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www.pharmapackagingcn.com/products/infusion-rubber-stopper/
Infusion Stoppers are designed for infusion bottles and provide optimal protection and drug delivery. Our range of pharmaceutical rubber Infusion Stoppers is specifically designed to meet multi-piercing needs and facilitate manufacturing processes.
Details of Infusion Rubber Stopper
Product SpecificationDrawing NoCrown FeaturesCrown Diameter mmCrown Thickness mmPlug Diameter mmTotal Height mm
22-B21501Pit radiation22.33.814.27.8
28-C1512Pit single hole single circle273.81811.8
32-A111603Four hole three segment arc radiation30.9423.612.2
32-A31614Four hole three segment arc radiation30.8524.216
The sewers require continuous maintenance. Cooking fat needs to be regularly removed, and recycled paper products tend not to break down so quickly - perhaps because the shorter, more damaged fibres need to be more strongly bonded in the re-manufacturing process.
I used auto colour balance, and long exposures of several seconds but the fluorescence - under the UV fluorescent lighting - from waste detergent water - seems real.
See also the related Brighton Sewer Tour Gallery.
External links:
Sewer tour photo gallery [Southern Water]
Brighton's magnificent sewers [Southern Water tour details]
A little history of Brighton's magnificent sewers [Southern Water]
Graham Harwood (UK), Matsuko Yokokoji (JP).
A coal-fired boiler powers a network of computers exploring the relationships between power and media. Coal Fired Computers explores the ecologies that have created and maintained power, and the subsequent health residues and crisis of fuelling that power. The work responds to the displacement of coal production to distant India, China or Vietnam and our industrial heritage, in particular the work of Charles Parsons whose steam turbine is used to produce 40% of today’s electricity. In many countries this rate is much higher (more than 70% in India and China).
According to the World Health Organization, 318.000 deaths occur annually from chronic bronchitis and emphysema caused by exposure to coal dust. The common perception is that wealthy countries have put this all behind them, displacing coal dust into the lungs of unrecorded, unknown miners in distant lands, coal returning in our lives in the form of cheap and apparently clean goods we consume.
Coal fired energy not only powers our computers here in Europe, but is integral to the production of the 300.000.000 computers made each year. 81% of the energy used in a computer’s life cycle is expended in the manufacturing process, now taking place in countries with high levels of coal consumption.
Proces produkcji chmur.
Cloud manufacturing process.
Quenching tower of modern no. 1 coke oven battery.
Wieża gaszenia koksu baterii nr 1 - bis.
The Lion Chambers is a building in the city centre of Glasgow, Scotland which began construction in 1904 and was completed in 1907. It was designated as a Category A listed building in 1966. It still stands today despite it recently being abandoned due to structural weakness. The building features stonework on the exterior showing a lion's head referencing the name, as well as the upper bodies of some Judges of the court, since the building was intended to comprise mainly lawyers' offices. It was made using a somewhat experimental method of construction called the Hennebique System which involves a reinforced concrete as its main material; the technique has fallen out of favour in modern times. Whether or not the building will be demolished or receive funding to be refurbished remains to be seen.
History
The Lion Chambers was originally designed by James Salmon and John Gaff Gillespie, who together formed the partnership known as Salmon, Son & Gillespie. The two were commissioned by William George Black, a lawyer and writer based in Glasgow who was well-established within the Glasgow Art Club, which included some well-known artists such as James Abbott McNeill Whistler. Because of this he integrated into his plans artists' studios that would be located in the top floors. The Glasgow Corporation was known to have somewhat of a soft spot for the innovative club of which Black was a member, and it is thought this may have helped to get the Lion Chambers approved for construction.
The building was home to many lawyers and artists for most of the 20th century, until the majority had to be evacuated in 1995 due to the decision that it was too dangerous to regularly use. The ground floor and basement were still used up until 2009 when it was decided that they too should be evacuated. The building remains there to this day with no clear indication of its future – the sum needed to restore it back to safe condition is far too great for the multiple co-owners to afford, and no one else has showed enough interest to invest in it. The building has been threatened for demolition since 1991 when the co-owners were served with a "Dangerous Building Notice", but the threats fell through because the building is Category A listed. In April 1991, water-pooling, cracking and spalling affected the building due to its structural decay. The co-owners decide to pursue demolition, since the repairs were estimated at £1–1.5 million. Four years later, The Scotsman reported that due to the danger of collapsing, all the occupants had been evacuated. Building Control assessed the building. On 12 April 1995, The Independent reported that the owners of Lion Chambers has been served with a Dangerous Building Notice, after which they submitted a demolition application. A month later, The Herald reported that for only 20 more years life of the building, the repairs would cost around £1.5 million. A report by the Glasgow Building Preservation Trust was submitted to Glasgow City Council, proposing a longer-term but more expensive approach to repairs. On 29 August 1995 the permission to demolish was refused, giving the owners six more months to deal with the Dangerous Building Notice. Glasgow Building Preservation Trust entered discussions about undertaking repairs, and also requested for notice of other parties wishing to take on the building. In October 1997, Glasgow Building Preservation Trust reported that they wanted to develop a centre for young designers, including workshop and training spaces, called the Centre for Product Resource Innovation and Design Enterprise (PRIDE). In 1999, £5,000 was granted for a feasibility study, as reported by The Annual Report of the Architectural Heritage Fund, stating that re-using as dwellings and workshop space would be viable. Historic Scotland and Glasgow City Council agreed that more research would be required into the building's mode of construction.
Architecture
Despite many common Glaswegian features such as typical corner turrets, careful modelling of the external walls and a pair of steep gables on the roof, the building was built using the Hennebique system by French Engineer, François Hennebique. This system involves mainly reinforced concrete offering an alternative to steel frames, making the building fireproof. The Hennebique system was designed to strengthen concrete to make it withstand forces which damage concrete the most and consists of using situ concrete (situ meaning 'cast in its place'). This allows the walls to be extremely thin – with a thickness of 100 millimetres (4 inches) – to maximise the amount of space within the rooms and avoid the need to have exterior scaffolding. The Hennebique system was first used in 1894 in Wiggen, Switzerland[8] and the Lion Chambers was the second building in Scotland to adopt this system and one of the first buildings in the UK.
However, the Hennebique system is not as popular in the UK as in the 1900s because of its many negative attributes, including the complexity of the framework and moulding in the manufacturing process. The architecture of the building allows the concrete to weather away easily, considerably in weather in the United Kingdom, which was one of the main reasons the Lion Chambers had to be abandoned. Additionally, the building doesn't provide the heat qualities required to meet today's standards.
Damages
Original design presented to the William George Black showed many weak points, including the lack of Thermal Insulation of the external walls and roof surfaces, causing condensation on the internal surfaces. Additionally, there was no external insulation against water penetration on the basement walls. This caused water to be able to penetrate the basement walls, which eventually led to the evacuation of the basement in 2009. In 2009, a feasibility study for the reparation of the Lion Chambers was instructed by Historic Scotland. The study advised there to be additional reparations to the building as further corrosion occurred due to the lack of activity in the building and the Glasgow City Council provided £156,000 to replace materials used in the building with wire mesh due to concerns over debris falling from the building.[4] Furthermore, around 25% of the windows have been boarded over due to safety reasons and the northern and eastern walls have been vandalised at ground level.
