iteration photos on Flickr

Drew Blair

Fractalworks plot May22mja1e

--------------

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.

-------------

tbcc, glide breaker, fighter plane, hyperonic fighter, stealth fighter, boeing phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, defense science, missile defense agency, aerospike, vtol, vertical take off, air taxi, personal air vehicle, boeing go fly prize, go fly prize,

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

Raven B Model, Mach 8-10 Hypersonic Business Jet - Iteration 10 (not a graphics design) by IO Aircraft

2

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

"iterations" 4 by Nick Hughes

3

This one has the most editing (layered two iterations) and is also the biggest in case I want to print it.

Delta-7 Jedi Interceptor MOC by GUMBINGER

2

Here is my second iteration of one of my favorite ships of Star Wars -- the Delta-7 Aethersprite Delta-7 Jedi Starfighter.

@khatmorg & @atlas_er are big influences on this design -- especially the cockpit area of @khatmorg & the wings by @atlas_er. Biggest difference in mine is the overall length is shorter by two studs (which I think is more accurate).

Overall I'm really happy with how it came out. I tried my best to eliminate all gaps, and make it smooth as possible. I've very proud of the green accent on the back wings, and how I was able to keep the front wing/hood area smooth.

I couldn't squeeze in rear landing gear, but I love how the underside came out.

Iterations: Fujiko Mine by Medicom Toy by stasiuwong

6 3

Different productions of the same character from the Lupin III manga and anime series.

(L) from the Stylish Collection

(R) from the Pre-Assembled Collection

Both figures are 12-inches tall.

3D view of May22mja1e by Kent Schimke

3 2

Fractal type:julia

Plot size (w,h):1280,1280

Maximum iterations:31000

Center Point (real, imaginary):-2.565481e-08,2.565481e-08 i

Plot Width (real):2.19E-05

Julia origin (real, imaginary):0.2633511860154667,-0.003120133399108344 i

Source mandelbrot width:7.5E-13

Color scheme name:ColorColorWheel

2013 Branch Week_25 by West Point - The U.S. Military Academy

In its second iteration at the U.S. Military Academy, the Department of Military Instruction hosts Branch Week Sept. 9-14 at West Point, N.Y. With roughly 180 Army officers and non-commissioned officers, representing all 16 commissionable branches, the weeklong Corps of Cadets “career fair” presented cadets will hands-on, face-to-face career guidance and counseling from branch representatives across the nation. Several hundred tons of equipment, tanks, attack helicopters and armored vehicles were on display throughout Central Area, to include a functional tactical operations center. U.S. Army photo by Mike Strasser/USMA PAO

BlueEdge - Mach 8-10 Hypersonic Commercial Aircraft, 220 Passenger Hypersonic Commercial Plane - Iteration 3 by IO Aircraft

1

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

-----------------------------

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.

Finished pile by Windell Oskay

2

Iterative Algorithmic Plastic Sculpture: Fimo Fractals!

Read more about this project here

Venom at Cobra Gold by MarineCorpsAviationAssociation

3

A crew chief disembarks a UH-1Y Venom at U-Tapao International Airport, Kingdom of Thailand, Feb. 10, 2018. Marine Light Attack Helicopter Squadron 369 ‘Gunfighters’ arrive to the Kingdom of Thailand to participate in the 37th iteration of Cobra Gold as part of the U.S. Marine Corps Aviation Combat Element. HMLA-369, Marine Aircraft Group 39, 3rd Marine Aircraft Wing, is currently forward deployed under the unit deployment program with MAG-36, 1st MAW. Exercise Cobra Gold 2018 is an annual exercise conducted in the Kingdom of Thailand held from Feb. 13-23 with seven full participating nations. (U.S. Marine Corps photo by Cpl. Andy Martinez)

Chevrolet C1 1960 Corvette Roadster by Peter Blackert

1

I quite like this C1 Corvette. It happens to be in my 'Automobiles of the Chrome Age' book, so I kind of have to make it the way it appears: 1960, white with blue coves. An unusual choice, but one that suits the car - it has that fresh 1950's era feel. Chrome and colour.

