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The Space Test Program-Houston 6 (STP-H6) payload is inside the Space Station Processing Facility high bay at NASA’s Kennedy Space Center in Florida on March 19, 2019. It is being prepared for its move to the SpaceX facility where it will be will be stowed in the trunk of the Dragon spacecraft for delivery to the International Space Station on SpaceX’s 17th Commercial Resupply Services mission (CRS-17) for NASA. STP-H6 is an x-ray communication investigation that will be used to perform a space-based demonstration of a new technology for generating beams of modulated x-rays. This technology may be useful for providing efficient communication to deep space probes, or communicating with hypersonic vehicles where plasma sheaths prevent traditional radio communications. CRS-17 is scheduled to launch from Space Launch Complex 40 on Cape Canaveral Air Force Station in late April. Photo credit: NASA/Ben Smegelsky
The Rockwell (now part of Boeing) B-1 Lancer is a four-engine, variable-sweep wing strategic bomber used by the United States Air Force. First envisioned in the 1960s as a supersonic bomber with sufficient range and payload to replace the Boeing B-52 Stratofortress, it developed primarily into a low-level penetrator with long range and supersonic speed capability.
The bomber's development was delayed multiple times over its history, as the theory of strategic balance changed from flexible response to mutually assured destruction and back again. The initial B-1A version was developed in the early 1970s, but its production was canceled and only four prototypes were built. In 1980, the B-1 resurfaced as the B-1B version with the focus on low-level penetration bombing. The B-1B entered service with the United States Air Force (USAF) in 1986.
The B-1B began service with the USAF Strategic Air Command as a nuclear bomber. In the 1990s, it was converted to conventional bombing use. It was first used in combat during Operation Desert Fox in 1998 and during the NATO action in Kosovo the following year. The B-1B continues to support U.S. and NATO military in Afghanistan and Iraq. The Lancer is the supersonic component of the USAF's long-range bomber force, along with the subsonic B-52 and Northrop Grumman B-2 Spirit. The bomber is commonly called the "Bone" (originally from "B-One"). With the retirement of the General Dynamics/Grumman EF-111A Raven in 1998 and the Grumman F-14 Tomcat in 2006, the B-1B is the U.S. military's only active variable-sweep wing aircraft.
General characteristics
* Crew: 4 (aircraft commander, copilot, offensive systems officer and defensive systems officer)
* Payload: 125,000 lb (56,600 kg) ; internal and external ordnance combined
* Length: 146 ft (44.5 m)
* Wingspan:
o Extended: 137 ft (41.8 m)
o Swept: 79 ft (24.1 m)
* Height: 34 ft (10.4 m)
* Wing area: 1,950 ft² (181.2 m²)
* Airfoil: NA69-190-2
* Empty weight: 192,000 lb (87,100 kg)
* Loaded weight: 326,000 lb (148,000 kg)
* Max takeoff weight: 477,000 lb (216,400 kg)
* Powerplant: 4× General Electric F101-GE-102 augmented turbofans
o Dry thrust: 14,600 lbf (64.9 kN) each
o Thrust with afterburner: 30,780 lbf (136.92 kN) each
* Fuel capacity, optional: 10,000 U.S. gal (38,000 L) fuel tank for 1–3 internal weapons bays each
Performance
* Maximum speed:
o At altitude: Mach 1.25 (721 knots, 830 mph, 1,340 km/h at 50,000 ft/15,000 m altitude)
o At low level: Mach 0.92 (700 mph, 1,130 km/h at 200–500 ft/60-150 m altitude)
* Range: 6,478 nmi (7,456 mi, 11,998 km)
* Combat radius: 2,993 nmi (3,445 mi, 5,543 km)
* Service ceiling: 60,000 ft (18,000 m)
* Wing loading: 167 lb/ft² (816 kg/m²)
* Thrust/weight: 0.38
Armament
* Hardpoints: six external hardpoints for 50,000 lb (22,700 kg) of ordnance (use for weapons currently restricted by START I treaty) and 3 internal bomb bays for 75,000 lb (34,000 kg) of ordnance.
* Bombs:
o 84× Mk-82 AIR inflatable retarder general purpose bombs
o 81× Mk-82 low drag general purpose bombs
o 84× Mk-62 Quickstrike sea mines
o 24× Mk-65 naval mines
o 30× CBU-87/89/CBU-97 Cluster Bomb Units (CBU)[N 1]
o 30× CBU-103/104/105 Wind Corrected Munitions Dispenser
o 24× GBU-31 JDAM GPS guided bombs[N 2]
o 15× GBU-38 JDAM GPS guided bombs (Mk-82 general purpose warhead)[N 3]
o 24× Mk-84 general purpose bombs
o 12× AGM-154 Joint Standoff Weapon
o 96× or 144× GBU-39 Small Diameter Bomb GPS guided bombs[N 4] (not fielded on B-1 yet)
o 24× AGM-158 JASSM
o 24× B61 thermonuclear variable-yield gravity bombs (no longer carried)
o 24x B83 nuclear bomb (no longer carried)
Avionics
* 1× AN/APQ-164 forward-looking offensive passive phased-array radar
* 1× AN/ALQ-161 radar warning and defensive jamming equipment
* 1× AN/ASQ-184 defensive management system
* 1× Lockheed Martin Sniper XR targeting pod (optional)
Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, the hatch is closed for the upcoming flight of a Cygnus cargo vessel. The spacecraft is scheduled for the upcoming Orbital ATK Commercial Resupply Services-6 mission to deliver hardware and supplies to the International Space Station. The Cygnus is scheduled to lift off atop a United Launch Alliance Atlas V rocket on March 22.
Photo credit: NASA/Dimitrios Gerondidakis
Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, the hatch is closed for the upcoming flight of a Cygnus cargo vessel. The spacecraft is scheduled for the upcoming Orbital ATK Commercial Resupply Services-6 mission to deliver hardware and supplies to the International Space Station. The Cygnus is scheduled to lift off atop a United Launch Alliance Atlas V rocket on March 22.
Photo credit: NASA/Dimitrios Gerondidakis
Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, the hatch is closed for the upcoming flight of a Cygnus cargo vessel. The spacecraft is scheduled for the upcoming Orbital ATK Commercial Resupply Services-6 mission to deliver hardware and supplies to the International Space Station. The Cygnus is scheduled to lift off atop a United Launch Alliance Atlas V rocket on March 22.
Photo credit: NASA/Dimitrios Gerondidakis
PictionID:53758802 - Catalog:14_031721 - Title:GD/Astronautics Details: Nose Cone Fairing - Filename:14_031721.tif - Images from the Convair/General Dynamics Astronautics Atlas Negative Collection. The processing, cataloging and digitization of these images has been made possible by a generous National Historical Publications and Records grant from the National Archives and Records Administration---Please Tag these images so that the information can be permanently stored with the digital file.---Repository: San Diego Air and Space Museum
1. INTRODUCTION
EARLY LUNAR ACCESS (ELA) was a "cheaper-faster-better" manned lunar mission study, carried out by General Dynamics in 1992-93. It was intended as a joint US-European pathfinder for NASA's more capable 4-man First Lunar Outpost (FLO). The project tried to reduce total costs by a factor of ten compared with Apollo, by utilizing existing launch vehicles rather than developing a large Saturn V-class rocket. This would be feasible since modern electronics, rocket engines and materials are more capable and weigh less than their Apollo-era counterparts. Hence a modern manned lunar spacecraft need not be as heavy as the Apollo Lunar Module. General Dynamics also claimed that an ELA-type program would have major scientific merit. It would offer major improvements beyond what was accomplished with Apollo, since ELA would enable 2–3-week crew stays on the Moon. Politically, it would encourage cooperation between NASA and ESA (or other foreign space agencies) which would make it appealing to US politicians.
