Design of a GN and C system to meet reliability goalsThis paper analyzes the reliability of the guidance, navigation, and control (GNC) portion of an avionics system for the Space Shuttle Orbiter. This analysis shows how the GNC design is affected by the need to achieve an acceptable probability of successful completion of a mission and of safe return to an airport. It varies the redundancy of the inertial measurement unit (IMU), computers, and other time-critical elements. It also includes the reliability of the flight control electronics and of the nontime-critical sensors on a phase-by-phase basis. It shows that quadruple redundancy in certain subsystems, high quality parts, and cross-strapping on orbit are required.
Document ID
19740038209
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Kayton, M. (TRW Systems Group Redondo Beach, Calif., United States)
Date Acquired
August 7, 2013
Publication Date
January 1, 1974
Subject Category
Navigation
Meeting Information
Meeting: Annual Reliability and Maintainability Symposium