A fault-tolerant architecture for launch vehicle guidance and control. II. Implementation

Abstract

For pt.I see ibid., p.333-6 (Oct. 1990). It is indicated that fault-tolerant guidance and control systems can be employed to meet the goals of the advanced launch system. Proven redundancy management techniques are proposed for implementation in such guidance systems. The methods discussed provide a high probability of failure detection while maintaining a low probability for false alarms. A hardware architecture that stresses robustness, simplicity, and ease of verification is advocated. The channelized repartition of instruments and electronics can be modified to support different requirements and applications. The issue of simultaneous or dormant failures is addressed. The fault-tolerant architecture and implementation discussed is considered to provide excellent reliability and probability of mission success, while maintaining very reasonable costs.<>