Future of the Lion Chambers
After the departure of the last tenant, Douglas, the owner of a supplies shop that occupied the ground floor, the 12,628-square-foot (1,173.2-square-metre) building now lies vacant. It is currently valued and being sold at £113,000. Although the building has a relatively low value, the restoration of the building would cost more than £1.3m, which has led the owners of the building struggling to find a bidder. There have been other attempts by agencies to restore the Lion Chamber, such as Four Acres Charitable Trust and the Glasgow City Council, however, all attempts are yet to be successful. Despite the pursuit of finding a solution to Lion Chambers, Historic Scotland and Glasgow City Council are committed to finding a solution to save the building. However, in 2000 on 26 October the Scotsman reported that Glasgow City Council had approved funding of £156,000 to be used to replace current scaffolding with a wire mesh, allowing for a further two years in which for them to create a funding package. Also in 2001 the Annual Report of the Historic Buildings Council for Scotland reported that £22,958 had been awarded to aid costs with scaffolding. In 2002 the Annual Report of GBPT reported that the idea to raise wire mesh was still in talks and that if completed would mean that the Dangerous Buildings notice would be removed from the site. Due to two buses colliding with the scaffolding, the scaffolding had to be rebuilt around the site. In 2004 the scaffolding began to be taken down, leaving the wire mesh still up. It was also reported by local planners that the building was available but not for leasing. In 2006 the GBPT back out of any arrangements with the building. By 2007 the lower floor of the building was only being used as an office supplies shop. Despite that windows were still boarded over and many of the walls had been vandalised with graffiti. In 2010 the last business unit located within the building moves out, leaving the building empty, this is supposedly because of the poor condition of the building. It is reported that Glasgow City Council offered the building to multiple owners for restoration at the price of only £1, however no successful deal were made. Glasgow City Council and Historic Scotland are still strongly committed to finding a solution to save the building.
[Information: Wikipedia]t
Introducing the Champlain Octagon Shaped On Ground Pools. This NEW product is exclusively offered by Propools! A semi-inground pool is perfect for yards which slope because the pool can be installed partially in the ground and partially out. It can be decked with redwood or pressure treated wood and complimented with either a concrete deck or pavers. Depths ranges available are from 40" to an 8' Deep End.
This pool wall, equipment and materials are like that of an inground pool but competitively priced like a higher end above ground pool. Features a 17-gauge no-weld wall, 9 bolt panel fastening system, Stake-Loktm Rivet-less/Weldless manufacturing process, Z-700 (G-235) galvanized coated panels and supports. Lifetime Transferable warranty.
Read More About: On Ground Pools
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".
To improve hold feeling and to add some visual spice, I have made a simple grip for my XZ-1 with ebony. The braided leather strap is also hand made by myself.
If somebody is interested in manufacturing process of this small wooden staff, please visit my blog at arkrico.blog.fc2.com/
W.A.S Benson Lamps and hollow ware
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.
INB2202-220x200cm-1000g-C-AAA
Mulberry Silk filled comforters, Queen size silk comforter with 300TC cotton cover. Comforter with loops that coordinate with a large selection inboo duvet covers.
The hand-stretched silk fibers is AAA Mulberry Silk,Oeko-Tex rating. Natural silk has anti-allergic, anti-mite,anti-bacterial, skin-friendly and the silk fleece sheds surplus heat by wicking away moisture from your body - keeping you cool and comfortable. the use of natural silk duvet can really do improve human health. Further more by being combined with a silk fleece blanket on the top, the silk comforter will be very flexible to adjust the temperature.
Features:
Significant benefits of silk comforters:
Silk is a natural insulator:Depending on the temperature, silk duvets either draw heat away from the body, or traps in the warmth. In the winter, the large fibres in silk duvets, reduce heat loss from the body, but in summer, the silk fleece sheds surplus heat by wicking away moisture from your body - keeping you cool and comfortable.
This also means that one silk duvet/quilt will satisfy two sleepers with different warmth needs.
Silk is naturally hypoallergenic: Silk duvets/quilts are resistant to dust and house mites, mildew, mould, and rot that attacks other fibres. Sufferers of asthma, blocked sinuses or other hay fever symptoms, can find relief in silk duvet bedding, as well as those with allergies to down or other synthetic material.
Silk is composed of 18 amino acids: The same amino acids that are found in our own bodies. Medical studies have show that this can help blood circulation and your digestion system during sleep. It also helps to reduce the discomfort of itchy skin and aids in preventing vascular sclerosis.
Silk duvets are also suited to children: Their lightweight nature and breathable qualities ensure a regulated, even, sleep temperature with no added chemicals for a healthier sleeping environment.
Silk duvets provide the same warmth as down duvets. They are comfortable all year round due to their insulating properties.
Specification:
1. The Silk comforters Silk duvets Silk blanket cover options:
100% cotton cover: (conventional)
233TC twill, 300TC,400TC Sateen and Jacquard cotton,
100% silk cover: (Luxury)
8mm, 15mm100% silk habotai, 16mm, 19mm, 23mm 100% silk/cotton Jacquard, 15mm silk, 16mm Pure silk Charmeuse.
Eco friendly Recyclable fiber fabrics: (low cost solution)
bamboo fiber Viscose, 100% Tancel,
Polyester fabrics: (lowest cost solution)
Polyester pongee
2. Filling material: 100% mulberry silk / 100% tussash silk or mixed depends on customers' requirement.
3. Filling Weight
Available in lightweight (summer), medium (all season) Summer and winter.
Summer-weight silk duvet (250gsm) is perfect for warm summer nights. ( equivalent of a 4 tog)
All Year round (winter)-weight (400gsm ) is ideal all year round for most people in a centrally heated environment.
Medium to winter duvet (aprrox 550-600gsm) is ideal for cold winter ( equivalent of a 9 tog)
Combining either two summer weights or a summer and winter silk duvet will allow maximum use of the quilts when you need more or less warmth.
Conventional size:
150x210cm, 180x210cm, 200x230cm, 220x240cm
Full sizes available:
1.2m single bed:
150x180cm
150x200cm
150x210cm
160x210cm
1.5m twin bed:
180x210cm
180x220cm
180x230cm
200x230cm
1.8m Queen bed:
220x240cm
Child bed:
100x150cm
USA size:
Baby 30" x 36"
Twin 68" x 86"
Full 78" x 86"
Queen 90" x 86"
King 104" x 94"
Cal king 108" x 98"
4. Manufacturing process:
The long-fiber mulberry silk is hand stretched and then hundred layered in a grid pattern until the desired tog rating and weight is achieved. Then the silk is hand stitched or box stitched, hand tacked. Hand Tufted on the the duvet case(shell) to prevent the silk filling moving.
5. Machine box stitch quilting pattern selection
diamond stitch(30x30cm or custom),
Ring stitch
Light weight box stitched silk duvet is ideal as a Summer quilt, bedspread, coverlet and throw.
