Mission Planning Of Space Rendezvous Phasing Maneuvers

Rendezvous and docking technology is a key technology for the second step of China manned spaceflight project. The mission plan for phasing maneuvers is a critical problem of rendezvous trajectory design and control. For the purpose of solving the phasing trajectory design and control problem, this dissertation studies phasing maneuver mission preflight planning problem, real-time planning problem and orbital reconfiguring planning problem. The main results achieved in this dissertation are summarized as follows.The phasing maneuver mission preflight planning strategies oriented to engineering application are studied. 1) The special-point maneuvers'program is designed based on Gaussian form perturbed equations of motion, and a simple iterative solving method combining a rough solver and an accurate solver is proposed by dividing the design variables into several groups; 2) A bi-level nonlinear programming model for combined maneuvers based on linear deviation equations on neighboring circular orbits is formulated. The higher-level problem is solved by employing a hybrid approach combining the parallel simulated annealing algorithm and the sequential quadratic programming algorithm, and the lower-level problem is solved using the linear iteration method based on feasible steepest descent algorithm; 3) The modified special-point maneuvers'program is proposed by adding the location of the circularizing maneuver as the design variable, and two different solving methods including the nonlinear programming method and the method based on the iteration of linear deviation equations'nonlinear solution are proposed. The proposed three preflight planning strategies are testified and validated by solving the perturbed phasing problem.The phasing maneuver mission real-time planning strategies for reducing the trajectory deviations'influence are studied. 1) The sensitivity of the main errors affecting phasing trajectory is analyzed using experimental design method, and the result is explained by linear deviation equations; 2) Based on the maneuver program's characteristics and the relationship between errors and terminal precision, three different real-time planning strategies are formulated respectively. The simple iterative solving method is proposed for special-point maneuvers, and the linear iterative solving method is proposed for combined maneuvers, while the solving method combining linear iteration and nonlinear programming is proposed for modified special-point maneuvers; 3) The precision of combined maneuvers and modified special-point maneuvers under real-time planning strategies is evaluated by Monte Carlo simulation. The results show that good terminal precision can be achieved based on the designed real-time planning strategies. Compared with modified special-point maneuvers, combined maneuvers have similar terminal position precision and better terminal velocity precision.The phasing orbital reconfiguring planning strategies after maneuver failure are studied. 1) The main constraints affecting the phasing orbital reconfiguring are analyzed, and the designing regulations for orbital reconfiguring are proposed; 2) The iterative solving method based on multiple-revolution lambert rendezvous algorithm is proposed for orbital reconfiguring which has no constraints of thrust direction, while the nonlinear programming solving method based on phase angle estimating is proposed for orbital reconfiguring which has the constraints of thrust direction. The proposed solving methods are testified and validated by solving an orbital reconfiguring problem after the thruster open/close failure.A phasing maneuver mission planning software is developed. According to the object-oriented methodology, the phasing maneuver mission planning software which integrates the achievements of this dissertation is developed. The software is coded by standard C++ programming language and developed in Visual C++ 6.0.The study is based on the traits of rendezvous phasing problem. The systematic solving methods are proposed according to the characteristics of preflight planning problem, real-time planning problem and orbital reconfiguring planning problem. The achievements of this dissertation are valuable both in theoretical research and operational application, and are used in the trajectory design of rendezvous and docking for the second step of China manned spaceflight project.