2. PROGRAM OBJECTIVES
To reach the main goals (low development cost and improved scientific return compared with Apollo), General Dynamics identified the following system and mission requirements.
Table 1 - System Requirements
- Maximize use of existing systems and subsystems or their derivatives
- Achieve first piloted lunar mission by 2000
- Provide capability for crew stay times for up to three weeks on the Moon
- Provide shirtsleeve environment for Intra-Vehicular Activity functions (telerobotic lunar rovers)
- Emplace permanent facilities that can support expansion to larger base operations
Table 2 - Mission Objectives
Lunar science:
- Characterize geology and physical properties
- Establish early astronomy outpost
- Demonstrate lunar oxygen processing pilot plant
Human Life Support Technologies:
- Assess effectiveness of EMU lunar spacesuits
- Evaluate crew capabilities for moderate (14-21 day) stay times
- Determine crew effectiveness during lunar night
Support of NASA's First Lunar Outpost:
- Survey and map potential landing sites
- Deploy navigation aids, communication links
- Determine effectiveness of telerobotic rovers
- Test materials & equipment exposed to long duration lunar environment
- Deploy critical supplies and equipment
3. SYSTEM ARCHITECTURE
Early Lunar Access would use the Space Shuttle and a large expendable launch vehicle such as the Ariane-5 or Titan IV. The former would carry a manned Lunar Exploration Vehicle spacecraft while the latter launches a wide-body Centaur G' rocket stage. Both payloads would rendezvous and dock in low Earth orbit. The Centaur then fires its engine to accelerate the complex toward the Moon and is then jettisoned.
Travel time to the Moon is about three days. To save fuel, the LEV makes a direct landing rather than enter an intermediate lunar parking orbit as Apollo did. The vehicle retains sufficient propellant to perform a later ascent burn to return the crew to Earth. For unmanned cargo missions, the LEV carries a heavier payload and uses up all its fuel for landing.
The launch vehicles (Shuttle plus Titan IV or Ariane-5) would have required some upgrades. The Shuttle would have needed either a lightweight Al-Li External Tank or Advanced Solid Rocket Motors to carry 25,720kg payloads to a 300km orbit. The new ET is now available but the ASRMs were cancelled in 1994. The ELVs would have been uprated to carry a 27t payload into Earth orbit. Proposed modifications included new aluminum-lithium tanks for the Titan IV plus a pair of additional solid rocket boosters for the Ariane-5.
The Centaur G' would have been modified for missions lasting up to ten days rather than a few hours. A single uprated RL-10 engine (since developed for the Delta III project) would have replaced the previous twin-engine configuration to save weight and improve reliability. The propellant tanks would have been enlarged and additional thermal insulation, power and reaction control propellant would have increased the in-orbit lifetime.
The crew capsule would be derived from the Apollo Command Module that last flew in 1975. It retains the external size and shape of the original Apollo CM design to take advantage of the existing aero- and thermodynamic databases developed during that program. The interior has however been scaled down since it only supports a crew of two instead of three, and the capsule is lighter since its design is based on modern materials, lightweight electronics and construction methods.
The lunar habitat (where the crew would live during their 21-day stay) would also be derived from previously developed hardware; in this case the Space Station Freedom mini-pressurized logistics module built by Italy's Alenia Spazio for NASA. The MPLM was later replaced with a larger module that presumably would be too heavy for Early Lunar Access. However, a scaled down version could still be taken from ESA's Ariane Transfer Vehicle which utilizes the same basic Alenia-built module.
Entirely new systems include a multiple payload adapter plus lunar science equipment and surface elements carried on the first unmanned ELA mission. The major new element is the Lunar Transfer Vehicle itself. It features an advanced high performance four-engine liquid oxygen/hydrogen propulsion system that throttles to enable soft landings on the Moon. The engines would be based on the RS-44 or similar systems. Redundancy is achieved through the capability to shut down a diametrically opposed pair in the event of a failure.
The payload mass exceeds the Shuttle's landing limits in the event of an abort, so a mechanism that dumps the LEV propellant in case of emergency would have to be incorporated. NASA safety requirements probably require that the propellants be carried outside the Shuttle cargo bay during ascent as well. Fortunately, Boeing has studied a system that would transfer excess propellant from the Shuttle External Tank in orbit.
4. SPACE OPERATIONS
Lunar missions using low Earth Orbit Rendezvous (EOR) are constrained by critical launch window opportunities. The LEV is deployed and checked one day after the Shuttle reaches orbit. If there is a problem that cannot be fixed in orbit, the LEV and its 2-crew is retrieved and returned to Earth with the Shuttle. Under normal conditions, however, the expendable launch vehicle would then place the Centaur rocket stage in a co-orbit with the Shuttle. The LEV and Centaur then dock (possibly assisted by the Shuttle) and depart from low Earth orbit a day later, when the launch window opens.
If the LEV/Centaur fails to depart on time (the launch window is in the order of one minute), there will be another translunar injection opportunity on the next orbit 90 minutes later. The Moon, however, will no longer be at the same point as the spacecraft when it is time to land three days later. A midcourse correction will be required to "catch up" with it. Consequently, the LEV would carry an additional 2% propellant for unplanned midcourse plane change maneuvers. This will provide a total delta-V or velocity change capability of 205 meters per second, sufficient for 13 lunar departure opportunities over 18 hours. In contrast, Apollo only had about four translunar injection opportunities, but of course there was Earth orbit rendezvous requirement. If the departure window is missed completely, there will be another series of 13 departure opportunities 3-11 days later. The Shuttle, Centaur and LEV can wait up to a week in Earth orbit so there would typically be two translunar injection opportunities per mission.
5. PROGRAMMATICS SUMMARY
EARLY LUNAR ACCESS MANIFEST EXAMPLE (Lunar Missions 1 through 4 (Cryogenic LEV)):
Mission 1: Initial Science & Exploration
Mission 2: Habitation System Deployment
Mission 3: First Crew Landing
Mission 4: Expanded Science & Exploration
Mission 1 is primarily science oriented and would offer immediate returns (geophysics, ultraviolet & optical telescopes) after the first landing. Mission 2 lands the habitat module, an environmental control & life-support system (ECLSS), fuel cells and other equipment. The first crewed mission then occurs with Mission 3. The total cost at this point would be $13 billion (1992 rates) over seven years for a "business as usual" all-NASA program. This figure includes all costs (research & development, launch, production, operations, testing) apart from the scientific payloads associated with the missions. European cooperation (where ESA would provide three Ariane-5 launchers, the habitation module and participate in some development & production work on the LEV/crew capsule) would reduce this figure by about $4 billion. A "cheaper faster better" approach would reduce the US share further, to $6 billion and total program costs to $10 billion. The marginal cost of continuing the program after this would be $2 billion per mission. The fourth expedition (not rigorously investigated by General Dynamics) would land additional equipment, supplies and spares for an additional 2-3 piloted missions to the same site.