Easy for machine wash.
6. Silk Quilt Edges Trimming options and decorative designs:
Piping edge with different color, matchingh or contrast
decorative logo by scalding hot drilling plans
5cm -10cm 100% pure charmeuse silk border binding, matchingh or contrast
5cm -10cm polyster satin silk border binding, matchingh or contrast
7. Inspecting opening & loops:
Depending on requirment recommend using a duvet (comforter) cover to protect and prolong the use of this beautiful silk comforter.
8. Cover Color: white, light pink, custom.
9. Packing : each with a plastic bag, match with exterior retail pacing: non-woven bag, cotton bag, gift packing
10. Washing:
Machine-washable, dry wash, hand wash
11. Minimun order quantity: 100pcs per color
12.Inquiry Number: INB2201-220x200 cm-1000g-C-Subsidiary details A
Nomenclature:
INB2201-150x210cm-700g-C-Subsidiary details
INB: INBOO products
-2201: product code for Mulberry Silk filled comforters, Silk duvets
-150x210cm: Silk duvets Size
-700g: filling weight
-C : Cotton cover
-S : Silk cover
-- Subsidiary details: For more details
Application:
Bedroom health sleeping
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.
AS17-162-24063 (7-19 Dec. 1972) --- A close-up view of the equipment used for the Heat Flow and Convection Experiment, an engineering and operational test and demonstration carried out aboard the Apollo 17 command module during the final lunar landing mission in NASA's Apollo program. Three test cells were used in the demonstration for measuring and observing fluid flow behavior in the absence of gravity in space flight. Data obtained from such demonstrations will be valuable in the design of future science experiments and for manufacturing processes in space.
Nao Victoria replica at the Ice Factory
On the top floor of the old Ice Factory, now the Doñana Visitor Center, there is a scale replica of the Nao Victoria, one of the five ships that set off in search of the spice route from the port of Sanlúcar de Barrameda on September 20, 1519, being the only one that returned to the same port of Sanlúcar, on September 6, 1522, thus completing the First Circumnavegation of the World three years after his departure.
The link between Sanlúcar, Seville, Portugal and the Basque Country is latent in the representation of the Nao Victoria, since its name comes from the church of Santa María de la Victoria in Triana, where Magellan, captain of the expedition, swore to serve the King Carlos I. In addition, the Guadalquivir river would make Sanlúcar the protagonist in this feat, as it is the umbilical cord between this port and that of Seville, with Sanlúcar having a fundamental role in the Journey, since it is here where the expedition of spices was born and ended .
Likewise, tradition tells that the ship was built in the shipyards of Zarauz, in the Basque Country, being the Basque Country the place of origin of Juan Sebastián Elcano, who would be the commander who finished the expedition when Magellan died in April 1521, in the island of Mactan, just before reaching the Moluccas islands, where the long-awaited spices were found.
As for this replica of the Nao Victoria, it is a 1:8 scale model of the original. On the exhibition base, barrels, pipes, bales, and boxes are represented in which the supplies and provisions, water, food and other elements for the journey were carried.
Without a doubt, the Doñana Visitor Center, the Ice Factory, is a place of interest to learn about the History and Culture that surrounds the surroundings of Doñana and the Guadalquivir river.
The Ice Factory is a modernist style building built in 1944, under the name of Marqués de Valterra. It is located on Avenida Bajo de Guía in Sanlúcar
This supplied ice to the fishing boats in Sanlúcar and remained in operation in its original role until 1978, after having overcome a serious explosion caused by the gases used in the manufacturing process. It is decorated with tiles from Triana (Seville).
In the year 2000 it was converted into the Visitor Center of the Doñana National Park
en.wikipedia.org/wiki/Sanl%C3%BAcar_de_Barrameda#:~:text=...
Blue Edge -Mach 8-10 Hypersonic Commercial Aircraft, It-1, 202 Passenger
Seating: 202 | Crew 2+4 (250 if denser seating)
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 1
IO Aircraft www.ioaircraft.com
Drew Blair www.linkedin.com/in/drew-b-25485312/
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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
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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.
-------------
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
-----------------------------
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.
The Horrockses Cotton Fairies take you on a tour of the cotton manufacturing processes at three of their Preston Mills - Yard Works, Centenary / New Preston and Fishwick.
This was Horrockses - Crewdson's contribution to the 1920 trade publication Concerning Cotton - A brief account of the aims and achievements of the Amalgamated Cotton Mills Trust Limited and it's component companies.
TO ENLARGE - either:
1. Right-click the image then choose Original or...
2. Select View all sizes from the Actions tab then choose Original
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.
American Airlines (US Airways)
Serial Number 1281
MFR Year 2000
Engine Model IAE V2500
Former America West Airlines
11-02-2001
Engine failure and evacuation, Airbus A319, November 2, 2001
Departure: George Bush Intercontinental Airport, Houston, Texas, USA
Destination: Phoenix Sky Harbor International Airport, Phoenix, Arizona, USA
Airplane Type(s): Airbus A319-132
Flight Phase: Cruise
Registration(s): N814AW
Operator(s): America West Airlines
NTSB short summary:
the #1 engine's fatigue failure of the #3 bearing due to the manufacturer's inadequate design of the high-pressure compressor stubshaft coating, which resulted in a loss of engine power and an emergency landing.
NTSB synopsis:
The transport airplane was in cruise flight at flight level 390 for 12 minutes when they received an "engine oil filter bypass" fault message on the engine centralized aircraft monitoring (ECAM) system; however, all of the engine parameters remained within limits. Subsequently, the oil pressure indication for the #1 (left) engine rose into the red band and a "high vibration and a thumping sound" was felt and heard. The flight crew then declared an emergency and diverted to another airport. The captain reported that during the landing roll, he moved both throttle levers into reverse, and simultaneously the cockpit and cabin began to fill with smoke. Air traffic controllers reported they observed white smoke emanating from the #1 engine during the landing roll. The captain stopped the airplane on the high-speed taxiway, turned off both engines, and an emergency evacuation ensued. The 1L and 2L doors were operated normally; however, the 1R door jammed when the flight attendant attempted to open it. Examination of the 1R door actuator and slide did not reveal the reason it failed to operate. Examination of the engine revealed that debris contamination of the #3 bearing initiated spallation of the bearing's outer ring raceway. Cyclic loading from the bearing balls passing over the growing raceway spall resulted in extensive fretting of the outer diameter surface of the outer ring, from which a fatigue crack was initiated. High-cycle fatigue progression radially through the outer ring was followed by rapid fracture and subsequent liberation of the outer ring fragments. The debris contamination more than likely came from the high-pressure compressor (HPC) stubshaft coating, which was liberated and entered the #3 bearing area causing it to fracture, and the engine to lose power. Research revealed this was one of five similar occurrences, which was traced down to a change in the manufacture process for the HPC stubshaft coating. The manufacturer has taken actions to alert operators of the existing problem.
