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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.
'Rocket Engine 253') and its later variants, the RD-275 and RD-275M, are liquid-propellant rocket engines developed in the Soviet Union by Energomash. The engines are used on the first stage of the Proton launch vehicle and use an oxidizer-rich staged combustion cycle to power the turbopumps.
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
The Vikas (a portmanteau from initials of VIKram Ambalal Sarabhai [5] [6]) is a family of hypergolic liquid fuelled rocket engines conceptualized and designed by the Liquid Propulsion Systems Centre in the 1970s. [7] [8] The design was based on the licensed version of the Viking engine with the chemical pressurisation system. [9]
In 2023, CASC plans to conduct more tests on the YF-90 engine, as well as on its first-stage counterpart, the YF-130 engine. The YF-130 is a liquid kerosene-oxygen rocket engine with a thrust of 500 tonnes. Both engines are expected to be ready for flight by 2025. [9] On December 17, 2024, the engine successfully underwent its first full system ...
Like many other liquid-fuel rocket engines, the XLR99s used regenerative cooling, in that the thrust chamber and nozzle had tubing surrounding it, through which the propellant and oxidizer passed before being burned. This kept the engine cool, and preheated the fuel. The basic engine has a mass of 910 lb (410 kg).
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