View allAll Photos Tagged Iteration
During a daylight training iteration at the Joint Multinational Training Command’s (JMTC) Range 309 and its adjacent shoot house in Grafenwoehr , Germany, visiting multinational Soldiers from the International Special Training Centre, also known as ISTC, rehearses combat breaching and clearing techniques before conducting a live-fire explosive breach.
This training, conducted on May 13 and 14, 2013, is part of one of the many course modules offered by ISTC to provide high quality training in advanced and specialized skills to officers and non-commissioned officers from the Special Forces of various NATO nations.
JMTC Grafenwoehr and Hohenfels ranges and facilities are state-of-the-art and offer a variety of adaptable training scenarios and are regularly used by ISTC faculty and students. JMTC proximity to ISTC’s Headquarters in Pfullendorf, Germany, makes it an ideal training venue for NATO Soldiers while enrolled for ISTC training.
Some photos in this set have been redacted for security purposes.
(U.S. Army Photo by Michael Beaton/Released).
VTOL - Hypersonic Plane - Mach 10 Shock Variables - Scramjet - IO Aircraft - Iteration 4 - Hypersonic Physics - Hypersonic Engineering
Early preview (Iteration 4) of an entirely new type of aircraft, no info is on the net yet and won't be for a while. RANGER - 2 Passenger VTOL Hypersonic Plane
www.ioaircraft.com/hypersonic/ranger.php
Drew Blair
www.linkedin.com/in/drew-b-25485312/
Vertical take off and landing - High Supersonic into Hypersonic Realm. Economy cruise above Mach 4, and can accelerate to beyond Mach 8. Non VTOL, could reach LEO. With a range of 5,000+ nm (8,000-10,000nm non vtol). Fuel H2, reducing fuel weight 95%.
Length, 35ft (10.67m), span 18ft (6m).
Propulsion, 2 Unified Turbine Based Combined Cycle. 2 Unified thrust producing gas turbine generators that provide the power for the central lifting fan (electric, not shaft driven) and the rear VTOL.
Estimated market price, $25-$30 million in production. New York to Dubai in an hour.
All based on my own technology advances in Hypersonics which make Lockheed and Boeing look ancient.
-------------
boeing phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, defense science, missile defense agency, aerospike, vtol, vertical take off, air taxi, personal air vehicle, boeing go fly prize, go fly prize,
Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
Thought I would upload the first iteration of the preference section. It is worth noting that this video (and all videos in this set) are the rough-round-the-edges in progress stuff. Animations, transitions even some elements are not polished yet.
So, thought I would just flick through some of the different 'tabs' or sections within the preferences and give you a general idea. You can see some elements aren't there yet (i.e. input fields in 'Controls').
We animated the width of the window where required, the content within would be best served with a nice quick cross-fade. Buttons could also do with a slight fade… you notice the sudden change between normal and press state on the dark buttons (the highlight), so that could do with a quick fade out on mouse down.
Anyway, there you go… progress. This is just the visual stuff as there is a lot going on behind the scenes. It is also worth noting that this work has now been merged into the master branch and work has started on getting the backend talking to the frontend. (Which just means… we are starting to make it real).
Black nursing top: Target
Black ankle pants: Old Navy
Booties: Civico 10, via DSW
Purple grandma sweater: H&M
Gray open cardigan: TJ Maxx
TOKYO, Japan (June 13, 2022) - Indonesian Marine Corps Brig. Gen. TNI (Mar) Y. Rudy Sulistyanto, left, commander of the 3rd Indonesian Marine Force, Col. Hendra D. Wijaya, expert staff for military cooperation, Indonesian Marine Corps Command, and U.S. Marine Corps Lt. Gen. Steven R. Rudder, commander, U.S. Marine Corps Forces, Pacific, participate in a trilateral meeting during the eighth iteration of the Pacific Amphibious Leaders (PAL) Symposium , Tokyo, Japan, June 13, 2022. PAL Symposium consists of discussions and presentations conducted to promote regional security and to enable responsive forces during crisis situations. The 2022 symposium brought together senior leaders from 18 participating delegations who are committed to a free and open Indo-Pacific, with the objective of strengthening and developing regional relationships. (U.S. Marine Corps photo by Lance Cpl. Haley Fourmet Gustavsen) 220613-M-GI936-506
** Interested in following U.S. Indo-Pacific Command? Engage and connect with us at www.facebook.com/indopacom | twitter.com/INDOPACOM | www.instagram.com/indopacom | www.flickr.com/photos/us-pacific-command; | www.youtube.com/user/USPacificCommand | www.pacom.mil/ **
A first iteration. Several problems here, including: 1) you can see unwanted reflections of the framework I used to set up the photo; 2) I used tracing paper as a diffuser with one of my speedlites and yiou can see the texture of this reflected on the plexiglass (rather than the clear shine of the plexiglass); 3) the magenta gel did not fully cover the second light source so some bits of the reflections are blown out.