NTSB factual narrative text:
HISTORY OF FLIGHT
On November 2, 2001, at 0734 central standard time, an Airbus Industrie A319-132 transport airplane, N814AW, operating as America West Airlines flight 786, experienced an engine anomaly while in cruise flight and diverted to the Midland International Airport (MAF), Midland, Texas. The captain, who held an airline transport pilot certificate, the first officer, who also held an airline transport pilot certificate, three cabin attendants, and 84 passengers were not injured. The airplane was registered to International Lease Finance Corporation of Los Angeles, California, and operated by America West Airlines of Phoenix, Arizona. Visual meteorological conditions prevailed, and an instrument flight rules (IFR) flight plan was filed for the 14 Code of Federal Regulations Part 121 scheduled passenger flight. The flight originated from the George Bush Intercontinental Airport (IAH), Houston, Texas, at 0610, and was destined for the Phoenix Sky Harbor International Airport (PHX), Phoenix.
Minton Tiles
The richly patterned and colored Minton tile floors are one of the most striking features of the extensions of the United States Capitol. They were first installed in 1856, when Thomas U. Walter was engaged in the design and construction of vast additions to the Capitol (1851-1865). For the floors in his extensions, Walter chose encaustic tile for its beauty, durability and sophistication.
•Artist: Minton, Hollins and Company
•Date: Installed in 1856
One striking example of the contrast between the interiors of the Old Capitol (finished in 1826) and the extensions (begun in 1851) may be seen in the differences in flooring materials. In the Old Capitol, stone pavers were used in corridors and other public spaces, such as the Rotunda and Crypt, while brick was used to floor committee rooms and offices. These materials, although durable and fireproof, would have looked plain and old-fashioned to the Victorian eye. In the mid-19th century, encaustic tile flooring was considered the most suitable and beautiful material for high-traffic areas. Unlike ordinary glazed tile, the pattern in encaustic tile is made of colored clays inlaid or imbedded in the clay ground. Because the color is part of the fabric of the encaustic tile, it will retain its beauty after years of wear. One observer noted:
“The indestructibility of tiles may be judged from the fact that the excavations at Pompeii have unearthed apartments where painted tiles are just as beautiful, the colors as fresh and bright as... when the fated city was in all its glory.”
Two types of tile were used at the U.S. Capitol: plain and inlaid encaustic tiles in a range of colors. Plain tiles were used as borders for the elaborate inlaid designs or to pave large corridor areas. They were available in seven colors: buff, red, black, drab, chocolate, light blue and white. Additional colors, such as cobalt blue, blue-gray, and light and dark green, appear in the inlaid encaustic tiles that form the elaborate centerpieces and architectural borders. They were made by “filling indentations in the unburnt tile with the desired colors and burning the whole together.”
The patterns and designs formed in the inlaid tiles were limited only by taste and imagination. They include geometric patterns such as the Greek key, guilloche, and basket weave; floral designs such as the fleur-de-lis; and figures such as dolphins and classical heads. Few of the patterns are repeated. Although most of the tiles are six-by-six-inch squares, some are round, triangular or pie-shaped. Approximately 1,000 different tile patterns are used in the corridors of the Capitol alone, and up to 100 different tiles may be needed to create a single design.
The original encaustic tiles in the Capitol extensions were manufactured at Stoke-upon-Trent in Staffordshire, England, by Minton, Hollins and Company. The firm’s patented tiles had won numerous gold medals at international exhibitions and were considered the best tiles made. In 1876, having seen Minton’s large display at the Centennial Exhibition in Philadelphia, one critic wrote, “Messr. Minton shone superior to all exhibits of the sort… and may be cited as showing the highest results in tile-pottery achieved by modern skill and research.”
Beginning in 1856, and continuing for five years, the tile was installed by the import firm of Miller and Coates of New York City. For the journey from New York to Washington, the tiles were packed in wooden casks weighing about 1100 pounds; each cask contained enough tiles to pave about 100 square feet. The cost of the tile ranged from $0.68 to $2.03 per square foot.
Thomas U. Walter had every reason to believe that the encaustic tile floors would last as long as his extensions stood. One visitor noted in 1859 that the tile floors vied with the beauty of marble and surpassed it in durability. While perhaps valid for other installations, however, this prediction proved overly optimistic for the Capitol Building. By 1924, the Minton tile was removed from the corridors in the first and second floors of the House Wing and replaced by “marble tile in patterns of a simple order.” In that day, marble was selected for its superior durability and because suitable replacement tile was difficult to find.
In the 1970s, however, a similar condition prompted a very different response. In 1972, a search was undertaken to determine a source of similar tiles in order to restore the original appearance of the building. Inquiries were made of all major American tile manufacturers, the American Ceramic Tile Manufacturers Association, and even Mexican and Spanish tile suppliers. Although the colors and designs could be reproduced relatively easily, the patterns would quickly wear because they would be applied to the surface. The “inlaid” feature of the encaustic tiles, i.e., the approximately 1/8-inch thickness of the pattern and color, is the characteristic that enables the Minton tiles to be walked upon for over 100 years without signs of wear. It was this technique that formed the basic difficulty of manufacture.
Finally, as a result of the Capitol’s needs becoming generally known, the Architect of the Capitol was placed in contact with H & R Johnson Tiles Ltd., located at Stoke-on-Trent, England. It was discovered that that firm was a successor company to the Minton Tile Co. and had even retained many of the original hand tools and forms in a private museum at the company’s manufacturing site.
Contact was then made with Mr. James Ellis, the Directing Architect of Ancient Monuments and Historic Buildings for the Crown. He had been trying for many years to establish a program for the replacement of the worn Minton tiles at the Houses of Parliament but had more or less given up the attempt because of H & R Johnson’s continued unwillingness to revive the encaustic tile process. However, the restoration work at the Arts and Industries Building of the Smithsonian Institution was in process at about the time the needs of the Capitol became known; it thus appeared that a market for such tiles was developing to the degree that the manufacturer began to reconsider its prior position. The company thus began the experiments that finally led to the present availability, after many decades, of the original Minton-type tiles.
Because the tiles in the Capitol are more decorative and have more complicated designs and color combinations than those in either the Houses of Parliament or the Smithsonian, those institutions were able to obtain replacement tiles sooner than the Capitol. The lessons learned in the manufacture of the simpler tiles served as a basis for filling the later needs.
Color photographs and full-sized drawings of the many required patterns were made and recorded, and many developmental submissions were made as the hand-made manufacturing process was re-developed. Finally, in 1986, the first acceptable tiles were delivered. The installation process was accomplished with modern cement adhesives and has yielded excellent results.
The program enabled the original tiles to be replaced with exact replicas. This project began on the first floor of the Senate wing, where the effects of 130 years of wear and tear were most noticeable. Replacement tile was closely scrutinized to ensure fidelity to the nineteenth-century originals. While difficult and slow, this process is the only fitting response to the history of the Capitol extensions, not only to restore the original beauty and elegance of these unique floors, but also to provide for their continuing attractiveness for the foreseeable future.
