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The engine developed about 3,500 pounds-force (16 kN) of thrust, which produced a velocity of 2,000 meters per second from lunar launch, to LOR, and CM docking. [7] [2] It weighed 180 pounds (82 kg), with a length of 47 inches (120 cm) and diameter of 34 inches (86 cm). [8] [unreliable source?] Lunar ascent by Apollo 17 ascent stage.
Engineers at Arnold Air Base with an Apollo service module engine Apollo Service Module Propulsion System The service propulsion system ( SPS ) engine was originally designed to lift the CSM off the surface of the Moon in the direct ascent mission mode, [ 20 ] The engine selected was the AJ10-137 , [ 21 ] which used Aerozine 50 as fuel and ...
A major portion of the service module was taken up by propellant and the main rocket engine. Capable of multiple restarts, this engine placed the Apollo spacecraft into and out of lunar orbit, and was used for mid-course corrections between the Earth and the Moon. The service module remained attached to the command module throughout the mission.
The Apollo 10 ascent stage engine was fired until its fuel was used up, sending it past the Moon into a heliocentric orbit. [ 9 ] [ 10 ] The Apollo 11 ascent stage was left in lunar orbit to eventually crash; all subsequent ascent stages (except for Apollo 13) were intentionally steered into the Moon to obtain readings from seismometers placed ...
The Apollo Lunar Module, used in the Moon landings, employed hypergolic fuels in both the descent and ascent rocket engines. The Apollo spacecraft used the same combination for the Service Propulsion System. Those spacecraft and the Space Shuttle (among others) used hypergolic propellants for their reaction control systems.
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.
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The LK Blok E had both primary and reserve engines allowing for reassurance of ascent; the Apollo LM lifted off with a single ascent engine, and had no backup or reserve but was designed for simplicity and reliability allowing for optimal assurance of ascent. A failure of the LM ascent engine would guarantee a critical mission failure. [1]