Integrated fault-tolerant air data inertial reference system

Details Integrated fault-tolerant air data inertial reference system Integrated fault-tolerant air data inertial reference system

1990-11-14

1994-03-22

Harvey, Jack B.

Boots, shoes, and leggings

364434, 33321, 74 534, G01C 1902

Patent

active

052970523

ABSTRACT:
A fault-tolerant air data and inertial navigation reference system utilizes skewed axis inertial sensors and fault-tolerant redundant electronics to provide higher redundancy with fewer parts. Parallelly operating processor circuits each receive the individual outputs of six skewed-axis gyros and six skewed-axis accelerometers. Each processor independently processes parity equations using the outputs to identify malfunctioning sensors. Further, the output of each processor is transmitted to three parallelly operating voter circuits. The voters are operable to discard a processor if its output does not agree with the majority. The voter outputs are similarly fed back to the processor circuits, which compare these outputs, and discard any voter whose output disagrees with the majority, thus providing a completely integrated system.

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"A Multi-DME/Inertial System for Aircraft Positioning", Latham & Richards, Navigation: Journal of The Institute of Navigation; vol. 24, No. 1, Spring '77.

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