The configuration of a redundant attitude reference system using three tuned dry gyros is presented. The system increases the reliability of a strapdown inertial navigator and the failure detection procedure required for system operation. The sensor orientation in the system is modeled and the relationships between navigation reference data and outputs of the tuned dry gyros are obtained. It is shown that sensor failure may be detected using various combinations of gyro outputs. The failure detection procedure is simulated and the speed of failure detection is evaluated.
16th International Symposium on Space Technology and Science, Vol. 1
- Pub Date:
- Strapdown Inertial Guidance;
- Error Correcting Devices;
- Kalman Filters;
- Instrumentation and Photography