Research On Control And Planning Of Terminal Intercepting Orbit For The Interceptor

With the rapid development of space technology, it has become the researchfocus of aerospace field to develop space attack-defense confrontation technology inevery country. The intercepting spacecraft is one of space interceptors and its orbitalplanning and control is the key factor in the success of intercepting mission.However, the terminal intercepting orbit which is different from rendezvous hasparticularities, for example, the target spacecraft is non-cooperative and it hasescape capability and defense system. Based on these particularities, thisdissertation focuses on the control, determination, and planning of terminalintercepting orbit for the interceptor. The major contents of this dissertation areconsisted of the following parts.Firstly, the robust H∞control method of terminal intercepting orbit is studiedwhen the target has no orbital maneuver. The uncertain system models of both circleorbit and elliptical orbit are established considering parametric uncertainty andcontrol input disturbance. The design method of robust H∞controller forintercepting orbit is proposed with multi-constraints including input constraint,system H∞performance, system finite-time performance, and poles assignment.Then the design method of robust H∞controller with saturation actuators isproposed taking system H∞performance as constraint and system finite-timeperformance as optimization index. The effectiveness of controller is validated andits control performance is analyzed by the simulation.Secondly, the robust control method of terminal intercepting orbit is studiedunder the special condition that the target is escaping. The relative orbit dynamicmodel is established when the target has orbital maneuver. This orbital maneuver istreated as system disturbance because of the cooperative target. The uncertainsystem model is built with saturation actuators parametric uncertainty, and controlinput disturbance. Taking system finite-time performance as optimization index, thedesign methods of three controllers are proposed based on EP gain, EE gain, andEP/EE gain, respectively. The effectiveness and robustness of these controllers isvalidated and their accuracy is compared by the simulation.Thirdly, the determination algorithm of terminal intercepting orbit is studiedbased on robust filtering theory considering the uncertainty of relative motion modeland non-Gaussian noise. Supposing that the orbital control law of interceptor isknown, the linear discrete system model is established based on indirectmeasurement. The design methods of three filters are proposed taking system H2performance, system H∞performance, and mixed H2/H∞performance as optimization index, respectively. The effectiveness and robustness of these filters isvalidated and their estimation accuracy is compared by the simulation. Then thesimulation with conditions of saturation actuators and escaping target are carried outand the effectiveness of mixed H2/H∞robust filter is analyzed.Finally, the intercepting orbit planning method based on genetic algorithm isstudied when the target has a defense system consisting of formation satellites. Thedynamic environment model is built according to the formation configuration anddefense radius of formation satellites. The method transforming dynamicenvironment model into static environment model is proposed. Based on this staticmodel, the path planning method is proposed by designing the coding rule, fitnessfunction, and genetic operators. Then the path planning method in dynamicenvironment model is proposed with a known control law based on geneticalgorothm. The effectiveness of methods is validated by the simulation.