Research On Trajectory Planning And Control Method Of GEO Target Approaching

Geosynchronous orbit is an important sort of orbits which has been widely used in communications,navigation and data relay fields.Achieving approach to the geosynchrouous satellites is the first step in carrying out on-orbit servicing missions.With the background of rendezvous missions between equator elliptic orbit chaser and GEO targets,this dissertation studies the trajectory planning,errors propagation analysis and orbit correction control.The main results achieved are summarized as follows:Firstly,the research on the approach strategy about equator elliptic orbit chaser and GEO targets is carried out.Through analysing the distribution characteristics of the GEO targets,design the equator elliptic orbit as the chaser parking orbit.The chaser approachs the GEO targets at the ascending node or descending node of the target orbits.Secondly,the fast determination method of fixed time remote optimal rendezvous trajectory planning is studied.Under the condition of no time constraint,derive the formula of velocity increment of the variable of the half path.Combined with the auxiliary optimal rendezvous orbit and all feasible solutions based on the multiple-revolution Lambert rendezvous,a graphic method to determining the optimal rendezvous is proposed.Then,the method of errors propagation analysis in the rendezvous is studied.Based on the C-W equation,a linear covariance analysis model and a CADET errors propagation model of the relative states are established respectively.Based on the nonlinear dynamic equation,a true linearized covariance analysis model and a CADET errors propagation model for relative states and their deviations are formulated.Monte Carlo method is applied to confirm the result of the two methods.Orthogonal experiment is adopted to analyse the effect of the errors on the result.Finally,the research of orbit correction control method is carried out.Making the terminal errors as the control target,a method of interative guidance based on the Lambert problem and a method of correcting the initial impulse transfer based on the pattern search are proposed respectively.The optimization model of fuel-terminal error combination is established.In this paper,the trajectory planning and control methods of GEO targets are studied,which can provide reference not only for on-orbit servicing,but also for the on-orbit monitoring or space interception.It is of great significance to improve the ability of offensive and defensive warfare.