Description of a dual fail-operational redundant strapdown inertial measurement unit for integrated avionics systems researchAttention is given to a redundant strapdown inertial measurement unit for integrated avionics. The system consists of four two-degree-of-freedom turned rotor gyros and four two-degree-of-freedom accelerometers in a skewed and separable semi-octahedral array. The unit is coupled through instrument electronics to two flight computers which compensate sensor errors. The flight computers are interfaced to the microprocessors and process failure detection, isolation, redundancy management and flight control/navigation algorithms. The unit provides dual fail-operational performance and has data processing frequencies consistent with integrated avionics concepts presently planned.
Document ID
19810042530
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 Electronics Div., Hampton, Va., United States)