基于B平面参数的行星际小推力轨道制导策略

针对行星际小推力转移轨道制导问题，提出了一种基于目标B平面参数的预测制导方法. 在对推力控制量进行分段参数化基础上，采用序列二次规划算法获得标称转移轨道；然后将分段控制函数系数作为制导参数，以B平面参数为目标约束，通过线性化处理建立目标B平面参数与离散制导参数间的映射关系. 基于微分校正思想，采用分段逐次修正策略实现了制导参数的修正. 以火星探测任务为例，基于蒙特卡洛仿真对本文方法进行了数值验证，结果表明:相比轨道参数方法，利用B平面参数方法的轨道修正次数更少，且制导精度高. 

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.