If it had been approved, the ELA project would have started in 1994 with a number of 1-year hardware definition studies. Hardware development would have started in 1995, leading to a first unmanned landing in mid-1999. General Dynamics assumed that at most two Shuttles and two expendable launchers would be available per year. Mission 2 would take place six months later, followed by the first manned landing six months after that. Early Lunar Access would then have given way to NASA's advanced First Lunar Outpost (FLO) program in 2002.
6. POSTSCRIPT
In some ways, Early Lunar Access was ahead of its time both technically and politically. The political basis quickly evaporated when the Clinton Administration ordered yet another Space Station redesign only months after General Dynamics unveiled the project in early 1993. The International Space Station and Shuttle has commanded virtually all of NASA's shrinking manned spaceflight budget ever since. Technically, ELA also ran into problems when NASA subsequently discovered that General Dynamics had underestimated the weight of the Lunar Exploration Vehicle. Had the project been approved, it would have required further costly upgrades to the Shuttle (=Advanced Solid Rocket Motors in addition to the currently approved super-lightweight External Tank) and Titan IV (=stretched aluminum-lithium propellant tanks).
The design philosophy behind Early Lunar Access appears solid, however. The major space powers (USA, Russia, ESA, Japan) continue to uprate their expendable rockets while new vehicles are on the drawing board. For example, the US Delta IV and Russian Angara boosters will soon provide the required lifting capability without any modifications. Spacecraft electronics keep getting cheaper and more capable while propulsion and materials advantages will make it possible to launch heavier payloads on smaller vehicles. This trend has continued for decades, and the major design driver today is economic in nature -- not political. Someday it will be possible to assemble a manned lunar spacecraft entirely from existing off-the-shelf "building blocks" already developed for the Space Station and commercial satellite programs. If Early Lunar Access was not technically feasible in 1994, it certainly will be in 2004 or 2014.”
The above, along with additional excellent graphics & tables at/from:
www.google.com/url?sa=i&url=https://forum.nasaspacefl...
Credit: “NASA Spaceflight Forum” website (although formatting suggests its source to be the “PMView Pro” website, ¯\_(ツ)_/¯)
Also, another excellent article, along with the image (featured as the cover for the January 18, 1993 of Aviation Week & Space Technology magazine) at/from:
www.thespacereview.com/article/4511/1
Credit: “The Space Review” website
Understandably, plenty of other rehashed ELA references/articles abound online.
Whatever…it’s all water under the bridge. Bottom Line: Another gorgeous work by Roy Gjertson for General Dynamics. This is the first/only high-resolution version of this I've ever seen, and it's now online...at 1200 dpi.
You're welcome. 😏
The unmanned aerial vehicle dropped an autonomous payload... a Pelican Case with a servo controlled parachute, guided by GPS and accelerometers. Total cost of the autonomous payload was about $500 in parts.
The payload was dropped from 10,000 feet, and was only off by a matter of feet.
Academic paper here:
Discovery STO - Single Stage to Orbit Heavy Lift, Hypersonic Aircraft - 70 TON Payload - IO Aircraft
IO Aircraft: www.ioaircraft.com
Discovery STO Specs
Length:197' 6" / Span: 93' / Palyload Bay: 61' L X 15" W X 15' H / Span: 70 Ton (140,000 LBS)
Engines: U-TBCC (Unified Turbined Based Combined Cycle) Inc/Zero Atmosphere
Inlets: Adaptive REST, Originally Hapb/Larc NASA
Fuel: 125,000 Gallons 12,000 PSI H2 / 90,000 Gallons 12,000 PSI O2
Fuel Weight: Apx 72,000 LBS Total / *If liquid, would be 1.4 Million LBS
Weight: Apx 325,000 LBS EOW/Dry Weight / Apx 537,000 T/O Weight, Max Payload
Airframe: 75+% Proprietary Advanced Composites, 400,000 PSI Tensile Strength Airframe / *NO Ceramic Tiles
Thermals: 6,000F Thermal Resistance
Estimated Cost: $750 Million Each (Fly Away Price)
Estimated Launch Cost: Apx $28 Million at 140,000 LBS, Including Maintenance Costs / Under $250 per pound at Maximum Paylaod Wieght *Could Drop to Below $50 per LBS
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Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
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Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
The N-1 was a heavy lift rocket intended to deliver payloads beyond low Earth orbit, acting as the Soviet counterpart to the NASA Saturn V rocket. This heavy lift booster had the capability of lifting very heavy loads into orbit, designed with manned extra-orbital travel in mind. Its first stage is the most powerful rocket stage ever built.
The N1-L3 version was developed to compete with the United States Apollo Saturn V to land a man on the Moon.
N1-L3 was under-funded and under-tested, and started development in October 1965, almost four years after the Saturn V. The project was badly derailed by the death of its chief designer Sergei Korolev in 1966. After four failed launch attempts, the program was suspended in 1974, and in 1976 was officially cancelled.
This is a Block A of the first stage.
NK-15 engine is equipped with 30 units.
The payload fairing halves for Orbital ATK's Pegasus XL rocket are staged inside Building 1555 at Vandenberg Air Force Base in California on Aug. 23, 2017. The Pegasus rocket is being prepared for NASA's Ionospheric Connection Explorer (ICON) mission. The explorer will launch on June 15, 2018, from Kwajalein Atoll in the Marshall Islands (June 14 in the continental United States) on the Pegasus XL, which is attached to the company's L-1011 Stargazer aircraft. ICON will study the frontier of space - the dynamic zone high in Earth's atmosphere where terrestrial weather from below meets space weather above. The explorer will help determine the physics of Earth's space environment and pave the way for mitigating its effects on our technology and communications systems.. Photo credit: Randy Beaudoin
Orbital ATK technicians remove the first half of the payload fairing for the Orbital ATK Pegasus XL rocket from its shipping container Aug. 4, 2017, at Vandenberg Air Force Base in California. The Pegasus rocket is being prepared for NASA's Ionospheric Connection Explorer, or ICON, mission. The explorer will launch on June 15, 2018, from Kwajalein Atoll in the Marshall Islands (June 14 in the continental United States) on Orbital ATK's Pegasus XL rocket, which is attached to the company's L-1011 Stargazer aircraft. ICON will study the frontier of space - the dynamic zone high in Earth's atmosphere where terrestrial weather from below meets space weather above. The explorer will help determine the physics of Earth's space environment and pave the way for mitigating its effects on our technology, communications systems and society. Photo credit: Randy Beaudoin
The Space Test Program-Houston 6 (STP-H6) payload is inside the Space Station Processing Facility high bay at NASA’s Kennedy Space Center in Florida on March 19, 2019. It is being prepared for its move to the SpaceX facility where it will be will be stowed in the trunk of the Dragon spacecraft for delivery to the International Space Station on SpaceX’s 17th Commercial Resupply Services mission (CRS-17) for NASA. STP-H6 is an x-ray communication investigation that will be used to perform a space-based demonstration of a new technology for generating beams of modulated x-rays. This technology may be useful for providing efficient communication to deep space probes, or communicating with hypersonic vehicles where plasma sheaths prevent traditional radio communications. CRS-17 is scheduled to launch from Space Launch Complex 40 on Cape Canaveral Air Force Station in late April. Photo credit: NASA/Ben Smegelsky
This 1 million-cubic-foot (28,300-cubic-meter) scientific balloon carried the TinMan (Thermal Neutron Measurement Experiment) payload to just over 120,000 feet (36,500 meters) from NASA’s Columbia Scientific Balloon Facility in Fort Sumner, New Mexico, on August 21, 2024.
