdale Fashion Mall. The wives, kids and a handful of former NFL players walked the runway with grace and style. Guests included Holly Robinson Peete, Antonio Cromardie, Steve Young, Kevin Hart and many more. She enjoyed the earthly interior of the i3 and spoke passionately about the need regarding increased sustainability in the world.
The mind is driven by thoughts and fueled by inventive answers. The i3 is 100% pure electric and the i8 is a plug-in hybrid sports car, which means its power is sourced from both gasoline and electricity. The i8 is comprised of a Life module and a Drive module. The 3-liter gasoline motor is placed in the rear and the smaller electric engine is housed up front. In addition, the i8 is essentially an AWD vehicle channeling traction from both axles simultaneously but doesn’t utilize the company’s hallmark xDrive system. A few common i8 performance specs include:
•0 to 60 mph = 4.2 seconds
•Top speed = 155 mph (electronically limited)
•Electric only top speed = 75 mph
•Pure electric range = 22 miles
Born electric, the i3 is engineered with BMW’s LifeDrive architecture, which is also structured into two categories, the Life Module and the Drive Module. Comprised of high-strength carbon, the Life Module protects and provides comfort for the driver and passengers. The second platform, the Drive Module, encompasses the electric drive system, the suspension and the HVAC. Since the car is lighter, the liquid-cooled lithium-ion battery (developed in-house by BMW) is smaller and only needs three hours for a full stage-2 (240-volt) charge. Additionally, BMW attempts to use as much renewable energy as possible for the manufacturing process of the carbon fiber i3.
The journey continues towards educating the world on the benefits of going green. BMW is both an innovator and leader in this technology category and has already spearheaded a positive movement. Expect more BMW i products down the line since they have only just begun.
It is chilly and rainy in Arizona for Super Bowl 48 but BMW turned up the heat with their all-electric i3 and hybrid i8 sports car. To add additional flavor to the recipe New England Patriots’ starting corner Kyle Arrington and wife VaShonda Arrington joined the experience for the energetic weekend festivities.
Kyle spent a few days in both vehicles during his activities, which included stops at the Nike Football Super Bowl Hospitality Gifting Suite at the immaculate Scottsdale Resort & Conference Center, the NFL Experience, family outings and dinner with his spouse. Vashonda’s centerpiece moment was raising funds for the Off the Field Player’s Wives Association’s “14th Annual Super Bowl Fashion Show” held at the upscale Scottsdale Fashion Mall. The wives, kids and a handful of former NFL players walked the runway with grace and style. Guests included Holly Robinson Peete, Antonio Cromardie, Steve Young, Kevin Hart and many more. She enjoyed the earthly interior of the i3 and spoke passionately about the need regarding increased sustainability in the world.
The mind is driven by thoughts and fueled by inventive answers. The i3 is 100% pure electric and the i8 is a plug-in hybrid sports car, which means its power is sourced from both gasoline and electricity. The i8 is comprised of a Life module and a Drive module. The 3-liter gasoline motor is placed in the rear and the smaller electric engine is housed up front. In addition, the i8 is essentially an AWD vehicle channeling traction from both axles simultaneously but doesn’t utilize the company’s hallmark xDrive system. A few common i8 performance specs include:
•0 to 60 mph = 4.2 seconds
•Top speed = 155 mph (electronically limited)
•Electric only top speed = 75 mph
•Pure electric range = 22 miles
Born electric, the i3 is engineered with BMW’s LifeDrive architecture, which is also structured into two categories, the Life Module and the Drive Module. Comprised of high-strength carbon, the Life Module protects and provides comfort for the driver and passengers. The second platform, the Drive Module, encompasses the electric drive system, the suspension and the HVAC. Since the car is lighter, the liquid-cooled lithium-ion battery (developed in-house by BMW) is smaller and only needs three hours for a full stage-2 (240-volt) charge. Additionally, BMW attempts to use as much renewable energy as possible for the manufacturing process of the carbon fiber i3.
The journey continues towards educating the world on the benefits of going green. BMW is both an innovator and leader in this technology category and has already spearheaded a positive movement. Expect more BMW i products down the line since they have only just begun.
BlueEdge - Mach 8-10 Hypersonic Commercial Aircraft, 220 Passenger Hypersonic Commercial Plane - Iteration 3
Seating: 220 | Crew 2+4
Length: 195ft | Span: 93ft
Engines: 4 U-TBCC (Unified Turbine Based Combined Cycle) +1 Aerospike for sustained 2G acceleration to Mach 10.
Fuel: H2 (Compressed Hydrogen)
Cruising Altitude: 100,000-125,000ft
Airframe: 75% Proprietary Composites
Operating Costs, Similar to a 737. $7,000-$15,000hr, including averaged maintenence costs
Iteration 3 (Full release of IT3, Monday January 14, 2019)
IO Aircraft www.ioaircraft.com
Drew Blair www.linkedin.com/in/drew-b-25485312/
-----------------------------
hypersonic plane, hypersonic aircraft, hypersonic commercial plane, hypersonic commercial aircraft, hypersonic airline, tbcc, glide breaker, fighter plane, hyperonic fighter, boeing phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, defense science, missile defense agency, aerospike, hydrogen, hydrogen storage, hydrogen fueled, hydrogen aircraft, virgin airlines, united airlines, sas, finnair ,emirates airlines, ANA, JAL, airlines, military, physics, airline, british airways, air france
-----------------------------
Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
-------------
Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
In 1871, during a time when the United States depended solely on Europe for optical lenses, Thomas A. Willson & Co. erected the first factory for the manufacturing of optical glass for lenses and reading glasses at the corner of Washington and 2nd Streets in Reading, Pennsylvania. Founded by Gile J. Willson and his son Dr. Thomas A. Willson, the company made innovative strides in addressing the occupational hazards faced by so many working in factories throughout the industrial revolution and is credited with launching the safety protection industry. Their first innovation, among many that would follow, was a protective lens that blocked dangerous and blinding rays produced by metal processing equipment.
