关键词: 途经点, 多脉冲制导, 状态转移, 交会对接, 模型预测与反演控制, 离散时间系统, 遗传算法

Abstract: To meet the requirements of mission scenarios such as space rendezvous and docking, formation configuration, in orbit services, and maneuvering avoidance, in the process of space multi pulse relative guidance with clear starting and ending states and passing through several expected waypoints, in order to obtain the optimal fuel consumption of the spacecraft, it is necessary to optimize the guidance trajectory and control process, determine a reasonable passing sequence, passing time, and passing speed.In discrete-time systems, based on the system dynamics state transition model, variable substitution and progressive iteration methods are used to represent the unknown relative velocity of the waypoint using known states and the guidance control sequence to be solved. Combined with the generalized inverse least squares solution, the optimal control sequence under the global two norm condition is obtained. Then, a model prediction and inversion guidance control method for spatial relative guidance under time and waypoint position constraints is designed.To further optimize the fuel consumption during the guidance process, a genetic algorithm is used to search for the sequence and optimal time of passing through each waypoint. The simulation results of near circular orbit rendezvous guidance control show that the proposed method can achieve fuel consumption optimization in high-precision, smooth relative guidance control processes under the conditions of constrained/unconstrained waypoint sequence and passage time in three scenarios related to passage time and sequence..

Key words: waypoint, multi pulse guidance, state transition, rendezvous and docking, model predictive and inversive control, discrete time systems, genetic algorithm