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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.
The ascent was normal up to 116.9 seconds after liftoff, at which point engine number eight shut off early. This was not planned, as it had been on SA-4 as a test, but the rocket compensated perfectly by burning the remaining fuel in the other seven engines for 2.7 seconds longer than planned. The first stage separated and the second stage ignited.
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 exterior of the SLA was covered by a thin (0.03–0.2 in or 0.76–5.08 mm) layer of cork and painted white to minimize thermal stresses during ascent. [3] The service module was bolted to a flange at the top of the longer panels, and power to the SLA multiply-redundant pyrotechnics was provided by an umbilical. Because a failure to ...
ARD support (ascent only) – maintained the abort region determinator processor which is used to predict trajectory capabilities during powered flight; Ascent support team (ascent only) – monitored the winds and weather at the launch site, help compute day-of-launch updates
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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.
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