Abstract
Verifying integrity of control computers in adverse operating environments is a key issue in the development, certification, and operation of critical control systems. For example, future commercial aircraft will necessitate flight-critical systems with high reliability requirements for stability augmentation, flutter suppression, and guidance and control. This paper considers the problem of applying distributed detection techniques and decision fusion to monitoring the integrity of fault tolerant redundant control computers. A monitoring strategy is presented and demonstrated from glideslope engaged until flare using a detailed simulation of a quad-redundant longitudinal control system for the B737 Autoland. The performance of the distributed monitoring system is assessed.
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