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The ascent propulsion system (APS) or lunar module ascent engine (LMAE) is a fixed-thrust hypergolic rocket engine developed by Bell Aerosystems for use in the Apollo Lunar Module ascent stage. It used Aerozine 50 fuel, and N 2 O 4 oxidizer. Rocketdyne provided the injector system, at the request of NASA, when Bell could not solve combustion ...
Booster systems engineer The booster systems engineer monitored and evaluated performance of propulsion-related aspects of the launch vehicle during prelaunch and ascent. During the Apollo program there were three booster positions, who worked only until trans-lunar injection (TLI) was complete; after that, their consoles were vacated. Booster ...
The 2005 NASA Exploration Systems Architecture Study (ESAS), part of the 2004 Vision for Space Exploration, recommended that the crew exploration vehicle (CEV) lunar surface access module (LSAM) ascent stage propulsion and service module propulsion systems employ a pressure-fed LOX/liquid methane (CH 4) engine.
The Lunar Seismic Profiling Experiment (LSPE) was a lunar science experiment, deployed by astronauts on the lunar surface in 1972 as part of Apollo 17.The goal of the LSPE was to record the seismic response generated by a variety of sources including the detonation of eight explosive charges, the ascent propulsion system on the lunar module and any natural sources.
It contained its own ascent propulsion system (APS) engine and two hypergolic propellant tanks for return to lunar orbit and rendezvous with the Apollo command and service module. It also contained a reaction control system (RCS) for attitude and translation control, which consisted of sixteen hypergolic thrusters similar to those used on the ...
The ascent stage contained the crew cabin, instrument panels, overhead hatch/docking port, forward hatch, optical and electronic guidance systems, reaction control system, radar and communications antennas, ascent rocket engine and propellant to return to lunar orbit and rendezvous with the Apollo Command and Service Modules.
He oversaw the development of the Lunar Module propulsion systems. A major concern was the ascent propulsion system, which was a critical component of the mission that had to work for the astronauts to survive. [43] Testing at the White Sands Missile Range in 1966 indicated combustion instability. [44]
The ILV lander system design consisted of three elements: a transfer element, a descent element, and an ascent element. ILV was proposed to be used for long-duration crewed lunar landings as part of NASA's Artemis program.
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