Credit: NASA/Sophia Roberts
Alt text: Photo of a large balloon being inflated.
Descriptive text: In this photograph, a large semi-transparent balloon is inflated against a flat desert landscape. A long tubular arm extends toward the ground from the left side of the balloon. The sky, which has a faint smattering of clouds, takes up two thirds of the photograph. The bottom third shows the desert in the distance and a large swath of concrete in the foreground. People and trucks are scattered around the balloon. The whole image has a brown tint, like an old photograph.
NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission.
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Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, the hatch is closed for the upcoming flight of a Cygnus cargo vessel. The spacecraft is scheduled for the upcoming Orbital ATK Commercial Resupply Services-6 mission to deliver hardware and supplies to the International Space Station. The Cygnus is scheduled to lift off atop a United Launch Alliance Atlas V rocket on March 22.
Photo credit: NASA/Dimitrios Gerondidakis
The Atlas payload fairing enclosing NASA's Magnetospheric Multiscale observatories (MMS) is attached to a lifting device for its hoist into the Vertical Integration Facility on Space Launch Complex 41 on Cape Canaveral Air Force Station in Florida. MMS, led by a team from NASA's Goddard Space Flight Center, consists of four identical spacecraft that will work together to provide the first three-dimensional view of magnetic reconnection, a fundamental process which occurs throughout the universe. Launch aboard a United Launch Alliance Atlas V rocket is set for March 12. To learn more about MMS, visit www.nasa.gov/mms. Photo credit: NASA/Dimitri Gerondidakis
In a clean room at the Astrotech Space Operations facility in Titusville, Florida, workers verify that an Atlas payload fairing securely encloses NASA's Magnetospheric Multiscale observatories (MMS) for launch. MMS, led by a team from the Goddard Space Flight Center, consists of four identical spacecraft that will work together to provide the first three-dimensional view of magnetic reconnection, a fundamental process which occurs throughout the universe. Launch aboard a United Launch Alliance Atlas V rocket from Space Launch Complex 41 on Cape Canaveral Air Force Station is targeted for March 12. To learn more about MMS, visit www.nasa.gov/mms. Photo credit: NASA/Kim Shiflett
The payload fairing for Orbital ATK's Pegasus XL rocket arrives by flatbed truck Aug. 4, 2017, at Vandenberg Air Force Base in California. The Pegasus rocket is being prepared for NASA's Ionospheric Connection Explorer, or ICON, mission. The explorer will launch on June 15, 2018, from Kwajalein Atoll in the Marshall Islands (June 14 in the continental United States) on Orbital ATK's Pegasus XL rocket, which is attached to the company's L-1011 Stargazer aircraft. ICON will study the frontier of space - the dynamic zone high in Earth's atmosphere where terrestrial weather from below meets space weather above. The explorer will help determine the physics of Earth's space environment and pave the way for mitigating its effects on our technology, communications systems and society. Photo credit: Randy Beaudoin
The payload fairing for an Orbital ATK Pegasus XL rocket is inspected in Building 1555 at Vandenberg Air Force Base in California.
The fairing will protect NASA's Cyclone Global Navigation Satellite System (CYGNSS) spacecraft during launch. The rocket and spacecraft are being prepared at Vandenberg, then will be attached to the Orbital ATK L-1011 carrier aircraft and transported to NASA's Kennedy Space Center in Florida. CYGNSS will launch on the Pegasus XL rocket from the Skid Strip at Cape Canaveral Air Force Station. CYGNSS will make frequent and accurate measurements of ocean surface winds throughout the life cycle of tropical storms and hurricanes. The data that CYGNSS provides will enable scientists to probe key air-sea interaction processes that take place near the core of storms, which are rapidly changing and play a critical role in the beginning and intensification of hurricanes.
Photo credit: NASA/Randy Beaudoin
Dr. Kristen John, principal investigator for Hermes at NASA’s Johnson Space Center in Houston, talks to NASA Social participants during a What’s On Board science briefing at the agency’s Kennedy Space Center in Florida on April 29, 2019. The briefing was held for SpaceX’s 17th Commercial Resupply Services (CRS-17) mission to the International Space Station. John presented on the Hermes Facility, an experimental microgravity facility that enables science experiments, microgravity exposure testing, testing of engineering components and CubeSats and any payloads that can fit in the Hermes design and operations constraints. NASA’s Orbiting Carbon Observatory-3 (OCO-3) and Space Test Program-Houston 6 (STP-H6) are two of the experiments that also will be delivered to the space station on CRS-17. The SpaceX Falcon 9 rocket and Dragon cargo module are scheduled to launch no earlier than May 3, 2019, from Space Launch Complex 40 on Cape Canaveral Air Force Station in Florida. Photo credit: NASA/Kim Shiflett
The payload fairing containing the Orbital ATK Cygnus pressurized cargo module is lifted by crane at the United Launch Alliance (ULA) Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The payload will be hoisted up and mated to the ULA Atlas V rocket. The Orbital ATK CRS-7 commercial resupply services mission to the International Space Station is scheduled to launch atop the Atlas V from pad 41. Cygnus will deliver 7,600 pounds of supplies, equipment and scientific research materials to the space station. Photo credit: United Launch Alliance
(07/10/1997) --- KENNEDY SPACE CENTER, Fla. -- The payload canister containing the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) payload for the STS-85 mission is hoisted to the Payload Changeout Room (PCR) at Launch Pad 39A. Also in the canister are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) payloads. All three will be transferred from the PCR into the payload bay of the Space Shuttle Orbiter Discovery after the space vehicle arrives at the pad. The CRISTA is a system of three telescopes and four spectrometers to measure infrared radiation emitted by the Earth’s middle atmosphere. During the 11-day mission, the CRISTA-SPAS-2 free-flying satellite will be deployed from Discovery and retrieved later in the flight. Also onboard the satellite will be the Middle Atmosphere High Resolution Spectrograph Investigation (MAHRSI) to measure ultraviolet radiation emitted and scattered by the Earth’s atmosphere. The TAS-1 holds seven separate experiments that will provide data on the Earth’s topography and atmosphere, study the sun’s energy, and test new thermal control devices, as well as several student-developed experiments. The IEH-2 experiments will study ultraviolet radiation from stars, the sun and in the solar system
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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www.ioaircraft.com/hypersonic/ranger.php
Drew Blair
www.linkedin.com/in/drew-b-25485312/
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Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
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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.