Meiji Shrine (明治神宮 Meiji Jingū?), located in Shibuya, Tokyo, is the Shinto shrine that is dedicated to the deified spirits of Emperor Meiji and his wife, Empress Shōken.[1] When Emperor Meiji died in 1912 and Empress Shōken in 1914, the Japanese people wished to pay their respects to the two influential Japanese figures. It was for this reason that Meiji Shrine was constructed and their souls enshrined on November 1, 1920.[2]
After the emperor's death in 1912, the Japanese Diet passed a resolution to commemorate his role in the Meiji Restoration. An iris garden in an area of Tokyo where Emperor Meiji and Empress Shōken had been known to visit was chosen as the building's location. Construction began in 1915, and the shrine was built in the traditional Nagarezukuri style and is made up primarily of Japanese cypress and copper. It was formally dedicated in 1920, completed in 1921, and its grounds officially finished by 1926.[3]
The original building was destroyed during the Tokyo air raids of World War II. The present iteration of the shrine was funded through a public fund raising effort and completed in October, 1958.[4]
Meiji Shrine was brought into the flow of current events with the 2009 visit of United States Secretary of State Hillary Clinton. After arriving in Tokyo on her first foreign trip representing the newly elected President Barack Obama, she made her way to this shrine in advance of meetings with Japan's leaders to show her "respect toward history and the culture of Japan." [5]
Meiji Shrine is located in a forest that covers an area of 700,000 square-meters (about 175 acres). This area is covered by an evergreen forest that consists of 120,000 trees of 365 different species, which were donated by people from all parts of Japan when the shrine was established. The forest is visited by many people both as a spiritual home of the people and as a recreation and relaxation area in the center of Tokyo.[2] The shrine itself is comprised of two major areas:
[edit]Naien
The Naien is the inner precinct, which is centered on the shrine buildings and includes a treasure museum that houses articles of the Emperor and Empress. The treasure museum is built in the Azekurazukuri style.
[edit]Gaien
The Gaien is the outer precinct, which includes the Meiji Memorial Picture Gallery that houses a collection of 80 large murals illustrative of the events in the lives of the Emperor and his consort. It also includes a variety of sports facilities, including the National Stadium, and is seen as the center of Japanese sports. It also includes the Meiji Memorial Hall, which was originally used for governmental meetings, including discussions surrounding the drafting of the Meiji Constitution in the late 19th century. Today it is used for Shinto weddings.
The latest iteration of the 'White Knight' features the gold anniversary scheme, in an even more minimalist motif.
2022 Ford Police Interceptor Utility Hybrid AWD
Uniformed Services Division
Sector 5 (NorthWest)
Baynard Police
Beachcomber Drive
Cypress Gardens
Baynard County, Florida, USA
#1stPixBaynardPolice
For more info about the dioramas, check out the FAQ:
(Updated June 2023) 1stPix FAQ
*******************************************************************************
This image and its name are protected under copyright laws.
All their rights are reserved to my own and unique property.
Any download, copy, duplication, edition, modification,
printing, or resale is stricly prohibited.
*******************************************************************************
11 712 vertices
48 912 triangles
First iteration of Oronia, which started out as an experiment. From here she just kept growing and taking on a life of her own.
The department has been building up a library of design related reference books over the last few years. Pupils are encouraged to make use of these books on a regular basis. The photographs here demonstrate the tremendous wealth of content contained therein.
