Guidance strategy for interplanetary low-thrust trajectory based on B-plane parameters

A predictive guidance scheme based on B-plane parameters is proposed for interplanetary low-thrust trajectories in this paper. Firstly, thrust control parameters are piecewise parameterized. The sequential quadratic programming algorithm is used to obtain the optimal nominal trajectory. Then, the coefficients of piecewise function are selected as the guidance parameters, and B-plane parameters are selected as the terminal constraints, so that the function relation between B-plane and guidance parameters is established. Based on differential correction algorithm, piecewise successive correction strategy is used to correct the guidance parameters. Finally, Monte Carlo analyses of Earth-Mars transfer are used to verify the efficiency of the proposed method. The result indicates that, compared with the orbit parameters method, the B-plane parameters method has the higher guidance precision and less correction frequency.