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Liquid rocket fuel. Oxidizer. Pumps carry the fuel and oxidizer. The combustion chamber mixes and burns the two liquids. The hot exhaust is choked at the throat, which, among other things, dictates the amount of thrust produced. Exhaust exits the rocket.
A solid fuel-oxidizer mixture (propellant) is packed into the rocket, with a cylindrical hole in the middle. An igniter combusts the surface of the propellant. The cylindrical hole in the propellant acts as a combustion chamber. The hot exhaust is choked at the throat, which, among other things, dictates the amount of thrust produced.
RS-68 being tested at NASA's Stennis Space Center Viking 5C rocket engine used on Ariane 1 through Ariane 4. A rocket engine is a reaction engine, producing thrust in accordance with Newton's third law by ejecting reaction mass rearward, usually a high-speed jet of high-temperature gas produced by the combustion of rocket propellants stored inside the rocket.
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The combustion tap-off cycle is a power cycle of a bipropellant rocket engine. The cycle takes a small portion of hot exhaust gas from the rocket engine's combustion chamber and routes it through turbopump turbines to pump fuel before being exhausted (similar to the gas-generator cycle). Since fuel is exhausted, the tap-off cycle is considered ...
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This template is for rocket engines that have flown or are expected to fly in the near term. Engines not yet flown should be in Italics. The criteria for acceptability of unflown rocket engines are: Option A. The engine has an article of at least Start class. The engine has been test fired, at least at the flight component or sub-scale level.
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