The sequence has been shot in such a way that the cover of the book is shown first and a few sample pages are included to give the student an idea of the content the book contains. Pupils may then approach staff and request a short term loan.
The department has been building up a library of design related reference books over the last few years. Pupils are encouraged to make use of these books on a regular basis. The photographs here demonstrate the tremendous wealth of content contained therein.
The sequence has been shot in such a way that the cover of the book is shown first and a few sample pages are included to give the student an idea of the content the book contains. Pupils may then approach staff and request a short term loan.
Some iterations of the simple pattern generator. Source code can be downloaded from Open Processing.
>>>http://www.openprocessing.org/visuals/?visualID=14117
The final iteration of the P5 appeared in September 1967. Now powered by the 3,528-cubic-centimetre (215.3 cu in) Rover V8 engine also used in the 3500, the car was badged as the "3.5 Litre", and commonly known as the 3½ Litre. The final letter in the "P5B" model name came from Buick, the engine's originator. Rover did not have the budget to develop a new engine, hence they chose to redevelop the lightweight aluminium engine available from Buick.
Output of 160 hp (120 kW) was claimed along with improved torque. When introduced in 1967 the Buick designed V8 produced 160 PS (118 kW; 158 hp) at 5,200 rpm and 210 lb⋅ft (280 N⋅m) of torque at 2,600 rpm.
The exterior was mostly unchanged, apart from bold '3.5 Litre' badging, a pair of fog lights which were added below the head lights, creating a striking 4 light array, and the fitting of chrome Rostyle wheels with black painted inserts. The P5B existed as both the 4-door coupé and saloon body style until end of production. Production ended in 1973, by when 9,099 coupés and 11,501 saloons had been built.
The 3½ Litre saloon variant was a favourite of high-ranking Government Ministers, and served as Prime Ministerial transport for Harold Wilson, Edward Heath, James Callaghan and Margaret Thatcher. As testament to their suitability, the last batch of P5Bs to roll off the Rover line in June 1973 was purchased by the British government and placed in storage, to be released for government use as required.
As for most of the models built his November, the Rover P5B 3.5 Litre is a major redesign of a previously created model. In LUGNuts there was a build challenge named 'Redo or Redemption' just for this type of build.
Date: May, 2017
Medium: Digital Photomontage
Locations: Tokyo & Hiroshima Children's Peace Memoria, Japan and Santa Cruz, CA.
Dimensions: 20" x 26.75"
©2017 Tony DeVarco and Mayako Nakamura
Part of the new series Bonnie DeVarco is calling "Figure | Ground" in collaboration with the Japanese Artist Mayako Nakamura incorporating a detail I made of her "Playground Series V" painting on canvas on the right with a digital photomontage of mine on the left.
To view Mayako's Playground series please go here: www.flickr.com/photos/ma85/albums/72157681102919935
The department has been building up a library of design related reference books over the last few years. Pupils are encouraged to make use of these books on a regular basis. The photographs here demonstrate the tremendous wealth of content contained therein.
The sequence has been shot in such a way that the cover of the book is shown first and a few sample pages are included to give the student an idea of the content the book contains. Pupils may then approach staff and request a short term loan.
The department has been building up a library of design related reference books over the last few years. Pupils are encouraged to make use of these books on a regular basis. The photographs here demonstrate the tremendous wealth of content contained therein.
The sequence has been shot in such a way that the cover of the book is shown first and a few sample pages are included to give the student an idea of the content the book contains. Pupils may then approach staff and request a short term loan.
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/
-----------------------------
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/
-----------------------------
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.
*******************************************************************************
This image and its name are protected under copyright laws.
All their rights are reserved to my own and unique property.
Any download, copy, duplication, edition, modification,
printing, or resale is stricly prohibited.
*******************************************************************************
Deformation of the Sierpinski tetrahedron.
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/
-----------------------------
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, 220 Passenger Hypersonic CommercialPlane - 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.
The department has been building up a library of design related reference books over the last few years. Pupils are encouraged to make use of these books on a regular basis. The photographs here demonstrate the tremendous wealth of content contained therein.
The sequence has been shot in such a way that the cover of the book is shown first and a few sample pages are included to give the student an idea of the content the book contains. Pupils may then approach staff and request a short term loan.
