Study Of Iterative Guidance For Long-Range Ballistic Missile

To improving guidance precision and maneuverability of long-range ballistic missile, this thesis presents the application of iterative guidance method in long range ballistic missile. And the main research is listed as below.Firstly, the guidance theory of ballistic missile is studied. The dynamics equations and kinematic equations of ballistic missile are established, in which Earth oblateness is considered. And they are simplified, considering the actual flight characteristics. Then, based on the iterative guidance principle, the kinematic equations real - time solutions are figured out.Secondly, the optimal control functional equation are established, which is based on optimal control theory and simplified assumption of averaging gravitation. Then analyze the feasibility of iterative guidance method in different terminal conditions and the optimal control problem's solutions of the ballistic missile are figured out. Finally, the guidance equations which meets the shutdown condition is deduced.Thirdly, take the required velocity as control variable to decide whether to shut the engine down. The landing error, considering the Earth oblateness and the air friction in the reentry phase, is compensated and the virtual target is hit. Based on the virtual target, the required velocity is calculated, so the shutdown control function is confirmed.The simulation program, which is used to testify the ballistic missile's iterative guidance law, is compiled with Matlab. Then analyze the relevant simulation results. Based on the iterative guidance simulations, analyze statistically the precision of iterative guidance with Monte-Carlo Static method.This thesis researches on the solution of guidance problem in mobile launching as well as the solution of improving the hit precision, which is statistical analyzed. This thesis shows certain theoretical significance and practical value in engineering project.