考虑逃逸与俘获过程的行星际小推力轨道设计

Design of Interplanetary Low-Thrust Trajectory Including Escape and Capture Phase

提出一种包含逃逸和俘获阶段的行星际小推力全程轨道设计方法.该方法采用分步式设计思想,针对地球逃逸、日心转移和目标星俘获三段轨道的转移特点,分别采用加权组合控制律和混合法进行顺序设计,并基于拼接条件在地球和目标星引力影响球处完成不同轨道段间的拼接.该方法降低了多引力场穿越轨道动力学的强非线性,具有较高的计算效率和良好的收敛性.以地球-火星转移为例对设计方法进行了仿真计算,数值结果表明:该方法可有效用于行星际小推力转移任务的全程轨道设计.

A novel design method for interplanetary low-thrust transfer trajectory including escape and capture phase is proposed.In this approach,based on multiple-step design concept,blended locally optimal laws and hybrid method are used to design earth escape,interplanetary transfer and target capture trajectories,respectively.And then,at sphere-of-influence of earth and target planet,the three individual trajectories are jointed by patched condition.The proposed approach can weaken the nonlinear property of orbit dynamic through several gravity fields,and has the advantages of fine convergence and rapidity.Finally,the validity of this method is verified by taking the earth-mars transfer trajectory as an example.The numerical result demonstrates that,the proposed approach can be used to design the whole interplanetary low-thrust trajectory efficiently.