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A total of 100 bench tests of liquid-propellant rockets were conducted using various types of fuel, both low and high-boiling and thrust up to 300 kg was achieved. [19] [18] During this period in Moscow, Fredrich Tsander – a scientist and inventor – was designing and building liquid rocket engines which ran on compressed air and gasoline ...
An LR105 Atlas sustainer engine on display at the Air Zoo.. The LR105 is a liquid-fuel rocket engine that served as the sustainer engine for the Atlas rocket family. [1] [2] [3] Developed by Rocketdyne in 1957 as the S-4, [4] [5] [6] it is called a sustainer engine because it continues firing after the LR89 booster engines have been jettisoned, providing thrust during the ascent phase.
liquid rocket engine: used on Proton, Angara: Keldysh Research Center: Russia Voronezh Mechanical Plant: Russia liquid rocket engine: used on Vostok, Voskhod, Molniya, Soyuz, Proton, Energia, Luna: Yuzhnoye Design Office / Yuzhmash: Ukraine RD-8; RD-843; RD-855; RD-856 etc. Oxygen+kerosene and N 2 0 4 +UDMH liquid rocket engine; Solid rocket ...
Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio AJ-10-190 USA: Aerojet: Space Shuttle, Orion, Apollo CSM: Active Upper N 2 O 4 /MMH: Pressure-fed: 316 [1] 26,689 [1] 8.62 [1] 118 [1] 23.08: Archimedes New ...
The major manufacturer of German rocket engines for military use, the HWK firm, [8] manufactured the RLM-numbered 109-500-designation series of rocket engine systems, and either used hydrogen peroxide as a monopropellant for Starthilfe rocket-propulsive assisted takeoff needs; [9] or as a form of thrust for MCLOS-guided air-sea glide bombs; [10 ...
Raptor is a family of methane/liquid oxygen rocket engines under development by SpaceX since the late 2000s, [2] although LH2/LOX propellant mix was originally under study when the Raptor concept development work began in 2009. [15]
The RL10 is a liquid-fuel cryogenic rocket engine built in the United States by Aerojet Rocketdyne that burns cryogenic liquid hydrogen and liquid oxygen propellants. Modern versions produce up to 110 kN (24,729 lb f) of thrust per engine in vacuum. RL10 versions were produced for the Centaur upper stage of the Atlas V and the DCSS of the Delta IV
These cryogenic temperatures vary depending on the propellant, with liquid oxygen existing below −183 °C (−297.4 °F; 90.1 K) and liquid hydrogen below −253 °C (−423.4 °F; 20.1 K). Since one or more of the propellants is in the liquid phase, all cryogenic rocket engines are by definition liquid-propellant rocket engines. [2]