Attention 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.
Description of a dual fail-operational redundant strapdown inertial measurement unit for integrated avionics systems research
ROLM Computer Users Group Meeting ; 1981 ; San Diego, CA
1981-02-01
Conference paper
No indication
English
The reliability analysis of a separated, dual fail operational redundant strapdown IMU
Tema Archive | 1983
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