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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 ...
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.
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.
Figure 1: A de Laval nozzle, showing approximate flow velocity increasing from green to red in the direction of flow Density flow in a nozzle. A rocket engine nozzle is a propelling nozzle (usually of the de Laval type) used in a rocket engine to expand and accelerate combustion products to high supersonic velocities.
Shock diamonds are the bright areas seen in the exhaust of this statically mounted Pratt & Whitney J58 engine on full afterburner.. Shock diamonds (also known as Mach diamonds or thrust diamonds, and less commonly Mach disks) are a formation of standing wave patterns that appear in the supersonic exhaust plume of an aerospace propulsion system, such as a supersonic jet engine, rocket, ramjet ...
The engine may be a cryogenic rocket engine, where the fuel and oxidizer, such as hydrogen and oxygen, are gases which have been liquefied at very low temperatures. Most designs of liquid rocket engines are throttleable for variable thrust operation. Some allow control of the propellant mixture ratio (ratio at which oxidizer and fuel are mixed).
In a gimbaled thrust system, the engine or just the exhaust nozzle of the rocket can be swiveled on two axes (pitch and yaw) from side to side. As the nozzle is moved, the direction of the thrust is changed relative to the center of gravity of the rocket. The diagram illustrates three cases.