This content is not included in your SAE MOBILUS subscription, or you are not logged in.
Hydraulic and Flight Control System for Space Shuttle Orbiter
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1972 by SAE International in United States
Annotation ability available
The Space Shuttle Orbiter is a combination spacecraft and aircraft which can remain in orbit from 7 to 30 d and also fly horizontally and land on existing commercial airport runways. The vehicle utilizes gimballing of the main rocket engines for control during ascent and typical aerodynamic surfaces for control during reentry, approach, and landing. A hydraulic system was selected as the power source for operation of these controls and for actuation of the landing gear, brakes, steering, and jet engine deployment.
This paper discusses the system selection rationale, power requirements, flight control characteristics, operational profile, maintenance features, built-in test requirements, and innovative features of the hydraulic system. The system design provides for spacecraft reliability with commercial aircraft serviceability.
|Journal Article||Evolution of the Space Shuttle Primary Avionics Software and Avionics for Shuttle Derived Launch Vehicles|
|Technical Paper||Space Shuttle Orbiter Guidance and Control System Design|