Fluid Power and Control Requirements for the Space Shuttle Orbiting Vehicle 730986
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.
Citation: McGillen, V. and Rosenbaum, B., "Fluid Power and Control Requirements for the Space Shuttle Orbiting Vehicle," SAE Technical Paper 730986, 1973, https://doi.org/10.4271/730986. Download Citation
Author(s):
Vernon McGillen, Bernhard Rosenbaum
Affiliated:
Space Div., Rockwell International
Pages: 14
Event:
Aerospace Fluid Power and Control Systems Technologies
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Spacecraft
Hydraulic systems
Rocket engines
Aircraft
Runways
Valves
Aerodynamics
Entry, descent, and landing
Airports
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