The C1 Corvette evolved significantly from the first cars in 1953 until the C2 model of 1963. The 1960 model here has the third iteration of nose - the quad lamps introduced in 1958. It also has the second iteration of the tail - I think this is my favourite treatment.

The V8 engine, introduced for 1966 had grown from 265 CID to 283 CID (4.3L to 4.6L) and now produced no less than 230 bhp (170 kW) and up to 315 bhp (235kW). In the light glass-fibre bodied C1, this made for a very quick car.

Discovery STO - 70 Ton, Single Stage to Orbit Fixed Wing Aircraft - Space Plane by IO Aircraft

Discovery STO - 70 Ton, Single Stage to Orbit Fixed Wing Aircraft - Space Plane - Hypersonic Plane, U-TBCC / Unified Turbine Based Combined Cycle & Aerospike

Iteration 1, Mach 8-10 in amtmosphere, 195ft long, Heavy Lift Single Stage To Orbit Fixed Wing Aircraft. 70 TONS, ie 140,000 LBS, 60 ft X 15ft X 15ft payload bay. Up in the Falcon Heavy and Delta IV class, except not $400 million to launch giant payloads into orbit, but below $250 per lbs, or about $28 million to launch giant payloads, and normalized orbital flight, as normal as a 737 commercial flight. Load up, refuel, take off in an afternoon. I estimate this aircraft would cost about $750 million each for space capable. In atmosphere commercial, roughly $300 million each for a 200 passenger M8-10 (not designed yet)

--------------

Drew Blair

Fractalworks plot Feb26wja1a

--------------

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.

-------------

tbcc, glide breaker, fighter plane, hyperonic fighter, stealth fighter, boeing phantom express, phantom works, boeing phantom works, lockheed skunk works, hypersonic weapon, hypersonic missile, scramjet missile, scramjet engineering, scramjet physics, boost glide, tactical glide vehicle, Boeing XS-1, htv, Air Launched Rapid Response Weapon, (ARRW), hypersonic tactical vehicle, hypersonic plane, hypersonic aircraft, space plane, scramjet, turbine based combined cycle, ramjet, dual mode ramjet, darpa, onr, navair, afrl, air force research lab, office of naval research, defense advanced research project agency, defense science, missile defense agency, aerospike, vtol, vertical take off, air taxi, personal air vehicle, boeing go fly prize, go fly prize,

Advanced Additive Manufacturing for Hypersonic Aircraft

Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.

Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.

*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.

What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.

Unified Turbine Based Combined Cycle (U-TBCC)

To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5

However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.

Enhanced Dynamic Cavitation

Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.

Dynamic Scramjet Ignition Processes

For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.

Hydrogen vs Kerosene Fuel Sources

Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.

Conforming High Pressure Tank Technology for CNG and H2.

As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.

As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).

Enhanced Fuel Mixture During Shock Train Interaction

Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.

Improved Bow Shock Interaction

Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.

6,000+ Fahrenheit Thermal Resistance

To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.

*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope

Scramjet Propulsion Side Wall Cooling

With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.

Lower Threshold for Hypersonic Ignition

Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.

Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities

Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.

Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)

To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.

A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.

Airport bag size checker by With Associates

From a while back, but recent conversations of biometric passports and fancy airport security made me think of this hi-tech system I encountered during a period of heightened alerts.

1. It makes you wonder why the management didn't organise something like this to be manufactured properly, considering how serious a job it was supposed to be doing.

2. It makes you wonder what sort of clever little tinkerer took the initiative to make this in their own time with some left over MDF they had at home.

I'd give them a job over their managers any day.

I'd like also to think that they enjoyed the alliteration in 'baggage gauge'.

Bag-gage-gauge. Baa-gage-gage. B'gagegage.

Reference Book Collection by Jordanhill School D&T Dept

2

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.

