Abstract
The paper considers an integrated attitude reference and navigation system for an orbital spacecraft. The system comprises a strapdown inertial attitude reference system based on electrostatic gyros (ESGs) and fiber-optic gyros (FOGs). Algorithms for joint processing of ESG and FOG data which use a Kalman filter and the corresponding criteria are described. Results of computer simulation of the system algorithms with MATLAB using ESG and FOG real test data are given.
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