Research On Iterative Guidance Method Of Launch Vehicle

The iterative guidance method launch vehicle is a synthetical and difficult subject which involves many courses and disciplines. In this paper, some researches are done in this field.First, basic theories are about the guidance and control method of greater launch vehicle are introduced, the kinematic and kinetic equations of six-degree of freedom of launch vehicle are set up.Second, according to the characteristic of an actual flying process of a launch vehicle, those equations are predigested. The real-time results of those equations are worked out by the method of explicit guidance.Third, On the basis hypothesis of mean gravitation, optimal control functional of the launch vehicle equations of state are set up by optimal control theory. The optimal control results of launch vehicle are worked out. This control method of automatic start is inferred, which can satisfy the terminal condition of satellite trajectories.Fourth, the iterative guidance's feasibility of different terminal conditions is analyzed.Fifth, VPM is real-time digital simulation system software of launch vehicle and missile. Based on the simulation system software, navigation and guidance real-time digital simulation system are developed to simulate the whole real-time flight control and guidance process. The results of the calculation show that navigation and guidance method is successful and satisfactory.Sixth, the results error of iterative guidance is analyzed. The methods of improve precision are put forward.In the paper, it solve the problem of mobile launch vehicle's guidance, it can ensure the orbit injection's accuracy of launch vehicle, the researches have some theoretical meaning and some value of engineering application.