Arduino with Rangefinder by Dr_Speed

3rd iteration of "Counter Intelligence" project. For best results with Maxbotic rangefinders I'd recommend the Lilypad. Parts from Sparkfun. Backlit 2x17 driven from serial interface of Lilypad.

Reference Book Collection by Jordanhill School D&T Dept

1

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.

2013 Branch Week_24 by West Point - The U.S. Military Academy

In its second iteration at the U.S. Military Academy, the Department of Military Instruction hosts Branch Week Sept. 9-14 at West Point, N.Y. With roughly 180 Army officers and non-commissioned officers, representing all 16 commissionable branches, the weeklong Corps of Cadets “career fair” presented cadets will hands-on, face-to-face career guidance and counseling from branch representatives across the nation. Several hundred tons of equipment, tanks, attack helicopters and armored vehicles were on display throughout Central Area, to include a functional tactical operations center. U.S. Army photo by Mike Strasser/USMA PAO

2013 Branch Week_27 by West Point - The U.S. Military Academy

In its second iteration at the U.S. Military Academy, the Department of Military Instruction hosts Branch Week Sept. 9-14 at West Point, N.Y. With roughly 180 Army officers and non-commissioned officers, representing all 16 commissionable branches, the weeklong Corps of Cadets “career fair” presented cadets will hands-on, face-to-face career guidance and counseling from branch representatives across the nation. Several hundred tons of equipment, tanks, attack helicopters and armored vehicles were on display throughout Central Area, to include a functional tactical operations center. U.S. Army photo by Mike Strasser/USMA PAO

Sierpinski Pyramid - Fourth Iteration by th_squirrel

2 1

The fourth iteration of the Sierpinski Pyramid made from Duplos for a math project.

Oaks Estate 20181202 001 by Will E Clickit

3

Iterations by three.

Sinister lakes and bright archipelago by Anders Sandberg

Iterate of z_{n+1}=tanh(z_n)*exp(0.821*i)+0.1*z_n^2, colored by argument (hue) and magnitude (brightness).

2013 Branch Week_29 by West Point - The U.S. Military Academy

1

In its second iteration at the U.S. Military Academy, the Department of Military Instruction hosts Branch Week Sept. 9-14 at West Point, N.Y. With roughly 180 Army officers and non-commissioned officers, representing all 16 commissionable branches, the weeklong Corps of Cadets “career fair” presented cadets will hands-on, face-to-face career guidance and counseling from branch representatives across the nation. Several hundred tons of equipment, tanks, attack helicopters and armored vehicles were on display throughout Central Area, to include a functional tactical operations center. U.S. Army photo by Mike Strasser/USMA PAO

documenting new room/paintjob in the early morning light by Klara

2 4

Previous iterations: 2005, 2006, 2008.

Newton's Method 5th roots of 1, selected basins, ring orbit trap by Jonathan Lidbeck

{"fn":{"maxIter":50,"coefficients":[1,0,0,0,0,1],"palette":{"colors":["ff000000"],"brightness":0.9,"id":"HueCycle","saturation":1},"id":"Newton5","trapFunction":{"radius":0.95,"cx":0,"id":"RingFunction","color":"ffffff","cy":0,"thickness":0.05},"rootColors":["0","ff0033","0","0","3300ff"]},"range":{"ymin":-1.5,"xmax":2,"ymax":1.5,"xmin":-2}}

Catwoman by Raheem Nelson

5 6

The follow up painting to The Dark Knight. This is the Anne Hathaway version of Catwoman. The anatomy was the hardest thing about this painting and it went through several iterations over many different sittings. I had to measure the proportions very carefully to pull over a solid sketch. The costume hatching came from what I learned about painting Batman. I was going to leave her unblended but the rough brush strokes didn't work for her features like they did for the Batman painting. The background is more abstract than the photo reference. I think it helps her stand out more. The snow brought the subject and the background together. Created in ArtRage. about.me/raheemnelson

