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The RS-25 engine consists of pumps, valves, and other components working in concert to produce thrust. Fuel (liquid hydrogen) and oxidizer (liquid oxygen) from the Space Shuttle's external tank entered the orbiter at the umbilical disconnect valves and from there flowed through the orbiter's main propulsion system (MPS) feed lines; whereas in the Space Launch System (SLS), fuel and oxidizer ...
Fuel in red, oxidizer in blue. The pintle injector is a type of propellant injector for a bipropellant rocket engine.Like any other injector, its purpose is to ensure appropriate flow rate and intermixing of the propellants as they are forcibly injected under high pressure into the combustion chamber, so that an efficient and controlled combustion process can happen.
High pressure propellant tanks require thicker walls and stronger materials which make the vehicle tanks heavier, thereby reducing performance and payload capacity. The lower stages of launch vehicles often use either solid fuel or pump-fed liquid fuel engines instead, where high pressure ratio nozzles are considered desirable. [2]
Engine Origin Designer Vehicle Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [e] Oxidiser: fuel ratio ...
Aestus II (also known as RS-72) was a turbopump-fed version of the pressure-fed Aestus developed in a collaboration between the Ottobrunn Space Propulsion Centre and Pratt & Whitney Rocketdyne (Boeing Rocketdyne at the time). It was designed for improved performance, thrust and reliability over its predecessor.
Rocketdyne brought the lunar module ascent engine out of its 36-year retirement in 2008 for NASA's Exploration Systems Architecture Study (ESAS) engine testing, re-designated it as RS-18, and reconfigured the non-throttleable hypergolic engine to use LOX/methane.
The RS-25 Space Shuttle main engine is another example of a staged combustion engine, and the first to use liquid oxygen and liquid hydrogen. [4] Its counterpart in the Soviet shuttle was the RD-0120 , which had similar specific impulse , thrust, and chamber pressure, but with some differences that reduced complexity and cost at the expense of ...
The core stage of the rocket is 8.4 meters (28 ft) in diameter and mount a Main Propulsion System (MPS) incorporating four RS-25 engines. [23] [24] The core stage is structurally similar to the Space Shuttle external tank, [25] [26] and initial flights will use modified RS-25D engines left over from the Space Shuttle program. [27]