Raven Model B Mach 8-10 - Supersonic / Hypersonic Business Jet - Iteration 6
Seating: 22 | Crew 2+1
Length: 100ft | Span: 45ft 8in
Engines: 2 U-TBCC (Unified Turbine Based Combined Cycle)
Fuel: H2 (Compressed Hydrogen)
Cruising Altitude: 100,000-125,000 ft @ Mach 8-10
Air frame: 75% Proprietary Composites
Operating Costs, Similar to the hourly operating costs of a Gulfstream G650 or Bombardier Global Express 7000 Series
IO Aircraft www.ioaircraft.com
Drew Blair www.linkedin.com/in/drew-b-25485312/
-----------------------------
supersonic business jet, hypersonic business jet, hypersonic plane, hypersonic aircraft, hypersonic commercial plane, hypersonic commercial aircraft, hypersonic airline, Aerion, Aerion Supersonic, 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.
Hyperion, Hypersonic Mach 15 Scramjet Missile - IO Aircraft - ARRW, HAWC, Air Launched Rapid Response Weapon
Length: 120" / Span 25"
Scramjet, Hypersonic, ARRW, HAWC, Air Launched Rapid Response Weapon, Scramjet Physics, Scramjet Engineering, Hypersonic Missile, hypersonic weapon, hypersonic fighter, hypersonic fighter plane, tgv, tactical glide vehicle, hypersonic commercial aircraft, hypersonic commercial plane, hypersonic aircraft, hypersonic plane, hypersonic airline, tbcc, glide breaker, fighter plane, phantom works, boeing phantom works, lockheed skunk works, boost glide, tactical glide vehicle, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, defense science, missile defense agency, aerospike, hydrogen aircraft, airlines, military, physics, airline, aerion supersonic, aerion, spike aerospace, boom supersonic, , darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, afosr, socom, arl, army future command, mda, missile defense agenci, dia, defense intelligence agency, Air Force Office of Scientific Research,
Iteration V8, Hyperion Mach 15 #hypersonic #scramjet (50% faster then the X-43 #nasa), 300% faster than #Lockheed, #NorthropGrumman, #Raytheon, and Boeing. Much is sanitized as the technology advances are dramatic and not public.
DOD's funding of #AGM-183A / Air Launched Rapid Response Weapon, the poeple developing it barely comprehend student level capabilities and 50/50 it will disintegrate even at Mach 5. China and Russia, already much faster and higher tech making it obsolete already, India's recent test, apx 700 mph faster.
Summarized details are accurate
#hypersonic #hypersonics #scramjet #hypersonicplane #hypersonicaircraft #skunkworks #spaceplane #boeing #lockheed #raytheon #bae #bombardier #airbus #northopgrumman #generaldynamics #utc #ge #afrl #onr #afosr #ReactionEngines #spacex #virginorbit #usaf #darpa #mda #rollsroyce #nasa #tesla #safran #embraer #AirLaunchedRapidResponseWeapon #additivemanufacturing #military #physics #3dprinting #supersonic #ramjet #tbcc #collinsaerospace #rockwell #phantomworks #hypersonicmissile #alrrw #boeingphantomworks #generalatomics #cessna #dassault #arl #unitedlaunchalliance #spaceshipcompany #navair #diu #dia #usaf #unitedtechnologies #defenseadvancedresearchprojectagency #graphene #additivemanufacturing
-----------------------------
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.
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 Horrockses Cotton Fairies take you on a tour of the cotton manufacturing processes at three of their Preston Mills - Yard Works, Centenary / New Preston and Fishwick.
This was Horrockses - Crewdson's contribution to the 1920 trade publication Concerning Cotton - A brief account of the aims and achievements of the Amalgamated Cotton Mills Trust Limited and it's component companies.
TO ENLARGE - either:
1. Right-click the image then choose Original or...
2. Select View all sizes from the Actions tab then choose Original
Vancouver Majestic Sit and Sleep | Latex Mattresses Vancouver 604-731-8226
Since 1985 Majestic has been helping you sleep well and save space at affordable prices. Twenty five years later and our product lines have grown to include Vancouver's largest selection of Green Living Mattresses, dining sets, solid hardwood bedroom suites and
of course, space saving futons.
Vancouver Family owned and operated since 1985, Majestic Sit & Sleep is committed to our customers and our environment. At Majestic Sit & Sleep we strive to be your leaders in alternative sleep.
Our new line of green living mattresses help to lower the CO2 levels in the air all while getting you the rest you deserve in a healthy, clean sleeping environment.
Small Space? We have the solution! We carry a large selection of futons and sofa beds whether it's for you, the last minute guest or the usual suspects we have something that fits!
Futons: Design it your Way
Step 1 - Choose your favorite design from our wide selection of pine, hardwood or metal frames.
Step 2 - Choose your level of comfort from our luxurious pillowtop futons to our more economical mattresses. Firm or soft, we are your futon specialist!
Step 3 - Finally it's time for that added touch just for you. Choose from a wide variety of fabrics that fit in your home...it's like having a custom made sofa without the BIG price tag.
Quality Assured we offer warranties on all our products and most all of our furniture is manufactured to our specifications!
Nature's Embrace Organic Baby
100% Organic Latex crib mattress
Baby's are precious and require proper nutrion and love to grow up strong and healthy. Generic mattresses use harmful chemicals and cheap materials in the manufacturing process. Nature's Embrace Organic Baby uses only the finest organic materials for your baby to sleep on, to assure your baby is sleeping in the healthiest sleep environment possible.
Made from:
100% Certified Organic Cotton, 100% Certified Organic Natural Dunlop latex.
More Natural Options coming soon!
Vancouver Majestic Sit and Sleep
Located: 1828 West 4th Avenue,
Vancouver BC Canada
Phone: 604-731-8226
email: majesticfuton@telus.net
Vancouver's largest futon and mattress store!
We look forward to seeing you soon!
"Vancouver Majestic Sit and Sleep" "Latex Mattresses Vancouver" "Futons Vancouver" "Green Living Mattresses"
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.
Escultura Splash Expo Zaragoza 2008
La escultura Splash es una escultura de 21 m de altura diseñada por Program Collective y desarrollada mediante fluidos y dinámicas por Pere Gifre para la Exposición Internacional de Zaragoza de 2008; a partir del concepto de diseñadores Program Collective formado por: Mona Kim, Todd Palmer, Olga Subirós y Simon Taylor, para la exposición diseñada por Program Collective “Agua para la vida” en el Edificio Torre del Agua.
El cálculo de las estructuras a cargo del ingeniero José Maria Velasco de AMATRIA y la construcción por PQC bajo la dirección de PROGRAM COLLECTIVE.
Características Técnicas
La escultura estaba formada por 135 piezas distintas que se sujetaban mediante cables a la parte superior del edificio Torre del Agua. Estas piezas fueron diseñadas íntegramente por ordenador por Pere Gifre representado una gota de agua impactando en una superficie.
Proceso de Desarrollo
Mediante la utilización de efectos visuales (efectos especiales) Pere Gifre generó un fluido y mediante procesos de Diseño asistido por computador se adaptaron para su fabricación.
El proceso de fabricación realizado por PQC en sus instalaciones en MADRID combina la Fabricación asistida por computadora con procesos artesanales para generar los volúmenes finales que posteriormente fueron transportados e instalados en la Torre del Agua dentro de la Exposición Internacional de Zaragoza de 2008 SPAIN.
