The Rocketdyne LR89 was a liquid-fueled rocket engine developed in the 1950s by Rocketdyne , a division of North American Aviation . It was designed to serve as a booster engine the Atlas rocket family . The LR89 was a liquid oxygen (LOX) and RP-1 (kerosene) engine.
4-516: It was used in configurations where it worked alongside the LR105 sustainer engine to enhance thrust in the first stage of the Atlas, being jettisoned when the vehicle weight had been considerably reduced due to propellant consumption. The LR89 was part of a family of engines that Rocketdyne developed to power the first American ICBM s and satellite launch vehicles. It was a gas-generator cycle engine, in which
8-422: A portion of the fuel and oxidizer is burned to drive a turbine, which powers the fuel pumps, and featured a hypergolic igniter . The LR89 engine underwent several upgrades throughout its operational life, resulting in multiple versions: The LR89 powered the first Atlas stage, in different configurations: This rocketry article is a stub . You can help Misplaced Pages by expanding it . LR105 The LR105
12-437: A small portion of the propellant is burned in a gas generator to drive the turbopumps , which supply the engine with fuel and oxidizer. The engine was designed to be throttleable , meaning its thrust could be adjusted during flight to optimize performance. The LR105 also features regenerative cooling , where RP-1 fuel is circulated through cooling channels in the engine's nozzle and combustion chamber before being injected into
16-564: Is a liquid-fuel rocket engine that served as the sustainer engine for the Atlas rocket family. Developed by Rocketdyne in 1957 as the S-4, it is called a sustainer engine because it continues firing after the LR89 booster engines have been jettisoned, providing thrust during the ascent phase. The LR105 is a liquid-propellant engine using RP-1 / LOX . The engine operates on a gas-generator cycle , where
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