基于伪谱法的有限推力远程交会轨迹优化  

Optimization of finite thrust Remote Rendezvous Trajectory Based on Pseudospectral Method

作　　者：柳明星[1] 冯彦军[1] 连晓斌 王彦革 LIU Ming-xing;FENG Yan-jun;LIAN Xiao-bin;WANG Yan-ge(Shanghai Institute of Satellite Engineering,Shanghai 201109,China;Shanghai Aerospace Electronic Technology Institute,Shanghai 201109,China)

机构地区：[1]上海卫星工程研究所,上海201109 [2]上海航天电子技术研究所,上海201109

出　　处：《计算机仿真》2025年第2期46-50,共5页Computer Simulation

基　　金：国家自然科学基金(1220228);上海市自然科学基金(23ZR1461800)。

摘　　要：针对末端时间自由的有限连续推力航天器远程交会问题非线性强,计算量大,优化过程复杂,难以得到收敛的数值解的特点,提出了一种基于序列二次规划算法进行求解的远程交会轨迹优化方法。首先建立了末端时间自由的共面轨道航天器远程交会模型,通过高斯伪谱法将该优化模型转化为一组可以送代求解的非线性优化问题,以任务燃料消耗最优作为代价函数,求解得出航天器共轨道面远程交会优化轨迹与推力控制序列。仿真结果表明,上述方法计算速度较快,实时性好,能够准确快速实现远程交会的目标,可为航天器远程交会任务提供一定技术参考。A remote rendezvous trajectory optimization method based on sequential quadratic programming algorithm is proposed to solve the problem of finite continuous thrust spacecraft remote rendezvous with end time freedom,which is characterized by strong nonlinearity,large computational complexity,complex optimization process,and difficulty in obtaining convergent numerical solutions.First,the remote rendezvous model for spacecraft with free terminal time is established.Second,by transforming the model into a set of nonlinear optimization problems that can be iteratively solved through Gaussian pseudospectral method,the optimizing problem is converted into nonlinear programming problem(NLP).Finally,considering the characteristics of large thrust of the spacecraft engine and using the minimum fuel consumption as the cost function,the remote rendezvous trajectory and thrust sequence are achieved by using the algorithm.The simulation results show that the above method has fast calculation speed,good real-time performance,and can accurately and quickly achieve the goal of remote rendezvous.It can provide certain technical references for spacecraft remote rendezvous tasks.

关 键 词：伪谱法 有限推力 远程交会 轨迹优化 

分 类 号：V411.8[航空宇航科学与技术—航空宇航推进理论与工程]