Study On Guidance And Conrtol Of Spacecraft Hitting Muti-Targets

As the improvement of the anti-missile defense system deployment and thediversification of anti-missile defense method among the military powers, thesurvival and penetration ability of missile are greatly reduced, therefore,Attention of research is gradually focused on the development of technologiesand applications for separation technology of the ballistic missiles. To hitmultiple targets in high accuracy, orbit maneuvers for the missiles are necessary,so that the trajectory deviations in attacking different targets can be corrected. Atthe same time, to achieve the guidance ability, stable and fast attitude control onthe missile is necessary.Thorough research is conducted in this thesis on related technologies formultiple warheads. Based on the establishment of the mathematical models of thespace targets, ground targets and the characteristics of the task, reasonableguidance scheme is developed. Guidance and attitude control method for multipletargets hitting is also studied. The main work of the thesis is as follows.(1) Establishment of mathematical models for the missile and the targets.Coordinate systems and their conversion relations are given. Then, thekinematic and dynamic models are established based on force analysis of thespace targets and the separation targets. Finally, mathematical models of the masscenter and the rotational inertia are constructed.(2) Investigation on middle course guidance law of the separation of spacetargetTraditional middle guidance problem is formulated, and the basic theory andthe algorithms for the middle course guidance are introduced, which is improvedwith the reentry angle constraint conditions considered. Using the two-bodytheory, the algorithm to calculate the required speed is proposed to meet thereentry conditions. The guidance algorithm is modified with the J2gravitationalperturbation considered. Finally, mathematical simulation is conducted to verifythe proposed algorithm.(3) Research on attitude control method based on dynamic inversion control methodThe attitude control system of the space target is designed based on thedynamic inversion control method. The basic theory of the dynamic inversioncontroller is introduced in detail, and a dynamic inversion controller is designedfor the attitude control system with the jet thrusters and three kinds of controlstrategy for the attitude control jet thrusters are given. Finally, mathematicalsimulation is conducted.(4) Mathematical simulation analysis on the process of Space targetseparationBased on the sequence of the separation process of the guidance scheme, the6-DOF mathematical simulation for the separation process is conducted.