2013 Branch Week_22 by West Point - The U.S. Military Academy

In its second iteration at the U.S. Military Academy, the Department of Military Instruction hosts Branch Week Sept. 9-14 at West Point, N.Y. With roughly 180 Army officers and non-commissioned officers, representing all 16 commissionable branches, the weeklong Corps of Cadets “career fair” presented cadets will hands-on, face-to-face career guidance and counseling from branch representatives across the nation. Several hundred tons of equipment, tanks, attack helicopters and armored vehicles were on display throughout Central Area, to include a functional tactical operations center. U.S. Army photo by Mike Strasser/USMA PAO

iteration 08 by Elijah Porter

4

detail of back

2013 Branch Week by West Point - The U.S. Military Academy

In its second iteration at the U.S. Military Academy, the Department of Military Instruction hosts Branch Week Sept. 9-14 at West Point, N.Y. With roughly 180 Army officers and non-commissioned officers, representing all 16 commissionable branches, the weeklong Corps of Cadets “career fair” presented cadets will hands-on, face-to-face career guidance and counseling from branch representatives across the nation. Several hundred tons of equipment, tanks, attack helicopters and armored vehicles were on display throughout Central Area, to include a functional tactical operations center.

Iterations (charting progression) by Lazlo Woodbine

3

More tinkering with my knight. Think I've made his face worse, but his body and mane better. Think its time to stop...

3D view of Feb26wja1a by Kent Schimke

4 6

Fractal type:julia

Plot size (w,h):2500,2500

Maximum iterations:50000

Center Point (real, imaginary):1.05042e-07,-1.05042e-07 i

Plot Width (real):0.000175

Julia origin (real, imaginary):-0.4994282919320107,0.5208905679611714 i

Source mandelbrot width:3.75E-12

Color scheme name:YeloPupr

Commando Course Graduation by Fort Drum & 10th Mountain Division (LI)

The first iteration of the Light Fighters School Commando Course graduated from the program this week.

1972 Rover P5B by Steve Pickering

2

At the veterantræf, Græsted, North Zealand, Denmark, 4th June 2022.

"The final iteration of the P5 appeared in September 1967.[7] 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 Buick engine, making it considerably stronger. While this added some weight, it still maintained the engine's light and compact features. The Borg Warner Type-35 automatic transmission, hydrosteer variable ratio power steering and front Lucas fog lights were now standard.

Output of 160 metric horsepower (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 greater power of the engine, along with its lower weight, provided improved performance as well as fuel economy.

The exterior was mostly unchanged, apart from bold "3.5 Litre" badging, a pair of fog lights which were added below the headlights, creating a striking four-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.

1971 Rover P5B owned by Queen Elizabeth II

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. For that reason, registered relatively new-looking P5s were therefore still familiar sights in Westminster for more than a decade after production had ended.

When Margaret Thatcher entered Downing Street in 1979 after her election victory, she was driven in a 1972 model. It was during Thatcher's eleven-year tenure that the P5 was eventually phased out as a Prime-Ministerial car, in favour of the Jaguar XJ.

Queen Elizabeth II also owns an Arden Green Rover P5B Saloon "JGY 280", which is on display at the Heritage Motor Centre, Gaydon, Warwickshire and was seen in the 18 May 2003 episode of BBC motoring show, Top Gear."

source: Wikipedia

Raven - B Model - Mach 8-10 - Supersonic / Hypersonic Business Jet - Iteration 6 Integration Perspective by IO Aircraft

Raven - B Model - Mach 8-10 - Supersonic / Hypersonic Business Jet - Iteration 6 Integration Perspective

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

BlueEdge - Mach 8-10 Hypersonic Commercial Aircraft, 220 Passenger Hypersonic Commercial Plane - Imaginactive Media Release ICAO by IO Aircraft

-----------------------------

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.

Newton5RingOrbitTrap5iter by Jonathan Lidbeck

1 5

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

-----------------------------

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.

