摘要
针对小推力轨道设计中任务窗12参数具有范围跨度大、非连续性强、对设计结果影响显著等特点，提出了一种基于多冲量能耗估算的任务窗口搜索方法。该方法基于多冲量轨道和小推力轨道的能耗一致性，先由朗伯特两冲量轨道经过数次迭代扩展快速获得多冲量轨道，再通过多冲量轨道能耗估算对任务区间进行全局栅格搜索，最终得到任务窗口的可行区域。仿真结果表明：1）该方法同时适用于交会和飞越任务；2）同朗伯特两冲量相比，它与小推力轨道能耗的一致性更强；3）同Sims和Flanagan最优多冲量相比，计算时间缩短了1～2个量级，计算效率显著提高。地球一火星交会任务的仿真应用表明，该方法只需8．59S即可获得任务窗口的可行区域，进而快速给出小推力最优转移轨道，验证了该方法的有效性。
A mission window search approach was proposed for the low-thrust mission based on the multi-impulse energy estimation. The multi-impulse transfer, which can be extended rapidly from the Lambert＇ s bi impulse solution within several iterations, was employed to effectively substitute for a low-thrust trajectory design. Through grid search of multi-impulse transfers, the feasible regions of the mission window were obtained. Numerical results show that： 1） the approach is suitable for both rendezvous and flyby missions; 2） its consistency with low-thrust transfer in energy consumption is better than the hi-impulse strategy; 3） its computational time is 1~2 orders of magnitude lower than that of Sims and Flanagan＇s approach. Its application to an Earth-Mars rendezvous mission verified its validity. The feasible regions were generated within 8.59 s, which can be readily used to generate optimal low-thrust trajectories.
出处
《中国空间科学技术》
EI
CSCD
北大核心
2014年第4期1-7,38,共8页
Chinese Space Science and Technology
关键词
多冲量
小推力
转移轨道
朗伯特问题
能耗估算
深空探测
Multi impulse
Low-thrust
Transfer orbit
Lambert＇s problem
Energy estimation
Deep space exploration