The department has been building up a library of design related reference books over the last few years. Pupils are encouraged to make use of these books on a regular basis. The photographs here demonstrate the tremendous wealth of content contained therein.
The sequence has been shot in such a way that the cover of the book is shown first and a few sample pages are included to give the student an idea of the content the book contains. Pupils may then approach staff and request a short term loan.
The third iteration of the original Leica M4, the M4-P, is the successor to the M4-2 or the rangefinder that saved Leitz's rangefinder line of cameras. Produced in Midland, Ontario, by Ernst Leitz Canada and released in 1980. The M4-P offers up auto-adjusting frame lines for a set group of focal lengths and is often called the inexpensive M-Series Rangefinder.
The total review drops in September 2023!
Leitz Leica M4-P - 7Artisans DJ-Optical 35/2 - Kodak Tri-X 400 @ ASA-320
Ilford Ilfotec HC (1+47) 8:30 @ 20C (Constant Rotation)
Meter: ReveniLabs Incident Meter
Scanner: Epson V700 + Silverfast 9 SE
Editor: Adobe Photoshop CC
Fractal type:mandelbrot
Plot size (w,h):2210,2210
Maximum iterations:33000
Center Point (real, imaginary):-0.75037128553,0.015510182 i
Plot Width (real):7.5E-09
Color scheme name:PMS_colors2
I think I like the modeling of the underside more than the top side of the chair in this iteration... although this leg needs to be worked out better.
Black nursing top: Target
Black ankle pants: Old Navy
Booties: Civico 10, via DSW
Purple grandma sweater: H&M
Gray open cardigan: TJ Maxx
SIX is an experimental electronic, surround sound performance series presented by the BFA in Video and Sound program. This iteration of SIX will feature renowned international sound artist Robert Henke along with several other performers. In lieu of traditional listening orientation, the music and sound is produced in an open, multi-directional format. This allows the performer, sound, environment, and audience to form an exploratory relationship. The audience is encouraged to walk around, lay down (bring a pillow or blanket if you like), and experience the sound from different angles.
Featured Performers
Robert Henke
Marcus Fischer
Strategy + Jetfinger
Solenoid
Dweomer
Mike Jedlicka + wndfrm
Robert Henke is a visiting artist from Europe, and is presenting a lecture on September 24 titled "Sound, Structures and Machines."
The BFA in Video and Sound at PNCA promotes an expansive investigation of video and sound as disciplines both distinct and allied. Cultivating a practice-based media literacy, this program supports the acquisition of critical, aesthetic and technical skills, which are vital to cultural production in today’s media environment.
Please join PNCA for the fifth edition of SIX, an experimental, surround sound performance series.
Artist Info
ROBERT HENKE, born 1969 in Munich, Germany, is a composer, sound designer, software developer, installation artist and audiovisual performer. His art is focused on carefully shaped details and gradual changes of repeating structures in different time scales. His sonic explorations are rooted in academic sound research and computer music as well as in contemporary club culture.
monolake.de/
MARCUS FISCHER is a musician + multimedia artist currently based in Portland, Oregon. He has released two albums on the 12k label along with numerous EPs and collaborations for a variety of other outlets. Field recordings, chance, and DIY instruments, coupled with acoustic instrumentation and visual art, define what has become Marcus’s minimal signature.
mapmap.ch
STRATEGY, otherwise known as multi-instrumentalist and programmer Paul Dickow, wires together programming and performing experience via a hodgepodge of table top electronics, computers and realtime musicianship. A musical explorer, Paul has been a longtime participant in Portland’s underground music community.
community-library.net
ROMEO FAHL ( JETFINGER ) currently lives in Portland, Oregon and has been playing music since the mid-80’s. He has been custom-building a massive modular synthesizer for the last 18 years. SIX has been proving a great outlet to hear and see this beast in all it’s burbling, growling, buzzing, multi-channel glory.
soundcloud.com/jetfinger
SOLENOID is the moniker of David Chandler, who loves synthesizer music and sound design. His unique mix of experimental and dance music has found him performing in festivals in the USA and Europe. He’s had many recordings released on various formats and from various countries over the last 13 years, but his home continues to be Portland.
