Flight test configuration for verifying inertial sensor redundancy management techniquesThe Redundant Strapdown Inertial Measurement Unit presently tested in flight configuration consists of a semioctahedral array of four dynamically tuned, two-degree-of-freedom (TDOF) gyros and four TDOF accelerometers which can provide dual, fail-operational performance for integrated avionics systems. Attention is given to the multilevel algorithm used for the detection and isolation of three ranges of sensor failure in an integrated avionics context. A technique for the generation of accelerometer and gyro error thresholds which is sensitive to dynamic sensor errors and separation effects is presented, together with simulation results. Emphasis is placed on the ensuring of highly reliable data for flight control/navigation functions, while minimizing false or missed alarms.
Document ID
19850031417
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bryant, W. H. (NASA Langley Research Center Hampton, VA, United States)
Morrell, F. R. (NASA Langley Research Center Flight Control Systems Div., Hampton, VA, United States)
Bailey, M. L. (Kentron International, Inc. Hampton, VA, United States)