一种立方星编队重构多脉冲机动规划方法  

A Multi-impulse Maneuver Planning Method for Cubesat Formation Reconfiguration

作　　者：徐根 刘幸川 陈丹鹤 廖文和[1] XU Gen;LIU Xingchuan;CHEN Danhe;LIAO Wenhe(School of Mechanical Engineering,Nanjing University of Science&Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《宇航学报》2022年第11期1533-1543,共11页Journal of Astronautics

基　　金：国家自然科学基金青年基金项目(51905272)。

摘　　要：针对立方星轨道机动能力约束,提出一种基于相对轨道根数动力学模型的多脉冲机动规划算法。对于相对轨道面内各分量之间的控制耦合问题,基于“先控制相对形状、后修正迹向距离”的策略,提出了满足速度增量约束的多脉冲机动规划算法;分析了近地轨道J 2摄动和大气阻力摄动对相对轨道的影响,并基于线性化的状态转移模型提出了迭代优化策略,以降低立方星在摄动影响下的轨道机动误差。仿真结果表明,所提出的多脉冲机动规划算法在不同任务条件下均可获得有效的机动规划,迭代优化策略可有效地提高终点位置的精度,在基于高精度轨道递推搭建的任务仿真中也验证了算法的有效性,可用于立方星编队构建和重构任务。Aiming at the constraints of cubesat orbital maneuverability,a multi-impulse maneuver planning algorithm based on relative orbital elements is presented.For the control coupling among the in-plane elements,the algorithm is proposed according to the strategy of“controlling the relative shape first and correcting the along-track distance later”,which satisfies the velocity increment constraint.In addition,the effect of J_(2) perturbation and atmospheric drag perturbation is analyzed,and an iterative optimization strategy is proposed based on the linearized state transition model to reduce the orbital maneuver error.The simulation results show that the proposed multi-impulse maneuver planning algorithm can obtain effective maneuver planning under different task conditions,and the proposed iterative optimization strategy can effectively improve the accuracy of terminal position.The algorithms are verified to be effective in the mission simulation based on high-precision orbit propagation,and can be used in cubesat formation construction and reconfiguration tasks.

关 键 词：立方星编队 相对轨道根数 多脉冲机动规划 迭代优化 

分 类 号：V448.234[航空宇航科学与技术—飞行器设计]