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PictionID:55544610 - Catalog:14_036661 - Title:Atls 42D Details: AIG Platform Cage; Installing in Pod on Missile 42D Date: 10/20/1959 - Filename:14_036661.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
I am going to post this as is for now, Iteration 1. Besides USPTO issued patent on the tanks last week. What is that? SS1, Single Stage to orbit Smallsat Launches to LEO. Orbital debris removal, satellite servicing. etc. Eliminating rockets, forever.
Launch cost estimates for 200 LBS? $50,000 USD... Correct. How? Slows it's itself down to 8,000 mph before re-entry which results in very little wear on the aircraft along with very high thermal resistance. It does not use liquid fuels, and unlike the other SSTO's I have designed and ready to be built, this is not a scramjet. This does not use rocket boosters. Takes off from a runway under its own power.. hence SSTO
space, ssto, space plane, ussf, space force, smallsat, orbital debri, satellite service, hypersonics, hypersonic, hydrogen, graphene, solar electric propulsion, satellite propulsion, satellites, Space Tech, Reusable Rockets, Sustainable Space, Rocket Engine, Space flight, darpa, defwerx, sda, Virgin Orbit, Sierra Nevada Corporation, NASA, National Aeronautics and Space Administration, AFWERX, Advanced Research Projects Agency, DARPA, Air Force Research Laboratory, Firefly Aerospace, European Space Agency, ESA, SpaceX, ARIANE SPACE, Axiom Space, Airbus Defence and Space, United States Space Force, Virgin Orbit Sierra Nevada Corporation NASA - National Aeronautics and Space Administration AFWERX Defense Advanced Research Projects Agency (DARPA) Air Force Research Laboratory Firefly Aerospace European Space Agency - ESA SpaceX ARIANESPACE Axiom Space Airbus Defense and Space United States Space Force
This clip is raw from Camera E-8 on the launch umbilical tower/mobile launch program of Apollo 11, July 16, 1969. This is an HD transfer from the 16mm original. Even more excellent footage is available on our DVDs at our website at www.spacecraftfilms.com
The camera is running at 500 fps, making the total clip of over 8 minutes represent just 30 seconds of actual time. Narration is provided by Mark Gray (me), Executive Producer for Spacecraft Films.
Falcon VTOL - VTOL Hypersonic Business Jet (This is not a graphics design)
New iteration update, Raven SSTO, up to 15,000 LBS payloads to orbit for apx $2 mln per launch. Compresses O2 and H2 fueled, not liquid fueled. Graphene Airframe, 6,000+F thermal resistance. Air Breathing Aerospike, along with the primary U-TBCC propulsion.
Details at link www.ioaircraft.com/hypersonic/falcon.php
Link to Conforming Tank Patent patents.google.com/patent/US20210080060
Link to Engines/Propulsion www.ioaircraft.com/hypersonic/utbcc.php
Falcon VTOL is a completely new aircraft design, next generation technologies, and capabilities never seen before. As seen here, anything released publicly are early iterations to get a good look and feel for the aircraft type publicly. But rest assured, every single aspect of this aircraft, the technologies, physics, and systems are already developed.
vtol, hypersonic, hypersonics, business jet, tbcc, nasa, nrl, onr, navsea, afrl, arl, jpl,
Virgin Orbit
Virgin Galactic
Sierra Nevada Corporation
Aevum Inc
NASA
NASA Jet Propulsion Laboratory
AFOSR, Air Force Office of Scientific Research
Defense Advanced Research Projects Agency
AFWERX
United States Air Force
Air Force Research Laboratory
Firefly Aerospace
ESA - European Space Agency
SpaceX
Axiom Space
Airbus
Airbus Defence
BAE Systems
Northrop Grumman Corporation
Lockheed Martin
Raytheon Technologies
Rolls-Royce plc
National Reconnaissance Office
The Aerospace Corporation
Collins Aerospace
BlackSky
United Launch Alliance
TÉLÉSAT
ONE.Web
ICAO - International Civil Aviation Organization
Dassault Aviation
United States Space Force
Blue Origin
Northrop Grumman Corporation
Arianespace
The F-1 rocket engines by Rocketdyne powered the first stage of the Saturn V rockets. These are what lifted it off the pad. Think about it: 5 of these lifted a 36-story building into the air.
More information on the engines is available here, but take what you find there with a grain of salt.
In der gesprengten V2 Raketen Triebwerksanlage.
In the burst open V2 Rocketengine facility.
Urbextour with JoniB, Bunkersachse, Marko Bunker and Bunkerpaule.
Info
Walter HWK 109-500 liquid-fuelled rocket engine.
The 109-500 is a self-contained, modular monopropellant Starthilfe (take-off assist) engine in a pod, able to produce 1,100 lb of thrust for thirty seconds. After the fuel was expended, the pod was jettisoned and it returned to earth by parachute, with the parachute packed externally, onto the blunt forward end of the pod.
In 1936, this experimental aircraft (EAA Chapter 501) proved that a rocket engine could lift an aircraft and payload much heavier than itself. The engine propelled this aircraft, which carried more than 6,000 letters above the frozen waters of Greewood Lake, located on the NY-NJ border.
The Descent Propulsion System (DPS) or LMDE (Lunar Module Descent Engine) is a rocket engine developed by Space Technology Laboratories for use in the Apollo Lunar Module. This is a backup engine, on display at the Western Reserve Historical Society in Cleveland, Ohio.
The design is credited to aerospace engineer Dr. Peter Staudhammer. The engine could throttle between 1,050 pounds-force (4.7 kN) and 10,125 pounds-force (45.04 kN). It weighed 394 pounds, is 90.5 inches long, and 59.0 inches in width.
The descent engine was the biggest challenge and the most outstanding technical development of the Apollo program. A throttleable engine was required, but very little research had been done in variable-thrust rocket engines.
Rocketdyne had proposed an engine in which thrust was controlled by the injection of inert helium gas into the propellant. While plausible, this approach was considered too advanced to be reliable.
TRW's Space Technology Laboratories (STL) proposed a much simpler design using flow control valves and a variable-area pintle injector (which operates in much the same manner as does a shower head). Furthermore, it recommended that the engine be gimbaled, to allow it to change the direction of thrust.
The first full-throttle firing of the STL descent engine was carried out in early 1964. NASA chose the STL design in January 1965.