community-library.net
DWEOMER (Jef Drawbaugh ) is an urban druid of sound. His new work is in sound design and composition for media, leaning heavily on cinematic themes. His live music and recorded soundscapes blossom with connections and juxtapositions between the technical world of electronic instruments and songcraft, rife with the fluid and nebulous areas of the cosmos and emotional response. He discovers patterns and shapes amidst chaotic spaces and lets stories unfold through cosmic voyages.
cascadnacsound.com
MIKE JEDLICKA runs Optic Echo Records and has a weekly show on Portland Radio Authority. He uses a multitude of instruments and electronics to create a wide variety of music, recently focusing on field recording laden acoustic ambient and experimental noise. His last release was a split 12" in 2010 entitled “Tabor / NW Passage”, on Optic Echo Records.
opticecho.com
WNDFRM is Tim Westcott, who has been working with sound as a creative medium since the early 90’s. He treats sound as an architectural element, incorporating manipulated field recordings, minimalistic sine tones, lush atmospheric harmonics, and the occasional dub-wise rhythmic foundation.
nuevaforma.com
September 23, 2012.
Photographs by: Marshall Astor '13.
The department has been building up a library of design related reference books over the last few years. Pupils are encouraged to make use of these books on a regular basis. The photographs here demonstrate the tremendous wealth of content contained therein.
The sequence has been shot in such a way that the cover of the book is shown first and a few sample pages are included to give the student an idea of the content the book contains. Pupils may then approach staff and request a short term loan.
Iteration 10 - Raven B Model - Mach 8-10, 22 Passenger hypersonic business jet. New iteration reflects design changes from Raven A Model, which is an SSTO, a real one. ALL technologies associated "are" developed. It is also ZERO CARBON.
More Info: www.ioaircraft.com/hypersonic/raven-business.php
Not a graphics design or graphics rendering, but sanitized cad screenshots. This is not a concept, but ready for serial production. Not really looking for investors and such. Everything DOD is funding for hypersonic fixed aircraft is OLD and rehashed perpetually for 40+ years at 10X the price. Others, pushing supersonics and hypersonics, also very old technologies at very expensive prices and operating costs. This, about the same as a G650 or Global Express costs and operating costs and normalized Mach 10 dynamics in all regards in atmosphere.
#afrl #afwerx #defensewerx #usaf #darpa #onr #arl #boeing #lockheedmartin #airbus #raytheon #northropgrumman #aerojet #dynetics #easa #bae #afosr #hypersonic #supersonic #scramjet #reactionengines #innovation #graphene #hydrogen #spacex #ula #virgingalactic #rocketlab #nasa #snc #sierranevadecorporation #dreamchaser #sdo #sda #spaceforce #dod #icao #dassault #bombardier #gulfstream #cessna #bigalow #boomsuprsonic #aerion #esa #airplane
This image is an iteration of a third test of additive color. This test attempts to determine whether luminance provided to a surface by a light source can affect additive color.
Setup: A large rectangle of black velvet was laid flat on the floor, and three identical rectangles of white ("snowcap") cardstock were laid on top of the velvet. The camera shutter was opened. An external flash unit with a red gel was fired 2 times from a height of approximately 30 inches. One rectangle (sheet) was removed. The flash was fired 2 times again. A second sheet was removed. The flash was fired 2 times again and the third sheet was removed. The camera shutter was closed.
The sheet that appears to be on the bottom of the pile, the darkest sheet, was actually on top and the first one to be removed after 2 flashes of the strobe. The middle sheet was the second one removed after 4 flashes. The bottom sheet, with 6 flashes, is the brightest one. The edges of sheet are visible as shadow lines on the sheets underneath them.
The two brightest sheets in this image are brighter than all the sheets in the previous image.
The added light should provide more colors for light painting.
Gels used were Rogue Lighting Filters Bright Red (f-stop loss 3 1/2). The flash unit used was a Yongnuo YN-568EX II 4-Channel TTL Flash Speedlite for Canon E-TTL/E-TTL II Cameras. A flash unit was used to provide more control over the amount of light to be supplied. Its output is more measurable and repeatable than a flashlight timed by a human.