Studies on optimized algorithm for SINS under high dynamic

Abstract

As to improve the attitude solving accuracy of strapdown inertial navigation system (SINS) boarded on the spacecraft for high dynamic application, a novel optimized coning error compensation algorithm is developed. Based on the rotation vector concept, a general scheme of N measurement samples coning error compensation by utilizing the last P measurement samples is proposed. Then, an optimized compensation algorithm is given in fixed frequency environment. And the key coefficients of this algorithm can be acquired by a simple matrix calculus rather than a complicated derivation. Finally, the algorithm is verified and tested by physical experiment. The results show that the coning error compensation accuracy does can be improved.