Effect of launch initial state errors on ballistic characteristic parameters

This paper is concerned with propagation law of launch initial state errors by affecting the gravitational and apparent acceleration of the dynamics equation, which leads to state deviation of three-dimensional trajectory and navigation errors for ballistic missile. The propagation process and influence mechanism of the initial state errors were analyzed. On this basis, the navigation perturbation equation with visual acceleration coupling was established by small disturbance method. Finally, the analytical solution of navigation perturbation equation was derived. The propagation matrices and deviations of the shutdown point and the placement at different launch azimuths and different launch points were obtained, and the propagation process from launch to shutdown point and placement was analyzed, and then the quantitative magnitude from the derived propagation matrices was obtained. The results show that the analytical solution can well match the numerical solution, and the influence of apparent acceleration coupling at shutdown point is negligible. Moreover, the initial positioning errors are the main factors to produce gravitational acceleration deviation, and the initial orientation errors are the main factors to produce visual acceleration deviation.