We consider an algorithm of complex flight control for a unit of angular rate sensors on the basis of a single-axis gyroscope, and briefly describe controllability and reliability of existing schemes. We proposed a scheme of a sensor with forced rotation relative to the aircraft body and obtained complete equations of motion. The results of simulating the scheme operation are demonstrated with a light maneuverable aircraft when angular rates are measured and sensor failures are detected. We indicate a preferential variant of sensor rotation and evaluate the unit reliability under sudden failures.
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