Splash Sculpture Expo Zaragoza 2008
The Splash sculpture is a sculpture of 21 m in height and designed by Collective Program developed by fluid and dynamic by Pere Gifre for Expo Zaragoza 2008; from Program Collective designers concept formed by Mona Kim, Todd Palmer, Simon Taylor and Olga Subirós for the exhibition designed by Program Collective "Water for Life" in the Water Tower Building.
The calculation of the structures in charge of the engineer José Maria Velasco of Amatria and construction under the direction of PQC PROGRAM COLLECTIVE.
Technical Characteristics
The sculpture was made up of 135 different pieces that were attached by wires to the top of the Water Tower building. These pieces were designed entirely by computer by Pere Gifre represented a drop of water hitting a surface.
Development process
Using visual effects (special effects) Pere Gifre fluid generated by processes of computer aided design adapted for manufacturing.
The manufacturing process performed by PQC at facilities in MADRID combines computer aided manufacturing with traditional processes to generate the final volumes were subsequently transported and installed at the Water Tower in the International Expo Zaragoza 2008 SPAIN.
This is the cover of a 36-page insert in the December 1964 Mexican edition of Reader’s Digest. The booklet was a formal announcement of Ford new manufacturing plant at Cuautitlan, just north of Mexico City. The booklet opens with a message from Mexican President Adolfo Lopez Mateos, and describes the manufacturing process and is full of ads from Ford suppliers.
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.
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/
-----------------------------
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
-----------------------------
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.
The Horrockses Cotton Fairies take you on a tour of the cotton manufacturing processes at three of their Preston Mills - Yard Works, Centenary / New Preston and Fishwick.
This was Horrockses - Crewdson's contribution to the 1920 trade publication Concerning Cotton - A brief account of the aims and achievements of the Amalgamated Cotton Mills Trust Limited and it's component companies.
TO ENLARGE - either:
1. Right-click the image then choose Original or...
2. Select View all sizes from the Actions tab then choose Original
The Horrockses Cotton Fairies take you on a tour of the cotton manufacturing processes at three of their Preston Mills - Yard Works, Centenary / New Preston and Fishwick.
This was Horrockses - Crewdson's contribution to the 1920 trade publication Concerning Cotton - A brief account of the aims and achievements of the Amalgamated Cotton Mills Trust Limited and it's component companies.
TO ENLARGE - either:
1. Right-click the image then choose Original or...
2. Select View all sizes from the Actions tab then choose Original
The Horrockses Cotton Fairies take you on a tour of the cotton manufacturing processes at three of their Preston Mills - Yard Works, Centenary / New Preston and Fishwick.
This was Horrockses - Crewdson's contribution to the 1920 trade publication Concerning Cotton - A brief account of the aims and achievements of the Amalgamated Cotton Mills Trust Limited and it's component companies.
TO ENLARGE - either:
1. Right-click the image then choose Original or...
2. Select View all sizes from the Actions tab then choose Original
The research space at Sector 7 of the Advanced Photon Source at Argonne National Laboratory is the only X-ray beamline in the world dedicated to fuel injection studies. The auto and aerospace industries and military use the system to study ways to make engines more fuel efficient and stable as well as to test new types of alternative fuels.
The injection system also aids in studies of spray systems, such as those used in manufacturing processes and industrial paint and coating equipment. The black foam at the center of the picture covers a rocket injector-system for the NASA rocket Morpheus that will be tested. November 2014.
Photograph Courtesy of Argonne National Laboratory
Mouth shut, lest one drools. See also manufacturing process of Jilipi
Calcutta, India 6.5.2007 / 20:14
The Horrockses Cotton Fairies take you on a tour of the cotton manufacturing processes at three of their Preston Mills - Yard Works, Centenary / New Preston and Fishwick.
This was Horrockses - Crewdson's contribution to the 1920 trade publication Concerning Cotton - A brief account of the aims and achievements of the Amalgamated Cotton Mills Trust Limited and it's component companies.
TO ENLARGE - either:
1. Right-click the image then choose Original or...
2. Select View all sizes from the Actions tab then choose Original
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/
-----------------------------
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
-----------------------------
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.
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.
Hyperion, Hypersonic Mach 15 Scramjet Missile - IO Aircraft - ARRW, HAWC, Air Launched Rapid Response Weapon
Length: 120" / Span 25"
Scramjet, Hypersonic, ARRW, HAWC, Air Launched Rapid Response Weapon, Scramjet Physics, Scramjet Engineering, Hypersonic Missile, hypersonic weapon, hypersonic fighter, hypersonic fighter plane, tgv, tactical glide vehicle, hypersonic commercial aircraft, hypersonic commercial plane, hypersonic aircraft, hypersonic plane, hypersonic airline, tbcc, glide breaker, fighter plane, hypersonic fighter, boeing phantom express, phantom works, boeing phantom works, lockheed skunk works, boost glide, tactical glide vehicle, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, defense science, missile defense agency, aerospike, hydrogen aircraft, airlines, military, physics, airline, aerion supersonic, aerion, spike aerospace, boom supersonic, , darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, afosr, socom, arl, army future command, mda, missile defense agenci, dia, defense intelligence agency, Air Force Office of Scientific Research,
Iteration V8, Hyperion Mach 15 #hypersonic #scramjet (50% faster then the X-43 #nasa), 300% faster than #Lockheed, #NorthropGrumman, #Raytheon, and Boeing. Much is sanitized as the technology advances are dramatic and not public.
DOD's funding of #AGM-183A / Air Launched Rapid Response Weapon, the poeple developing it barely comprehend student level capabilities and 50/50 it will disintegrate even at Mach 5. China and Russia, already much faster and higher tech making it obsolete already, India's recent test, apx 700 mph faster.
Summarized details are accurate
#hypersonic #hypersonics #scramjet #hypersonicplane #hypersonicaircraft #skunkworks #spaceplane #boeing #lockheed #raytheon #bae #bombardier #airbus #northopgrumman #generaldynamics #utc #ge #afrl #onr #afosr #ReactionEngines #spacex #virginorbit #usaf #darpa #mda #rollsroyce #nasa #tesla #safran #embraer #AirLaunchedRapidResponseWeapon #additivemanufacturing #military #physics #3dprinting #supersonic #ramjet #tbcc #collinsaerospace #rockwell #phantomworks #hypersonicmissile #alrrw #boeingphantomworks #generalatomics #cessna #dassault #arl #unitedlaunchalliance #spaceshipcompany #navair #diu #dia #usaf #unitedtechnologies #defenseadvancedresearchprojectagency #graphene #additivemanufacturing
-----------------------------
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.
The sewers require continuous maintenance. Cooking fat needs to be regularly removed, and recycled paper products tend not to break down so quickly - perhaps because the shorter, more damaged fibres need to be more strongly bonded in the re-manufacturing process.
I used auto colour balance, and long exposures of several seconds but the fluorescence - under the UV fluorescent lighting - from waste detergent water - seems real.