The scientific balloon carrying the Salter Test Flight payload lifts off from NASA’s Columbia Scientific Balloon Facility’s location in Fort Sumner, New Mexico, on August 22, 2024.
Credit: NASA/Jeanette Kazmierczak
Alt text: Photo of a large balloon lifting off from the ground.
Descriptive text: An enormous scientific balloon is lifting off from the ground into a clear blue sky in this photograph. The balloon is white, slightly transparent, and ribbed vertically. It ripples as it rises and has an indent on the side facing the camera. On the ground, to the left, is a truck carrying long metal cylinders. To the right is a crane. A long white carpet stretches between them. Windmills are barely visible along the horizon.
NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission.
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CN's investment in building the New Richmond Autoport seems to be paying off with carloads of new autos arriving every day, often outnumbering the cars of Twin Cities bound interchange freight. It can be tough to make out the makes and models before they hit the pavement on the other side of town but as L517 paused for a meet with L516 careful study can reveal clues. In this case a cherry red tailgate with a Silverado badge indicates a batch of full-size GM trucks. There have been quite a variety of vehicles unloaded but GM trucks are likely the most common cargo. July 20, 2023.
Presentations on the ExoMars payload by Daniil Rodionov (ACS, FREND) IKI Moscow, Manish Patel (NOMAD) Uni Padua, and Gabriele Cremonese, Co-PI for CASSIS, Astronomical Observatory, Padua. Images credit: ESA/R. Palmari
Orbital ATK technicians remove the second half of the payload fairing for the Orbital ATK Pegasus XL rocket from its shipping container Aug. 4, 2017, at Vandenberg Air Force Base in California. The Pegasus rocket is being prepared for NASA's Ionospheric Connection Explorer, or ICON, mission. The explorer will launch on June 15, 2018, from Kwajalein Atoll in the Marshall Islands (June 14 in the continental United States) on Orbital ATK's Pegasus XL rocket, which is attached to the company's L-1011 Stargazer aircraft. ICON will study the frontier of space - the dynamic zone high in Earth's atmosphere where terrestrial weather from below meets space weather above. The explorer will help determine the physics of Earth's space environment and pave the way for mitigating its effects on our technology, communications systems and society. Photo credit: Randy Beaudoin
Inside a clean room in Building 1555 at Vandenberg Air Force Base in California, technicians install the first half of the Northrop Grumman Pegasus XL payload fairing around NASA's Ionospheric Connection Explorer (ICON) on Oct. 4, 2018. ICON is being prepared for its launch on the Pegasus XL, which is attached to the company's L-1011 Stargazer aircraft, from the Skid Strip at Cape Canaveral Air Force Station in Florida. Launch is scheduled for Oct. 26. ICON will study the frontier of space - the dynamic zone high in Earth's atmosphere where terrestrial weather from below meets space weather above. The explorer will help determine the physics of Earth's space environment and pave the way for mitigating its effects on our technology, communications systems and society. Photo credit: NASA/Dan Quinajon
Commer Raider 1.5 Ton chassis and a 2 Ton payload from 1934 CRF 836
Seen at the 2023 Kettering Vintage Rally and Steam Fayre
The payload fairing containing NOAA’s GOES-T satellite, secured on a transporter, arrives at the United Launch Alliance (ULA) Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The fairing-encapsulated GOES-T spacecraft was mated with the launch vehicle on Feb. 17, 2022.
GOES-T is slated for launch on March 1, 2022.
Photo credit: United Launch Alliance
The payload fairing containing NOAA's Geostationary Operational Environmental Satellite-S (GOES-S) is lowered by crane onto the United Launch Alliance (ULA) Atlas V rocket in the ULA Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The fairing will be secured to the rocket in preparation for launch. GOES-S is the second in a series of four advanced geostationary weather satellites. The satellite is slated to launch aboard the ULA Atlas V on March 1. Photo credit: NASA/Glenn Benson
The payload fairing containing the Orbital ATK Cygnus pressurized cargo module is lifted by crane at the United Launch Alliance (ULA) Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The payload will be hoisted up and mated to the ULA Atlas V rocket. The Orbital ATK CRS-7 commercial resupply services mission to the International Space Station is scheduled to launch atop the Atlas V from pad 41. Cygnus will deliver 7,600 pounds of supplies, equipment and scientific research materials to the space station. Photo credit: United Launch Alliance
Encapsulated inside its payload fairing, the Cygnus spacecraft for the upcoming Orbital ATK Commercial Resupply Services-6 mission departs the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida. Mounted atop a KAMAG transporter, Cygnus is being moved to Space Launch Complex-41 at Cape Canaveral Air Force Station where it will be mounted atop a United Launch Alliance Atlas V rocket. The Cygnus is scheduled to lift off atop a United Launch Alliance Atlas V rocket on March 22 to deliver hardware and supplies to the International Space Station.
Photo credit: NASA/Dimitrios Gerondidakis
New Iteration - Grey Hawk - Mach 8-10 - 7th / 8th Gen Hypersonic Super Fighter Aircraft, IO Aircraft www.ioaircraft.com
New peek, very little is posted or public. Grey Hawk - Mach 8-10 Hypersonic 7th/8th Gen Super Fighter. This is not a graphics design, but ready to be built this moment. Heavy CFD, Design Work, Systems, etc.
All technologies developed and refined. Can out maneuver an F22 or SU-35 all day long subsonically, and no missile on earth could catch it. Lots of details omitted intentionally, but even internal payload capacity is double the F-22 Raptor. - www.ioaircraft.com/hypersonic.php
Length: 60'
Span: 30'
Engines: 2 U-TBCC (Unified Turbine Based Combined Cycle)
2 360° Thrust Vectoring Center Turbines
Fuel: Kero / Hydrogen
Payload: Up to 4 2,000 LBS JDAM's Internally
Up to 6 2,000 LBS JDAM's Externally
Range: 5,000nm + Aerial Refueling Capable
www.ioaircraft.com/hypersonic.php
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Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
-------------
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.
Encapsulated inside its payload fairing, the Cygnus spacecraft for the upcoming Orbital ATK Commercial Resupply Services-6 mission departs the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida. Mounted atop a KAMAG transporter, Cygnus is being moved to Space Launch Complex-41 at Cape Canaveral Air Force Station where it will be mounted atop a United Launch Alliance Atlas V rocket. The Cygnus is scheduled to lift off atop a United Launch Alliance Atlas V rocket on March 22 to deliver hardware and supplies to the International Space Station.
Photo credit: NASA/Dimitrios Gerondidakis
STS-85 Payload Specialist Bjarni V. Tryggvason is assisted with his ascent/reentry flight suit by white room closeout crew members Jack Burritt and Carlos Gillis at Launch Pad 39A before he enters the crew cabin of the Space Shuttle orbiter Discovery
The payload fairing containing NOAA's Geostationary Operational Environmental Satellite-S (GOES-S) was lifted up by crane and moved into the United Launch Alliance (ULA) Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The fairing was mated to the ULA Atlas V rocket on February 16, 2018.
