A strapdown inertial navigation algorithm of spinning missile in launch coordinate system
Aiming at the improvement of the accuracy in attitude algorithm of spinning missile,a strapdown inertial navigation algorithm in launch coordinate system was proposed.Firstly,the navi-gation algorithms were deduced.Secondly,the rotation vector algorithms using pre-angular and calcu-lation errors were deduced.Finally,by using the improvement method for scaling factor,the attitude measurement was better realized.The mathematical simulation and semi-physical simulation for ana-lyses of two-sample,optimal two-sample are made.The results indicate that the performance of the optimal algorithm using pre-angular increment is better than traditional algorithm.The test verified the correctness and effectiveness of the algorithm.
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