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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
The aerospike engine is a type of rocket engine that maintains its aerodynamic efficiency across a wide range of altitudes. [1] It belongs to the class of altitude compensating nozzle engines. [2] Aerospike engines were proposed for many single-stage-to-orbit (SSTO) designs. They were a contender for the Space Shuttle main engine. However, as ...
The P160C is a solid-fuel rocket engine designed for use as the first stage of the Vega-E and as the boosters of the Ariane 6 Block 2 launch vehicles. The solid rocket motors were developed by Europropulsion, a joint venture of Avio and ArianeGroup, for the European Space Agency. The "C" in the name signifies its "Common" use across these ...
Rocket engine nozzles are surprisingly efficient heat engines for generating a high speed jet, as a consequence of the high combustion temperature and high compression ratio. Rocket nozzles give an excellent approximation to adiabatic expansion which is a reversible process, and hence they give efficiencies which are very close to that of the ...
Unlike ducted engines, rockets give thrust even when the two speeds are equal. In 1903, Konstantin Tsiolkovsky discussed the average propulsive efficiency of a rocket, which he called the utilization (utilizatsiya), the "portion of the total work of the explosive material transferred to the rocket" as opposed to the exhaust gas. [6]
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.
Aerojet Rocketdyne proposed in 2014 to "lobby the government to fund an all-new, U.S.-sourced rocket propulsion system." In June 2014, Aerojet initially projected it would cost under US$25 million per pair of engines, not including the up to US$1 billion estimated development cost to be funded by the government.
RL-10 is an early example of cryogenic rocket engine. Rocket engines need high mass flow rates of both oxidizer and fuel to generate useful thrust. Oxygen, the simplest and most common oxidizer, is in the gas phase at standard temperature and pressure, as is hydrogen, the simplest fuel.
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