伴随卫星的燃料-时间优化回收  

Fuel-Time Optimal Rendezvous of an Inspector Satellite to its Master

作　　者：张健[1] 戴金海[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《宇航学报》2007年第1期167-170,208,共5页Journal of Astronautics

基　　金：武器装备预研重点基金项目资助(9140A20050106KG0168)

摘　　要：伴随卫星回收是伴星应用中的一项主要技术。航天任务需求对伴星回收问题不仅提出了最省燃料要求,而且提出了最小时间要求。本文设计了一条稳定的燃料-时间优化回收轨道。从相对运动的Hill方程出发,给出伴星回收问题描述,阐述回收轨道设计思想及稳定回收条件,提出一种有效的螺旋式回收策略,探讨参数确定方法,并对回收轨道的特点和稳定性进行分析,最后研究了燃料消耗量与回收时间及初始相位的关系。仿真结果表明,利用螺旋回收策略,可以保证伴随卫星快速、稳定回收,且能在燃料消耗量与回收时间之间寻求最佳折衷。The rendezvous of an inspector satellite to its master is one of the key techniques in formation flying. The diversity of the space missions demands minimization of both fuel and time. A stable time-fuel optimal spiral orbit for the rendezvous of an inspector satellite is put forward. Descriptions of the rendezvous problem based on Hill＇s equation are given, and the design intents and prerequisites of the transfer orbit are expounded, Then an effective spiral rendezvous control scheme is raised, and its characteristics and stability is discussed, At last, the tradeoff between fuel cost and rendezvous time and initial phase is investigated, Simulation results show that the spiral control sheme is efficient and feasible. It can accomplish rendezvous effectively, and can gain tradeoff between fuel and time.

关 键 词：伴随卫星 相对轨道控制 燃料-时间优化 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]