Error Analysis And Trajectory Design Optimization For Autonomous Rendezvous On Elliptical Orbit

The autonomous rendezvous and docking technology is crucial to on-orbit service,military application, space debris clearance, and deep space exploration. The ellipticalorbit state transition matrix, autonomous rendezvous switching condition, closed-loopcovariance analysis and optimal multi-objective rendezvous trajectory design areresearched. The main results achieved in this dissertation are summarized as follows.Based on the TH equations, a ne w state transition matrix for relative motionon an arbitrary elliptical orbit is deduced.1) In the target orbit coordinate system, thegeneral form of relative dynamics equations, Lawden equations and TH equations arederived.2) Based on the TH equations, a new state transition matrix for relative motionon an arbitrary elliptical orbit (0e1) is deduced, which avoids the singularity ofLawden equation. As a result, the state transition matrix of circular orbit rendezvous andelliptical orbit rendezvous are unified.3) The characteristics of elliptical orbitrendezvous trajectory are analyzed.The impulsive guidance model and a ne w s witching condition are developedfor elliptical autonomous rendezvous.1) The models such as the Hill guidance model,multi-impulse guidance model and horizontal impulsive guidance model are developed.2) The factors that influence the radial oscillation of spacecraft relative trajectory areanalyzed in both nearly circular orbit rendezvous and elliptical orbit rendezvous.Considering the propellant consumption and relative trajectory error, the switchingcondition that changes the rendezvous process from ground guided phase to self-guidedphase is given.The covariance of autonomous rendezvous under closed-loop control isanalyzed.1) Based on the assumption of impulsive control, the error dispersionequations during the processes of propagation, update and correction are derived.Furthermore, the relative trajectory control covariance is obtained.2) The effections ofimpulse number, rendezvous time, eccentricity and initial true anomaly on the terminalposition control accuracy are analyzed, and the results are verified by Monte Carlosimulations.According to the performance indexes and considering propellantconsumption, relative position robustness and relative velocity robustness, themethod of optimal multi-objective trajectory design based on closed-loop control isproposed.1) Based on linear covariance analysis method, propellant consumption,relative position robustness and relative velocity robustness are formulated.2) NSGA-IIis employed to solve the optimal multi-objective rendezvous problem, and theeffectiveness of the optimization results is validated by Monte Carlo simulations.The error analysis and trajectory design optimization for autonomous rendezvous on elliptical orbit are researched in this dissertation. The technologies such as theelliptical orbit state transition matrix, autonomous rendezvous switching condition,closed-loop covariance analysis and optimal multi-objective rendezvous trajectorydesign are developed. Some new methods and useful conclusions are obtained, whichare useful to autonomous rendezvous mission design.