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Fluid Power and Control Requirements for the Space Shuttle Orbiting Vehicle
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1973 by SAE International in United States
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The Space Shuttle Orbiter Vehicle is a combination spacecraft and aircraft which can remain in orbit for 7 days and also fly horizontally and land on existing SAC type airport runways. The vehicle utilizes gimbaling of the main rocket engines and rudder control during ascent and aerodynamic surfaces for control during re-entry, approach and landing. A hydraulic system was selected for actuation of those controls and for actuation of the landing gear, brakes, steering, and main engine control valves.
This paper discusses system characteristics, power requirements and maintenance features of the Orbiter Hydraulic system. The hydraulic system goal for design is to provide vehicle reliability and serviceability comparable to aviation standards.