小推力航天器逃离太阳系的引力辅助轨迹设计  

Gravity-assist Trajectory Design for Low-thrust Spacecraft Escaping from the Solar System

作　　者：范子琛 成飞[2] 李文龙[2] 霍明英[1] 齐乃明[1] FAN Zichen;CHENG Fei;LI Wenlong;HUO Mingying;QI Naiming(School of Astronautics,Harbin Institute of Technology,Harbin 150001,China;Shanghai Institute of Satellite Engineering,Shanghai 201109,China)

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001 [2]上海卫星工程研究所,上海201109

出　　处：《宇航学报》2024年第7期1032-1039,共8页Journal of Astronautics

基　　金：上海航天技术研究院创新基金(SAST2022046);中国博士后科学基金(2023M740911);黑龙江省博士后基金(LBH-Z23139)。

摘　　要：针对太阳系边界探测,利用形函数轨迹优化算法快速生成连续小推力航天器引力辅助逃离太阳系的三维轨迹,实现在有限燃料条件下的超远距离探测。通过对比有无引力辅助设计的仿真结果,证明了引力辅助技术在逃离太阳系过程中的有效性。仿真结果表明,基于贝塞尔形函数方法的连续小推力轨迹优化算法可以高效地设计出引力辅助逃离太阳系的合理三维初始轨迹,对于初始探测任务的快速设计和分析具有重要意义。For the exploration of the Solar System boundaries,the shape-based trajectory optimization algorithm is used to quickly generate three-dimensional gravity-assist trajectories of continuous low-thrust spacecraft escaping from the Solar System,achieving ultra long range exploration under limited fuel conditions.The effectiveness of gravity-assist technology in escaping the Solar System is demonstrated by comparing simulation results with and without gravity-assist design.The simulation results show that the continuous low-thrust trajectory optimization algorithm based on the Bezier shape-based method can efficiently design a reasonable three-dimensional initial gravity-assist trajectory for escaping from the Solar System.This is of great significance for the rapid design and analysis of initial detection missions.

关 键 词：引力辅助 小推力轨迹设计 逃离太阳系 贝塞尔形函数法 

分 类 号：V476.4[航空宇航科学与技术—飞行器设计]