Research On Orbit Optimization And Control Of Intercept Satellite

Space technology develops rapidly and play significant role in people’ economy, life and military activity. Research of space attacking and defending technology makes great sense to country’s outer space resource. This dissertation studied the orbit optimization and control of the intercepting satellite which is an important method of the space interception.In the multiple impulsive interception problem, the dissertation applied the accurate intercepting dynamics and fuel-optimal objective. After simplified the problem, we employed the feasible solution iteration method to include the intercept terminal and contact angle constraints in the optimization object function. In order to solve this multiple solution minimizing problem. We improve the cuckoo search algorithm by the simplex idea. The simulation indicates the changed CS algorithm validity.The second section discussed the distant two-side time optimal intercepting problem in which both the pursuer chased the evader in the dynamics containing the J2 nonspherical perturbation. Both the two satellite employed the continuous small thrust. The Hamiltonian was applied to obtain the optimal control of the differential games’ saddle solution. The time-save optimization question was altered as the two-point boundary value problem. I used the meta-optimization and the nonlinear regulation algorithm to solve the BPBVP. Considering the thruster angle constraints, the dissertation optimized the Hamiltonian with the geometrical means to gain the optimal control strategy in the 2D/3D circumstance. Simulation was used to show the effectiveness of the proposed method.Then the thesis studied the pursuit and evasion problem at the intercepting end with both sides could maneuver by small magnitude acceleration. The C-W equation was obtained by set the virtual referred orbit. The thesis transformed the infinite horizontal continuous differential games to the algebraic Riccati equation and discuss the optimal and sub optimal feedback control when the control magnitude was unlimited and constrained respectively. Also the suboptimal close-loop control strategy is obtained to deal with the finite time control problem with acceleration magnitude maximal constraints. At last the practical feedback control were given to the pursuer and evader by introducing the zero control miss vector. The advantages and weakness of the control strategy were discussed in the simulation.The last section made research on the feedback control strategy of multiple satellites cooperation with multiple object and simple object based on the zero control miss vector. It also studied the pursuer-evader-defender coexist scene where the defender take effect in short time. Objective function including the pursuit and evasion thought was employed to give the control of the pursuer satellite. More practical and effective feedback was given to the interceptor with the help of the geometrical prove. The simulation lastly shown the reliability and rapidity of the multiple satellite cooperation interception and the advantage of the feedback control obtained by the geometrical method...