Hydraulic and Flight Control System for Space Shuttle Orbiter

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.