See also the related Brighton Sewer Tour Gallery.
External links:
Sewer tour photo gallery [Southern Water]
Brighton's magnificent sewers [Southern Water tour details]
A little history of Brighton's magnificent sewers [Southern Water]
From Barfoot's series of coloured lithographs of 1840 depicting the cotton manufacturing process.
Original text written to accompany Lithograph No.2:
"When the COTTON is gathered, it generally happens that the seeds, and parts of the husk, cling very fast to it. It would take a very long time, and be very tedious, to pick it by the hand. Machines have, therefore, been made, which do this work very quickly. The Machine used for this purpose is called a Gin, and the operation is called Ginning the Cotton. After this, it is packed closely in bags, and presses are used to reduce it to as small compass as possible, that it may be removed with less trouble and expense. It is sometimes conveyed thousands of miles from the place where it grew; and, after being made into cloth, it is taken back, and work in the same land that produced it. The Cotton-Mill or Factory is a very large, well-lighted building, with a great quantity of Machinery in it, which is very clean, and kept in motion by a powerful Steam-Engine. The first thing done to the Cotton, when taken out of the bags, is to put it into the Willowing-Frame or Blowing Machine, the outside of which you see in this picture. The man on the right, first puts the Cotton on what is called the Feeder, which turns it inside the machine, where there is a large Drum, called a Cylinder, full of spikes or iron teeth, to tear and loosen the Cotton, and to cleanse it from dust and motes. The dust ascends through a large pipe, as seen in the drawing, and the motes fall through below. The clean Cotton is turned out at the other end of the frame by the Discharger, which is kept in slow motion for that purpose; but the motion of the Cylinder is very rapid indeed. Some of these Cylinders turn round two hundred times in a minute."
'The Progress of Cotton', J. R. Barfoot, Manchester, 1840
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.
Mach 8-10 Hypersonic Commercial Aircraft, It-1, 202 Passenger
Seating: 202 | Crew 2+4 (250 if denser seating)
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 1
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
-----------------------------
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.
BlueEdge - Mach 8-10 Hypersonic Commercial Aircraft, 210 Passenger Hypersonic Plane - Iteration 2
Seating: 210 | 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 2
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.
The Chancellor Rishi Sunak visits Pall Corporation, a biotech business in Ilfracombe north Devon, where he met staff and toured the manufacturing process
Photo showing the Project "Urban Green: Bamboo Bicycle" by Angelina Djukic, Lukas Gabesam, Japleen Khurana, Alina Schweighofer (Euregio) HTBLVA Ferlach at the JKU at the Ars Electronica Festival 2021.
In the project “Urban Green: Bamboo Bicycle”, an environmentally friendly manufacturing process of bamboo bicycles was developed. The four artists did not want to accept that the conventional construction of bamboo frames uses non-environmentally friendly fasteners and toxic paints. Therefore, they developed an innovative production process that uses only biodegradable materials such as lignin and bio-resin. The fasteners are designed using CAD programs such as Fusion 360 and produced via 3D printing. Environmentally friendly injection molding technology is used to connect the fasteners to the frame. In addition, the artists* have given the bamboo bicycle of the future an innovative design that can be adapted to individual wishes.
Urban Green: Bamboo Bicycle won the Young Professionals Award of Distinction in the u19-create your world category at the Prix Ars Electronica 2021.
Credit: tom mesic
»You & Me« from the Scrappies series - cast in 925 Sterling silver.
The body parts of the Scrappies are inspired by everything that can be found in a scrapyard: Old bolts and nuts, rusty coils, pipes, parts of ball bearings, tin cans, and more.
The figurines are cast in minute detail, including "rust holes" and traces of an alleged "welding". The scrap metal look gives the characters their own special, irresistible charm.
Each of the pendants is individually and uniquely created in a complex, novel manufacturing process:
It all begins with a digital 3D design which is then used to build a wax model. The wax model is created layer by layer on a special 3D wax printer. The wax model is used to produce a negative, heat-resistant shell around the wax.
Heat is applied to the outer shell such that the wax melts out and leaves room for liquid silver to be poured in. Finally, the shell has to be destroyed to take the finished object out.
More at www.indiegogo.com/you-n-me
The Legos Company has been fantastically successful. In each of the last 5 years sales have risen 24% and profits, 40%.
But it was not always so. For most of its 80-year existence, its reach did not extend so far beyond Billun, Denmark, where Ole Kirk Christiansen, a carpenter unable to secure enough wood to build furniture during the 1930s depression, began experimenting building wooden toys.
The company under Christiansen’s progeny soared in the last couple decades but tie-in products to the Star Wars and Harry Potter movies nearly doomed the company in 2003; sales of those products crashed when the movie franchises hadn’t yet come out with new films.
This, according to Wharton Professor Dave Robertson and former LEGO Professor of Innovation and Technology Management at Switzerland's Institute for Management.
Robertson, a Chestnut Hill resident, discussed his new book, “Brick by Brick: How LEGO Rewrote the Rules of Innovation and Conquered the Global Toy Industry” at the William Jeannes Library in Lafayette Hill this past Thursday evening.
He began his slide talk by distributing baggies, each packed with the identical same six logo pieces, and instructed the audience to “Build a duck” and gave us only a minute or two. Participants then brought their “ducks” up to the front table.
At the end of the talk, Robertson pointed to the wide variation of these Lego “ducks” as evidence that incredible creativity is possible even when severe constraints are imposed, a major thesis of his book.
He credits Lego Company’s resurgence to its imposition of key constraints: drastically reducing the number of parts (about 14000 different ones at peak) that had made the manufacturing process unwieldy, getting back to products that are more “Lego-y” and subjecting product proposals to the approval a committee of 3 seasoned Lego designers. And, ultimately, insisting that projected profitability be a constant constraint.
What Lego pioneered was not just a toy, Robertson maintains, but a system of play. And that system “is about the brick.” See www.businessweek.com/articles/2013-12-16/mattels-lego-tra...
Oban Distillery is one of the oldest distilleries in Scotland, dating back to around 1800. It underwent refurbishment in the 1890's and there has been little change to the present buildings since then.
Oban distillery takes it name from the town where the Highlands meet the Islands and nestles below the steep cliff that overlooks Oban.
Having booked ourselves for the one hour distillery tour (£ 7.50 each) I was extremely disappointed to be told long after we had paid and about to walk onto the distillery tour it was forbidden to take photographs (for Health & Safety reasons. All you flickr fiends better stop taking photos now if you want to live much longer). Since this was pretty well the only reason why I wanted to go in I debated demanding my money back but hesitated in doing so. I must admit I was going to take a photo of a machine that crushed the malted barley, and raised my camera to do so when the wizened tour guide behind me said, "That's the last photo you'll take" in a way that made me think she would take each of my limbs and put them across her knees and snap them in half before tearing my head from my torso with her bared teeth and throwing the remains over the cliff behind the distillery. There was no warehouse where the men of Oban tossed and turned the malted barley to let it germinate and infuse with the aroma of peat. They import the grain ready malted. There was no warehouse visible where we could see hundreds of wooden casks sitting silently in a cool warehouse for a minimum of 14 years. There was a sample of 53% proof 10 year old malt, but when you are given what seemed like around 2.5ml, not much more than a few teardrops, you felt they were a bit mean, although you did get a modest tot and a glass of their signature whisky afterwards before being led into the distillery shop where you could buy more. The tour was 'efficient' but for me lacked the very 'spirit' of whisky I had come to see, the malt being turned, the peat smoke, the rows of barrels sitting in the warehouse. Sadly, it didn't feel as special to me as it should have done. The Health & Safety lecture reminded me it had just become a modern manufacturing process.