During the 1890s the company expanded the reach of the safety industry to address not only vision, but also hearing, respiratory and head protection. Dr. Frederick Willson, the son of Dr. Thomas A. Willson, had joined the family company and became the president under a new name, T.A. Willson Co. Inc. as the company incorporated in 1910.
The National Safety Council was created in 1913, and T.A. Willson & Co. Inc. helped to set the bar for the establishment of uniform safety standards in industry. Through the 1920s, they continued expanding their line of safety equipment for the protection of coal miners, military personnel, and the evolving field of aviation. In 1929 the company changed its name to Willson Goggles, Inc., with Thomas A. Willson Jr. as the company’s president, and by World War II, Willson Goggles was helping the war effort by making aviator goggles and high altitude oxygen masks for pilots in the military.
In 1936 the company again changed its name to reflect the ever-expanding range of safety protection equipment they had come to represent. The new name, which would take the company through the next forty-five years, was Willson Products, Inc. They went on to produce fashionable sunglasses, as modeled by the contestants of the 1938 Miss America Pageant, and swim goggles, as worn by Florence Chadwick, the first woman to swim both directions of the English Channel in 1950.
Eventually the company changed hands first to Ray-O-Vac Corp. in 1956, and the following year to Electric Storage Battery (ESB) Co., but maintained the Willson Products name through the atomic age and space age, still leading the safety industry in research and development of equipment to meet the needs of a technologically advancing society. By 1981 the company was manufacturing more than 3,000 separate items in protective gear, and at that time became Willson Safety Products.
Willson shifted its focus to the development of new varieties of respirators, gloves and other protective equipment in the 1980s. They stopped manufacturing safety eyewear and began to purchase those products offshore. The company teamed up with Christian Dalloz, a French-based company to create protective eyewear, and Willson became Dalloz’s largest customer. Dalloz bought Willson Products in 1989, and changed the company name to Dalloz Safety in 1997.
Between 200 and 300 people were employed at the Dalloz plant in Reading, but due to outdated equipment and manufacturing processes, layoffs began. By 2001 fifty employees remained, and in May, 2002 the Dalloz Safety plant in Reading closed.
A 130-year history of safety industry innovation and leadership came to an end, and the future of the buildings that had been erected to accommodate the Willson family’s enterprising manufacturing was uncertain. In the midst of hopes and plans for the revitalization of the greater Reading area, the City of Reading recognized the value and the character of these buildings, and their potential to serve the community in a whole new way. Plans to develop a community arts and cultural resource center began, fueled by the proven success of similar adaptive reuse arts center projects. By converting abandoned factories, these community arts centers have revitalized their areas, maintaining local historical and architectural integrity while inspiring a cultural and economic resurgence as the community and visitors come together to create, appreciate, and celebrate the arts.
Discovery STO - Single Stage to Orbit Heavy Lift, Hypersonic Aircraft - 70 TON Payload - IO Aircraft
IO Aircraft: www.ioaircraft.com
Discovery STO Specs
Length:197' 6" / Span: 93' / Palyload Bay: 61' L X 15" W X 15' H / Span: 70 Ton (140,000 LBS)
Engines: U-TBCC (Unified Turbined Based Combined Cycle) Inc/Zero Atmosphere
Inlets: Adaptive REST, Originally Hapb/Larc NASA
Fuel: 125,000 Gallons 12,000 PSI H2 / 90,000 Gallons 12,000 PSI O2
Fuel Weight: Apx 72,000 LBS Total / *If liquid, would be 1.4 Million LBS
Weight: Apx 325,000 LBS EOW/Dry Weight / Apx 537,000 T/O Weight, Max Payload
Airframe: 75+% Proprietary Advanced Composites, 400,000 PSI Tensile Strength Airframe / *NO Ceramic Tiles
Thermals: 6,000F Thermal Resistance
Estimated Cost: $750 Million Each (Fly Away Price)
Estimated Launch Cost: Apx $28 Million at 140,000 LBS, Including Maintenance Costs / Under $250 per pound at Maximum Paylaod Wieght *Could Drop to Below $50 per LBS
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single stage to orbit, sto, space plane, falcon heavy, delta iv, hypersonic commercial aircraft, hypersonic commercial plane, hypersonic aircraft, hypersonic plane, ICAO, International Civil Aviation Orginization, hypersonic airline, tbcc, glide breaker, fighter plane, hyperonic fighter, boeing phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, defense science, missile defense agency, aerospike, hydrogen fueled, hydrogen aircraft, virgin airlines, united airlines, sas, finnair ,emirates airlines, ANA, JAL, airlines, military, physics, airline, british airways, air france, aerion supersonic, aerion, spike aerospace, boom supersonic,
-----------------------------
Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
-------------
Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
ABERDEEN PROVING GROUND, Md. (Dec. 19, 2014) -- The U.S. Army is seeking to implement a new mortar manufacturing process to provide improved weapons at a lower cost, officials said.
The Army introduced a nickel super-alloy called Inconcel to produce mortars in 2008, but its properties make it challenging to manufacture. Researchers have been working on an alternative method to overcome the difficulties, said Chris Humiston, a mechanical engineer with the Armament Research, Development and Engineering Center at Watervliet Arsenal, New York.
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