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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 ...
The Orbital Maneuvering System (OMS) is a system of hypergolic liquid-propellant rocket engines used on the Space Shuttle and the Orion spacecraft.Designed and manufactured in the United States by Aerojet, [1] the system allowed the orbiter to perform various orbital maneuvers according to requirements of each mission profile: orbital injection after main engine cutoff, orbital corrections ...
The AJ10-190 engines could be reused for up to 100 missions. Diagram of an RS-25 (or Space Shuttle Main Engine), that used a twin shaft staged combustion cycle. There were three of these on the back of the orbiter. Comparing the diagram of the RS-25 to that of the Orbital Manoeuvring System (OMS), it is clear that the RS-25 engine is far more ...
Thrust vectoring for many liquid rockets is achieved by gimbaling the whole engine. This involves moving the entire combustion chamber and outer engine bell as on the Titan II's twin first-stage motors, or even the entire engine assembly including the related fuel and oxidizer pumps. The Saturn V and the Space Shuttle used gimbaled engines. [1]
The Space Shuttle External Tank for the MPTA rolls off the assembly line at the Michoud Assembly Facility. Never intended for actual spaceflight, the MPTA consisted of the internal structure of a Space Shuttle orbiter aft-fuselage, a truss structure that simulated the basic structure and shape of an orbiter mid-fuselage and a complete Space Shuttle Main Engine (SSME) assembly, including all ...
The AJ10-190 engine was used on the Space Shuttle Orbital Maneuvering System (OMS) for orbital insertion, on-orbit maneuvers, and de-orbiting, first flown in 1981. They produced 26.7 kilonewtons (6,000 lb f ) of thrust with a specific impulse ( I sp ) of 316 seconds. [ 6 ]
A series of launch vehicles was proposed, based on the proposed Space Transportation Main Engine (STME) liquid-fuel rocket engine. The STME was to be a simplified, expendable version of the RS-25 engine. The NLS-1 was the largest of the three proposed vehicles and would have used a modified Space Shuttle external tank for its core
The Block 1 configuration of SLS, which first flew the Artemis I mission, has a core stage powered by four RS-25 engines, two Space Shuttle-derived five-segment solid rocket boosters, and an Interim Cryogenic Propulsion Stage (ICPS) upper stage.