An onboard failure detection and identification (FDI) technique for dual redundant sensors on the NASA F8C digital fly-by-wire (DFBW) aircraft is presented. The failure of one of a pair of sensors of the same type is detected by a direct redundancy trigger which observes the difference between the outputs of these two sensors. Identification of the failed sensor is accomplished utilizing the analytic redundancy that exists as kinematic and functional relationships among the variables being measured by dissimilar instruments. In addition, identification of generic failures, common to both instruments of a given type, is accomplished by using a time trigger to periodically initiate analytic redundancy failure identification tests for individual sensors. The basic form of these tests is the comparison of the measurement of a variable using the suspect instrument with another measurement of the same variable obtained using other instrument types.
Dual redundant sensor FDI techniques applied to the NASA F8C DFBW aircraft
Guidance and Control Conference ; 1976 ; San Diego, CA
1976-01-01
Miscellaneous
No indication
English
Learning control system studies for the F8 DFBW aircraft
Tema Archive | 1976
|The States of Technology Before DFBW
British Library Conference Proceedings | 1996
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