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.
Fluid Power and Control Requirements for the Space Shuttle Orbiting Vehicle
Sae Technical Papers
Aerospace Fluid Power and Control Systems Technologies ; 1973
1973-02-01
Conference paper
English
Space Shuttle Reaction Control System Requirements
NTIS | 1970
|Space shuttle reaction control system requirements
NTRS | 1970
|Space Shuttle Technology Requirements
NTIS | 1970
Space Shuttle EVA requirements
NTRS | 1973
|