Research On The Guidance Law For Non-cooperative Close-in Spacecraft Rendezvous

Since human society entered the twenty-first century,modern industrial science and technology have been changed rapidly.With the continuous development and progress of science and technology in the space industry,space activities are becoming more and more frequent,which have brought great influence on human society,national defense,military and national interests.At the same time,the competition for space resources is becoming more and more intense and the space security and interests have long been the focus of the world.It is one of the important directions for the future development of space science and technology,which guarantees the safety of space spacecraft effectively and improve its own ability of space attack and defense in the future.This paper is set in the research background of space spacecraft rendezvous and docking and the approach of space rendezvous near range guidance for noncooperative target spacecraft is deeply studied,especially for "noncooperative" constraint conditions on noncooperative target spacecraft,where the method and strategy of short range guidance are explored and analyzed.The main research work can be summarized in the following aspects.It introduces the research background,the current situation of relevant research both at home and abroad,and the value and significance of this study.The space rendezvous,the process of rendezvous and docking and the close range guidance are explained based on the space mission.In view of the tasks,objects and requirements of the guidance stage of the close range guidance phase,the whole structure of the tracking spacecraft control system is designed and the modules of each module are designed where the function of each section is described in detail.The relative motion between the target spacecraft and the tracking spacecraft is analyzed.On the one hand,the relative motion of spacecraft in the process of rendezvous and docking is analyzed on the basis of the theory of spacecraft dynamics,where the establishment and conversion of coordinate system,and the dynamic equation are given,at the same time the mathematical model of the spacecraft rendezvous near range guidance is established.On the other hand,the space two body and orbit elements are defined,and the calculation formula and method steps of the spacecraft’s flight orbit are derived on this basis,so as to complete the determination and prediction of the initial orbit of the spacecraft.The mathematical model of the relative motion of the two spacecraft is linearized under certain assumptions and the C-W equation is derived.At the same time,the general method of derivation of the relative motion equation under the influence of the non-perturbation is given,and the relative motion of the two spacecraft in the orbit plane is analyzed by the C-W equation.The spatial expression of relative motion state of the two spacecraft is derived using modern control system theory from the point of view of energy,and the guidance law and the C-W equation based pulse guidance model for the tracking of the spacecraft are further derived.We mainly focus on the optimization and track maneuver strategy of short-range guidance algorithm for noncooperative targets on the basis of the above research.Firstly,the characteristics of the noncooperative target and the short range guidance phase guidance task are analyzed.Then,the near range guidance algorithm and the orbit maneuver strategy are derived and optimized according to the constraints of the near range guidance orbit maneuver of the noncooperative target space rendezvous.Finally,the multi pulse optimal orbit control is solved and the simulation is used to simulate the trajectory maneuver.The software carries out the simulation test and the contrast analysis.