Inertial measurement unit fault detection isolation reconfiguration using parity logic

摘要

A method of implementing a fault-tolerant-avionic architecture in a vehicle includes using parity logic to monitor the functionality of at least three non-fault-tolerant inertial measurement units during a parity check and calculating a threshold from expected inertial measurement unit performance during a parity check. If a failure of an inertial measurement unit is detected based on the calculated threshold, then the method further includes identifying the failed inertial measurement units based on a direction of a parity vector in parity space. Each inertial measurement unit comprises at least one triad of sensors.