Instrument failure detection using the dedicated observer scheme (DOS) depends on partial state observability through each instrument which is monitored. For instrument fault detection by the DOS technique, a quantitative measure of partial state observability is established for each instrument and used to determine a necessary condition on the output structure of the system. This measure, called the internal redundancy of the instrument, indicates the complexity of the logic required for failure detection, and it also indicates where some hardware redundancy can be introduced into the system to improve the fault detection capability of the DOS. The principles developed are applied to a simulation of the pitch axis autopilot of the A7 jet aircraft.
Instrument Failure Detection in Partially Observable Systems
IEEE Transactions on Aerospace and Electronic Systems ; AES-18 , 3 ; 310-317
1982-05-01
1543794 byte
Article (Journal)
Electronic Resource
English
Instrument failure detection in partially observable systems
Tema Archive | 1982
|Decision-Making for Autonomous Systems in Partially Observable Environments
BASE | 2013
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