GOES-S is slated for launch on March 1.
Additional Launch Info: goo.gl/RMBbHU
Photo credit: NASA/Glenn Benson
The two halves of the payload fairing are fully closed around the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA's Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November. Photo credit: NASA/Kim Shiflett
Encapsulated inside its payload fairing, the Cygnus spacecraft for the upcoming Orbital ATK Commercial Resupply Services-6 mission departs the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida. Mounted atop a KAMAG transporter, Cygnus is being moved to Space Launch Complex-41 at Cape Canaveral Air Force Station where it will be mounted atop a United Launch Alliance Atlas V rocket. The Cygnus is scheduled to lift off atop a United Launch Alliance Atlas V rocket on March 22 to deliver hardware and supplies to the International Space Station.
Photo credit: NASA/Dimitrios Gerondidakis
Encapsulated inside its payload fairing, the Cygnus spacecraft for the upcoming Orbital ATK Commercial Resupply Services-6 mission departs the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida. Mounted atop a KAMAG transporter, Cygnus is being moved to Space Launch Complex-41 at Cape Canaveral Air Force Station where it will be mounted atop a United Launch Alliance Atlas V rocket. The Cygnus is scheduled to lift off atop a United Launch Alliance Atlas V rocket on March 22 to deliver hardware and supplies to the International Space Station.
Photo credit: NASA/Dimitrios Gerondidakis
A Hough Payloader Airport Tractor working hard at the Airport.
Taken at Melbourne Airport, Victoria in 2016.
NSROC technician Mark Freese and Launcher Engineer Jarod Atkins helping load the first payload on the transport trailer.
Credit: NASA
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A NASA-funded sounding rocket mission will launch from an atoll in the Pacific this spring. The mission will help scientists better understand and predict the electrical storms in Earth's upper atmosphere that can negatively affect satellite communication and global positioning signals.
The mission, called EVEX, for the Equatorial Vortex Experiment, will launch into a crucial layer of charged particles surrounding our planet. Called the ionosphere, this layer serves as the medium through which high frequency radio waves – such as those sent down to the ground by global positioning system (GPS) satellites or, indeed, any satellite communicating with Earth – travel. The ionosphere begins about 60 miles above the ground and is filled with electrons and ions, alongside the more familiar extension of our electrically neutral atmosphere. Governed by Earth’s magnetic field, high-altitude winds, and incoming material and energy from the sun, the ionosphere can be calm in certain places or times of day, and quite turbulent at others.
EVEX will launch two rockets for a twelve-minute journey through the equatorial ionosphere above the South Pacific. This area of the ionosphere is known for calm days and tempestuous evenings, times when the ionosphere becomes rippled like a funhouse mirror, disturbing radio signals, and introducing GPS errors of a half mile or more. The two rockets will measure events in two separate regions of the ionosphere to see how they work together to drive the ionosphere from placid and smooth to violently disturbed. Such information could ultimately lead to the ability to accurately forecast this important aspect of space weather.
The launch window for EVEX is from April 27 to May 10. The team will decide when to fly based on conditions in the ionosphere on any given night.
Read more at www.nasa.gov/mission_pages/sounding-rockets/news/evex.html
NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission.
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Inside a clean room in Building 1555 at Vandenberg Air Force Base in California, technicians install the first half of the Northrop Grumman Pegasus XL payload fairing around NASA's Ionospheric Connection Explorer (ICON) on Oct. 4, 2018. ICON is being prepared for its launch on the Pegasus XL, which is attached to the company's L-1011 Stargazer aircraft, from the Skid Strip at Cape Canaveral Air Force Station in Florida. Launch is scheduled for Oct. 26. ICON will study the frontier of space - the dynamic zone high in Earth's atmosphere where terrestrial weather from below meets space weather above. The explorer will help determine the physics of Earth's space environment and pave the way for mitigating its effects on our technology, communications systems and society. Photo credit: NASA/Dan Quinajon
Grey Hawk - Mach 8-10 - 7th / 8th Gen Hypersonic Super Fighter Aircraft, IO Aircraft www.ioaircraft.com
New peek, very little is posted or public. Grey Hawk - Mach 8-10 Hypersonic 7th/8th Gen Super Fighter. This is not a graphics design, but ready to be built this moment. Heavy CFD, Design Work, Systems, etc.
All technologies developed and refined. Can out maneuver an F22 or SU-35 all day long subsonically, and no missile on earth could catch it. Lots of details omitted intentionally, but even internal payload capacity is double the F-22 Raptor. - www.ioaircraft.com/hypersonic.php
Length: 60'
Span: 30'
Engines: 2 U-TBCC (Unified Turbine Based Combined Cycle)
2 360° Thrust Vectoring Center Turbines
Fuel: Kero / Hydrogen
Payload: Up to 4 2,000 LBS JDAM's Internally
Up to 6 2,000 LBS JDAM's Externally
Range: 5,000nm + Aerial Refueling Capable
www.ioaircraft.com/hypersonic.php
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Unified Turbine Based Combined Cycle. Current technologies and what Lockheed is trying to force on the Dept of Defense, for that low speed Mach 5 plane DOD gave them $1 billion to build and would disintegrate above Mach 5, is TBCC. 2 separate propulsion systems in the same airframe, which requires TWICE the airframe space to use.
Unified Turbine Based Combined Cycle is 1 propulsion system cutting that airframe deficit in half, and also able to operate above Mach 10 up to Mach 15 in atmosphere, and a simple nozzle modification allows for outside atmosphere rocket mode, ie orbital capable.
Additionally, Reaction Engines maximum air breather mode is Mach 4.5, above that it will explode in flight from internal pressures are too high to operate. Thus, must switch to non air breather rocket mode to operate in atmosphere in hypersonic velocities. Which as a result, makes it not feasible for anything practical. It also takes an immense amount of fuel to function.
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Advanced Additive Manufacturing for Hypersonic Aircraft
Utilizing new methods of fabrication and construction, make it possible to use additive manufacturing, dramatically reducing the time and costs of producing hypersonic platforms from missiles, aircraft, and space capable craft. Instead of aircraft being produced in piece, then bolted together; small platforms can be produced as a single unit and large platforms can be produces in large section and mated without bolting. These techniques include using exotic materials and advanced assembly processes, with an end result of streamlining the production costs and time for hypersonic aircraft; reducing months of assembly to weeks. Overall, this process greatly reduced the cost for producing hypersonic platforms. Even to such an extent that a Hellfire missile costs apx $100,000 but by utilizing our technologies, replacing it with a Mach 8-10 hypersonic missile of our physics/engineering and that missile would cost roughly $75,000 each delivered.
Materials used for these manufacturing processes are not disclosed, but overall, provides a foundation for extremely high stresses and thermodynamics, ideal for hypersonic platforms. This specific methodology and materials applications is many decades ahead of all known programs. Even to the extend of normalized space flight and re-entry, without concern of thermodynamic failure.