The Iso Grifo is a limited production grand tourer manufactured by Italian automobile manufacturer Iso Autoveicoli S.p.A. between 1965 and 1974.[1] Intended to compete with Grand Touring offerings from Ferrari and Maserati, it used a series of American power trains and components supplied by Chevrolet and Ford.[2][3][4] Styling was done by Giorgetto Giugiaro at Bertone, while the mechanicals were the work of Giotto Bizzarrini.[5]
The first production GL models appeared in 1965 and were powered by American Chevrolet small-block 327 (5.4-litre) V8 engines fitted to American supplied Borg-Warner 4-speed manual transmissions. The 5.4-litre engine was rated at 300 hp (220 kW) in its standard form and allowed the car to attain a speed of 110 km/h (68 mph) in first gear.[6]
Iso Grifo Series II
In 1970, the Grifo Series II was introduced, with sleeker styling and hide-away headlights and powered by big-block Chevrolet 454 V8 (7.4-litre) engines. It was replaced in 1972 with the Grifo IR-8, which used a small-block Ford Boss 351 engine (5.8-litre) as its power-train. This was the last new Iso of any type, as the manufacturer went bankrupt; it shut down and ceased all operations permanently in 1974.[1] The bankruptcy had a number of causes, perhaps the largest being the 1973 oil crisis, which significantly reduced demand for cars with large displacement engines.
History
Iso Grifo Series I, rear view
Iso S.p.A. was already well known for producing the high-performance Rivolta IR 300; a sleek looking 2+2 Coupe based on Chevrolet Corvette mechanicals.[7] After leaving Ferrari, in 1961 Giotto Bizzarrini set up “Prototipi Bizzarrini” in Livorno, Tuscany where he designed and consulted for marques such as ATS, Lamborghini, and Iso.[8] In 1963, he designed the Iso Grifo A3/L ("L" for Lusso, Italian for "luxury") for Renzo Rivolta, who was looking for a follow-up to his IR 300.[8] The body was designed by Giorgetto Giugiaro at Bertone, while Bizzarrini put his expertise in the mechanicals.[5]
Bizzarrini figured there would also be a demand for a race version of the Grifo and developed the A3/C (C for Corsa) with a dramatic, modified alloy body.[8] He later dubbed it his “Improved GTO", as he designed the 250 GTO when he had worked for Ferrari. In the Corsa, he moved the engine back about 40 mm (1.6 in), making the A3/C a front, mid-engine car. To adjust the timing, mechanics had to remove a piece of the dashboard.[8] Both the racing and road legal versions of the car were being built simultaneously. When leaving the factory, the Iso Grifo was originally fitted with Pirelli Cinturato 205VR15 tyres (CN72).
At the Turin Motor Show that same year, Bertone showed the Grifo A3/L prototype while Iso unveiled the unpainted competition version: the Iso Grifo A3/C.[9] Both became successful in their own right, the road car receiving praise from the press, while the race car performed very well although it had been made on a much tighter budget compared to Ferrari.[9] Rivolta also showed a prototype A3/L Spyder at the Geneva Motor Show.
Grifo GL – Bizzarrini A3/C split
Iso concentrated on getting the A3/L ready for production, focusing on some of the design changes that had to be made to the prototype. The car got a light face-lift that made it less aggressive in appearance. It was given a modified but reliable 5.4 litre Chevrolet small-block 327 V8 engine—having variable power outputs of 300–350 horsepower (220–260 kW)—coupled to a Borg-Warner 4-speed manual transmission. The engines were completely ordered and manufactured in the United States; they were shipped to Italy, where they were taken apart before they were eventually installed in the cars. This was similar to the manufacturing process of the IR 300. With a weight of less than 2,200 lb (1,000 kg), the car was able to attain a top speed of over 275 km/h (171 mph).
In 1964, the prototype A3/C raced at Le Mans (driven by Edgar Berney and Pierre Noblet), running well until brake problems required a two-hour pit stop.[9] The car resumed the race, finally finishing 14th. In 1965, the car performed better, finishing 9th at Le Mans.[9]
The production of the Iso Grifo GL started in 1965, but the Bizzarrini and Rivolta partnership quickly fell apart over the use of the name Grifo. This resulted in separate production of the Grifo GL and the competition Bizzarrini A3/C.[9][10] The Grifo GL was produced at Bresso, while the A3/C was produced at Piero Drogo's Sports Cars of Modena, under Bizzarrini's strict supervision. Bizzarrini refined his A3/C, eventually developing his line of models.[9][10] Only 22 examples of the Grifo A3/C were made before Rivolta and Bizzarrini split.
Model year changes
Iso Grifo Can Am Series I
In October 1966, the first Grifo (car #97) with a targa top was shown at the Turin Motor Show. Designed by Bertone and featuring the stunning removable roof, the reliable 300 hp Chevy 327 V8, and the coveted ZF 5 speed transmission. Only fourteen Series I Targas and four series II Targas were built.[3]
In 1968 the Grifo 7 Litri was introduced, featuring a Chevrolet L71 big-block engine, a Tri-Power version of the 427 engine. The massive power plant required several mechanical changes to the car in order to fit, i.e. strengthened chassis components as well as an enlarged engine compartment with reinforced mounts. A large hood scoop (dubbed "Penthouse" due to its size) was added to clear for the engine's deck height. It produced an officially advertised minimum of 435 hp (324 kW) at 5,800 rpm. The factory claimed the 7 Litri could attain a top speed of 300 km/h (186 mph).
In 1970, a styling change was made to the nose section of the car for the Grifo Series II. It was given a sleeker look and hide-away headlights. In the IR-9 "Can Am" version, the engine was switched from the 427 engines to the newer, even more powerful Chevrolet 454 7.4 litre engine.
Iso Grifo Can Am with the characteristic 7-litre engine "penthouse" on the hood and Grifo Series II hide-away headlights
In 1972, the Grifo IR-8 was introduced, using a small-block Ford Boss 351 engines. These models can be recognized by their taller hood scoop. This was the final Iso automobile made, as Iso S.P.A. closed its doors in 1974 during the 1970s oil crisis.[1]
Production
In total, 330 Series I and 83 Series II cars were built for a total of 413 cars, 90 of which were 7-litre versions. The rarest are the Series II 5-speeds (23 built) and the Series II Targa (4 built). Due to their rarity today, Grifos are desirable collectibles. A former employee of Iso, Roberto Negri, runs a small company in Clusone, Italy, specializing in maintaining and restoring Grifos. Wikipedia