Fluid Power and Control Requirements for the Space Shuttle Orbiting Vehicle Space Div., Rockwell International

Format:

Conference/Event

Author/Creator:

McGillen, Vernon, author.

Conference Name:

Aerospace Fluid Power and Control Systems Technologies (1973-10-24 : San Diego, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1973

Summary:

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

Notes:

Vendor supplied data

Publisher Number:

730986

Access Restriction:

Restricted for use by site license