*Note, most entities that are experimenting with additive manufacturing for hypersonic aircraft, this makes it mainstream and standardized processes, which also applies for mass production.
What would normally be measured in years and perhaps a decade to go from drawing board to test flights, is reduced to singular months and ready for production within a year maximum.
Unified Turbine Based Combined Cycle (U-TBCC)
To date, the closest that NASA and industry have achieved for turbine based aircraft to fly at hypersonic velocities is by mounting a turbine into an aircraft and sharing the inlet with a scramjet or rocket based motor. Reaction Engines Sabre is not able to achieve hypersonic velocities and can only transition into a non air breathing rocket for beyond Mach 4.5
However, utilizing Unified Turbine Based Combine Cycle also known as U-TBCC, the two separate platforms are able to share a common inlet and the dual mode ramjet/scramjet is contained within the engine itself, which allows for a much smaller airframe footprint, thus engingeers are able to then design much higher performance aerial platforms for hypersonic flight, including the ability for constructing true single stage to orbit aircraft by utilizing a modification/version that allows for transition to outside atmosphere propulsion without any other propulsion platforms within the aircraft. By transitioning and developing aircraft to use Unified Turbine Based Combined Cycle, this propulsion system opens up new options to replace that airframe deficit for increased fuel capacity and/or payload.
Enhanced Dynamic Cavitation
Dramatically Increasing the efficiency of fuel air mixture for combustion processes at hypersonic velocities within scramjet propulsion platforms. The aspects of these processes are non disclosable.
Dynamic Scramjet Ignition Processes
For optimal scramjet ignition, a process known as Self Start is sought after, but in many cases if the platform becomes out of attitude, the scramjet will ignite. We have already solved this problem which as a result, a scramjet propulsion system can ignite at lower velocities, high velocities, at optimal attitude or not optimal attitude. It doesn't matter, it will ignite anyways at the proper point for maximum thrust capabilities at hypersonic velocities.
Hydrogen vs Kerosene Fuel Sources
Kerosene is an easy fuel to work with, and most western nations developing scramjet platforms use Kerosene for that fact. However, while kerosene has better thermal properties then Hydrogen, Hydrogen is a far superior fuel source in scramjet propulsion flight, do it having a much higher efficiency capability. Because of this aspect, in conjunction with our developments, it allows for a MUCH increased fuel to air mixture, combustion, thrust; and ability for higher speeds; instead of very low hypersonic velocities in the Mach 5-6 range. Instead, Mach 8-10 range, while we have begun developing hypersonic capabilities to exceed 15 in atmosphere within less then 5 years.
Conforming High Pressure Tank Technology for CNG and H2.
As most know in hypersonics, Hydrogen is a superior fuel source, but due to the storage abilities, can only be stored in cylinders thus much less fuel supply. Not anymore, we developed conforming high pressure storage technology for use in aerospace, automotive sectors, maritime, etc; which means any overall shape required for 8,000+ PSI CNG or Hydrogen. For hypersonic platforms, this means the ability to store a much larger volume of hydrogen vs cylinders.
As an example, X-43 flown by Nasa which flew at Mach 9.97. The fuel source was Hydrogen, which is extremely more volatile and combustible then kerosene (JP-7), via a cylinder in the main body. If it had used our technology, that entire section of the airframe would had been an 8,000 PSI H2 tank, which would had yielded 5-6 times the capacity. While the X-43 flew 11 seconds under power at Mach 9.97, at 6 times the fuel capacity would had yielded apx 66 seconds of fuel under power at Mach 9.97. If it had flew slower, around Mach 6, same principles applied would had yielded apx 500 seconds of fuel supply under power (slower speeds required less energy to maintain).
Enhanced Fuel Mixture During Shock Train Interaction
Normally, fuel injection is conducted at the correct insertion point within the shock train for maximum burn/combustion. Our methodologies differ, since almost half the fuel injection is conducted PRE shock train within the isolator, so at the point of isolator injection the fuel enhances the combustion process, which then requires less fuel injection to reach the same level of thrust capabilities.
Improved Bow Shock Interaction
Smoother interaction at hypersonic velocities and mitigating heat/stresses for beyond Mach 6 thermodynamics, which extraordinarily improves Type 3, 4, and 5 shock interaction.
6,000+ Fahrenheit Thermal Resistance
To date, the maximum thermal resistance was tested at AFRL in the spring of 2018, which resulted in a 3,200F thermal resistance for a short duration. This technology, allows for normalized hypersonic thermal resistance of 3,000-3,500F sustained, and up to 6,500F resistance for short endurance, ie 90 seconds or less. 10-20 minute resistance estimate approximately 4,500F +/- 200F.
*** This technology advancement also applies to Aerospike rocket engines, in which it is common for Aerospike's to exceed 4,500-5,000F temperatures, which results in the melting of the reversed bell housing. That melting no longer ocurrs, providing for stable combustion to ocurr for the entire flight envelope
Scramjet Propulsion Side Wall Cooling
With old technologies, side wall cooling is required for hypersonic flight and scramjet propulsion systems, otherwise the isolator and combustion regions of a scramjet would melt, even using advanced ablatives and ceramics, due to their inability to cope with very high temperatures. Using technology we have developed for very high thermodynamics and high stresses, side wall cooling is no longer required, thus removing that variable from the design process and focusing on improved ignition processes and increasing net thrust values.
Lower Threshold for Hypersonic Ignition
Active and adaptive flight dynamics, resulting in the ability for scramjet ignition at a much lower velocity, ie within ramjet envelope, between Mach 2-4, and seamless transition from supersonic to hypersonic flight, ie supersonic ramjet (scramjet). This active and dynamic aspect, has a wide variety of parameters for many flight dynamics, velocities, and altitudes; which means platforms no longer need to be engineered for specific altitude ranges or preset velocities, but those parameters can then be selected during launch configuration and are able to adapt actively in flight.
Dramatically Improved Maneuvering Capabilities at Hypersonic Velocities
Hypersonic vehicles, like their less technologically advanced brethren, use large actuator and the developers hope those controls surfaces do not disintegrate in flight. In reality, it is like rolling the dice, they may or may not survive, hence another reason why the attempt to keep velocities to Mach 6 or below. We have shrunken down control actuators while almost doubling torque and response capabilities specifically for hypersonic dynamics and extreme stresses involved, which makes it possible for maximum input authority for Mach 10 and beyond.
Paradigm Shift in Control Surface Methodologies, Increasing Control Authority (Internal Mechanical Applications)
To date, most control surfaces for hypersonic missile platforms still use fins, similar to lower speed conventional missiles, and some using ducted fins. This is mostly due to lack of comprehension of hypersonic velocities in their own favor. Instead, the body itself incorporates those control surfaces, greatly enhancing the airframe strength, opening up more space for hardware and fuel capacity; while simultaneously enhancing the platforms maneuvering capabilities.
A scramjet missile can then fly like conventional missile platforms, and not straight and level at high altitudes, losing velocity on it's decent trajectory to target. Another added benefit to this aspect, is the ability to extend range greatly, so if anyone elses hypersonic missile platform were developed for 400 mile range, falling out of the sky due to lack of glide capabilities; our platforms can easily reach 600+ miles, with minimal glide deceleration.
Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, the agency’s Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer, or OSIRIS-REx spacecraft is encapsulated in its payload fairing. Targeted for liftoff at 7:05 p.m. EDT Sept. 8, 2016, OSIRIS-Rex will be the first U.S. mission to sample an asteroid, retrieve at least two ounces of surface material and return it to Earth for study. The asteroid, Bennu, may hold clues to the origin of the solar system and the source of water and organic molecules found on Earth.
Photo credit: NASA/Dimitri Gerondidakis
John "JC" Carver, a payload integration engineer with NASA Kennedy Space Center's Test and Operations Support Contract, opens the door to the growth chamber of the Advanced Plant Habitat (APH) Flight Unit No. 1 for a test harvest of half of the Arabidopsis thaliana plants growing within.
The harvest is part of an ongoing verification test of the APH unit, which is located inside the International Space Station Environmental Simulator in Kennedy's Space Station Processing Facility. The APH undergoing testing at Kennedy is identical to one on the station and uses red, green and broad-spectrum white LED lights to grow plants in an environmentally controlled chamber. The seeds grown during the verification test will be grown on the station to help scientists understand how these plants adapt to spaceflight. Photo credit: NASA/Leif Heimbold
The Chinook and its 15,000 pound payload are center-right in this photo, above the two dark humps or hills.
A CH-47 Chinook crew from Bravo Company, 1-126th General Support Aviation Battalion, was called to assist aviators from the Naval Strike and Air Warfare Center from Fallon, Nev., on Jan. 5, 2012. One of their Navy MH-60S Seahawk's had crash landed during a training mission high in the Toiyabe National Forest near the U.S. Marine Corps Mountain Warfare Training Center (MWTC), northwest of Bridgeport, Calif. All four crewmen aboard were able to walk away from the Dec. 21 incident but now the Navy wanted their aircraft back. The California Army National Guard flight crew from Stockton landed on a bald hilltop at 9,200 feet and was escorted to the crash site by Marines from the MWTC. Over the next few hours U.S. Marine rigging specialists from the Combat Logistics Battalion 17, specially called up from Camp Pendleton, worked with their fellow Devil Dogs trained in alpine, rock, and snow warfare, to prepare the pre-stripped helicopter for extraction. Taking guidance from a Naval MH-60S crew chief and the experts flying the tandem rotor hauling machine, the multi-service recovery team was able to pluck the 15,000 pound fallen bird, which was painted as an opposition force "enemy" aircraft, above the pine trees, down the canyon and back to the MWTC. Everyone watching, including representatives from the U.S. Forestry Service and the MWTC Environmental Office applauded the safe and successful operation. The aircraft, which lost its tail end during the hard landing, will rest on the Marines tarmac while it is subjected to further pokes and prods as key personnel continue to investigate how the incident happened. (Army National Guard photos by Master Sgt. Paul Wade)
While the C-141A Starlifter had done well in the 1960s, especially in supply efforts over Vietnam, the aircraft had one glaring problem: it would “bulk out” before it reached its projected payload weight: the fuselage would be full, but the aircraft was capable of carrying more. In response to this and the C-141’s need for fueling stops on long trips, the USAF began upgrading the C-141A fleet to C-141B standard.
By adding two plugs fore and aft of the wings, the fuselage was stretched 23 feet. While the Starlifter was still incapable of carrying oversize loads, it now could carry up to its full weight. Inflight refuelling capability was also added. All surviving C-141As were upgraded between 1977 and 1982 to B standard, essentially adding 90 new C-141s to the fleet without building new aircraft. With the C-5B Galaxy also entering service, the C-141B gave the USAF unmatched air transport capability, something that would be very useful in time of war. Its first wartime service would be Operation Desert Shield, the buildup to the First Gulf War of 1991. Starlifters carried nearly half of all payloads delivered to the Southwest Asia theater.
The 1990s would see the most use of the aircraft, especially over the wartorn former nations of Yugoslavia. During NATO efforts to resupply Bosnian towns cut off by Serbian forces, C-141s were flown from Rhein-Main airbase at low level over Bosnia, where cargo pallets were dropped from the rear filled with food. As these pallets could cause damage when they hit the ground, the pallets were replaced by food boxes tied together: these boxes would break apart in midair and float down on individual parachutes. These “food bombs” would be used later in other areas where the C-141 was unable to land. Other Rhein-Main based Starlifters made the trip into the Bosnian capital of Sarajevo, the airport of which was considered one of the most dangerous spots on earth, constantly subject to mortar and sniper fire, and required a diving approach to avoid being shot at by Serbian antiaircraft units posted in the mountains around the airport. C-141s and other NATO transports kept the city alive during its three-year siege, which finally ended in 1995.
In response to this, 13 C-141Bs were modified to SOLL II standard, with low-light vision equipment, GPS, and defensive chaff/flare countermeasures, for operations over high-threat areas or in conjunction with Special Forces units. Later, about a third of the lowest-timed Starlifters were modified to C-141C standard, with a new “glass” cockpit and upgraded avionics.
Despite the upgrade, the days of the C-141 were numbered. It was getting old, and wing cracks had begun to appear on older aircraft. As the C-17 Globemaster III was now coming into service, Starlifters began to be retired. The C-141Cs soldiered on long enough to be used in Afghanistan and Iraq, where they finally used their paratroop-carrying capability in combat, dropping elements of the 101st Airborne Division near Tikrit in northern Iraq. After 2004, the Starlifter was retired from active units and passed on to Air National Guard and Reserve units; the last eight operational C-141s were used to shuttle supplies into New Orleans after the Hurricane Katrina disaster of 2005. This was the Starlifter’s swan song, as after this operation ended the C-141 finally left USAF service after forty years of service. Of 285 aircraft, 19 were lost in accidents; 13 are preserved in museums.
As the small marking on the nose says, this is the very first stretched C-141B, 66-0186. Built as a C-141A, it originally served with the 437th Military Airlift Wing at Charleston AFB, South Carolina. In 1977, 66-0186 was returned to Lockheed Marietta to be stretched, and completed flight testing at both Dobbins AFB (the location of Lockheed Marietta) and Edwards AFB, California. Once testing was finished, it was assigned to the 443rd MAW at Altus AFB, Oklahoma and was occasionally used as the personal aircraft of the commanding officer of Military Airlift Command. Unlike the rest of the C-141 fleet in the 1980s, 66-0186 was not camouflaged and kept the original white over gray scheme for its entire career. It was retired in 1993 and slated for preservation because of its status as the first C-141B.
As there was nowhere to display 66-0186, it was dismantled and stored at the Lockheed plant. When the Marietta Museum of History acquired land for an airpark on the northwest side of Dobbins, 66-0186 was moved there, repainted, and partially reassembled. When I saw it in 2019, it was still lacking engines; the rear ramp is displayed open, albeit with mesh covering to keep people out of the cargo bay. Seeing this aircraft was special for my uncle, who used to do maintenance on C-5s and C-141s during his time in the USAF.