Add to ORKGThe concept of a pyro thruster, combining an automatic structural attachment with quick disconnect and thrusting capability, is described. The purpose of the invention is to simplify booster installation, disengagement, and jettison functions for the U.S. Air Force Advanced Launch Systems (ALS) program
The application of pyrotechnics to aerospace systems has been resisted because normal engineering me...
Application of vortex amplifier principles to throttling of monopropellant thrusters is described. I...
The Pegasus Air-Launched Space Booster development program, begun in early 1987, has the objective o...
A design is presented for a pneumatic ejection system capable of ejecting a spin stabilized satellit...
The system includes reusable turbojet propelled booster vehicles releasably connected to a reusable ...
The development is described of an interface, the Titan Payload Adapter (TPA), between a Space Trans...
A new Relatchable Launch Mechanism was developed which enables a deployable system to be restrained ...
The thrust vector control systems of the solid rocket boosters are turbine-powered, electrically con...
During the initial certification test of the forward structural attachment of the space shuttle orbi...
A heavy launch vehicle is discussed. The launch vehicle is comprised of an expendable, multi-contain...
The design of the space shuttle solid rocket booster (SRB) subsystems for reuse posed some unique an...
A gimballing spacecraft reaction-control-system thruster was developed that consists of a small hydr...
Space transportation solid rocket motor systems; Shuttle derived heavy lift launch vehicles; advance...
Space vehicle staging and separation events require pyrotechnic devices. They are single-use mechani...
A first space vehicle is attached with a second space vehicle which includes a rocket propulsion noz...
The application of pyrotechnics to aerospace systems has been resisted because normal engineering me...
Application of vortex amplifier principles to throttling of monopropellant thrusters is described. I...
The Pegasus Air-Launched Space Booster development program, begun in early 1987, has the objective o...
A design is presented for a pneumatic ejection system capable of ejecting a spin stabilized satellit...
The system includes reusable turbojet propelled booster vehicles releasably connected to a reusable ...
The development is described of an interface, the Titan Payload Adapter (TPA), between a Space Trans...
A new Relatchable Launch Mechanism was developed which enables a deployable system to be restrained ...
The thrust vector control systems of the solid rocket boosters are turbine-powered, electrically con...
During the initial certification test of the forward structural attachment of the space shuttle orbi...
A heavy launch vehicle is discussed. The launch vehicle is comprised of an expendable, multi-contain...
The design of the space shuttle solid rocket booster (SRB) subsystems for reuse posed some unique an...
A gimballing spacecraft reaction-control-system thruster was developed that consists of a small hydr...
Space transportation solid rocket motor systems; Shuttle derived heavy lift launch vehicles; advance...
Space vehicle staging and separation events require pyrotechnic devices. They are single-use mechani...
A first space vehicle is attached with a second space vehicle which includes a rocket propulsion noz...
The application of pyrotechnics to aerospace systems has been resisted because normal engineering me...
Application of vortex amplifier principles to throttling of monopropellant thrusters is described. I...
The Pegasus Air-Launched Space Booster development program, begun in early 1987, has the objective o...