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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.
Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [e] Oxidiser: fuel ratio Aeon 1 USA: Relativity Space: Terran 1: Retired 1st CH 4 / LOX: Gas generator: 310: 86,740 (SL) [64] Aeon 1 Vacuum USA: Relativity Space: Terran 1: Retired 2nd CH ...
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 ...
Pogo oscillation is a self-excited vibration in liquid-propellant rocket engines caused by combustion instability. [1] The unstable combustion results in variations of engine thrust, causing variations of acceleration on the vehicle's flexible structure, which in turn cause variations in propellant pressure and flow rate, closing the self-excitation cycle.
During the flight, the ascent and descent engines would be fired. A "fire in the hole" test would be conducted to verify that the ascent stage could still fire while attached to the descent stage, a procedure that would be used on the lunar surface and in the event of an aborted lunar landing. It involved shutting down the descent stage ...
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]
English: Apollo 17 flight trajectory from liftoff to end of S-IVB first burn. - Altitude is given above Fischer Ellipsoid. E.g. at time 400s: EPO altitude 172km = 6545km geocentric distance = 167km above a spherical Earth of radius 6378.1 km
Some LESS designs used a single engine under the center, but many used multiple engines around the edge, typically based on the Apollo reaction control system (RCS) thrusters used for attitude control on the command and service module (CSM) and lunar module (LM). These had a thrust of around 100 pounds-force (440 N) each, so putting eight ...