Raven - Model B Mach 8-10 - Supersonic / Hypersonic Business Jet - Iteration 6 by IO Aircraft

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

Fractalworks plot Feb27wma1h

-----------------------------

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.

Feb27wma1h by Kent Schimke

3 9

Fractal type:mandelbrot

Plot size (w,h):2210,2210

Maximum iterations:20000

Center Point (real, imaginary):-0.097248652543884,0.65024132722605 i

Plot Width (real):9.38E-12

Color scheme name:POP0

Raven - Model B Mach 8-10 - Supersonic / Hypersonic Business Jet - Iteration 6 by IO Aircraft

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

Fractalworks plot Mar24wja1g

-----------------------------

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.

2013 Branch Week_15 by West Point - The U.S. Military Academy

In its second iteration at the U.S. Military Academy, the Department of Military Instruction hosts Branch Week Sept. 9-14 at West Point, N.Y. With roughly 180 Army officers and non-commissioned officers, representing all 16 commissionable branches, the weeklong Corps of Cadets “career fair” presented cadets will hands-on, face-to-face career guidance and counseling from branch representatives across the nation. Several hundred tons of equipment, tanks, attack helicopters and armored vehicles were on display throughout Central Area, to include a functional tactical operations center. U.S. Army photo by Mike Strasser/USMA PAO

3D view of Mar24wja1j by Kent Schimke

1 1

Fractalworks plot Mar24wja1h

Fractalworks plot Mar24wja1i

Fractalworks plot Mar24wja1j

2013 Branch Week_20 by West Point - The U.S. Military Academy

In its second iteration at the U.S. Military Academy, the Department of Military Instruction hosts Branch Week Sept. 9-14 at West Point, N.Y. With roughly 180 Army officers and non-commissioned officers, representing all 16 commissionable branches, the weeklong Corps of Cadets “career fair” presented cadets will hands-on, face-to-face career guidance and counseling from branch representatives across the nation. Several hundred tons of equipment, tanks, attack helicopters and armored vehicles were on display throughout Central Area, to include a functional tactical operations center. U.S. Army photo by Mike Strasser/USMA PAO

Surly Cross Check v2.5 by Brian Biggs

4

This is yet another iteration of the CC. I didn't like the mtb bars, so I pulled the ones off the old blue three-speed and today picked up these Big Cheese grips at Elliot's request. She has good taste that one.

I just procured a studio in Center City, so I bought another Cross Check last week that I'll be building up to be this one's twin, but with On-One's Mungo bars and maybe higher gearing since I won't have the hills to deal with. This set-up really works for me.

VTOL - Hypersonic Plane - High Supersonic - Scramjet - IO Aircraft - Iteration 4 by IO Aircraft

1

VTOL - Hypersonic Plane - High Supersonic - Scramjet - IO Aircraft - Iteration 4

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

Drew Blair

70 Ton Payload, Single Stage to Orbit Fixed Wing Aircraft - Hypersonic Plane - Space Plane by IO Aircraft

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.

-------------

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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.

70 Ton Payload, Single Stage to Orbit Fixed Wing Aircraft - Hypersonic Plane - Space Plane

Earlier, pre Iteration 1, Just felt like posting this online, working out the physics/geometries/energy requirements and contruction.

Mach 8-10 in amtmosphere, 195ft long, Heavy Lift Single Stage To Orbit Fixed Wing Aircraft. 70 TONS, ie 140,000 LBS, 60 ft X 15ft X 15ft payload bay. Up in the Falcon Heavy and Delta IV class, except not $400 million to launch giant payloads into orbit, but below $250 per lbs, or about $28 million to launch giant payloads, and normalized orbital flight, as normal as a 737 commercial flight. Load up, refuel, take off in an afternoon. I estimate this aircraft would cost about $750 million each for space capable. In atmosphere commercial, roughly $300 million each for a 200 passenger M8-10 (not designed yet)

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Drew Blair