航天器受迫绕飞构型设计与控制  

Spacecraft forced fly-around formation design and control

作　　者：张冉[1] 殷建丰[2] 韩潮[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]北京空间飞行器总体设计部,北京100194

出　　处：《北京航空航天大学学报》2017年第10期2030-2039,共10页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：针对航天器在轨服务任务对绕飞技术的要求,研究了航天器受迫绕飞构型设计和控制问题。基于C-W(Clohessy-Wiltshire)方程的解析解,提出了双水滴拼接绕飞构型,并将单脉冲或双脉冲受迫绕飞延展至多脉冲绕飞构型设计;推导了伴随航天器初始状态变量与绕飞构型形状参数的关系,得到了4种构型的解析表达式和脉冲控制策略。通过数值仿真算例验证了设计的4种绕飞构型能够实现伴随航天器的慢速绕飞和快速绕飞,比较了不同绕飞构型的燃料消耗和绕飞距离误差。数值结果表明,双水滴拼接绕飞构型总脉冲最小。研究成果完善了航天器受迫绕飞构型设计与控制的相关理论,为工程应用提供参考。In order to meet the requirements of spacecraft fly-around technology in on-orbit service mis- sion, spacecraft forced fly-around formation design and control scheme was investigated. Based on the analytic solution of the C-W（Clohessy-Wiltshire） equations, bi-teardrop formation was proposed. Then multi-impulse fly-around formations were developed after single- or double-impulse formations. The formula between the ini- tial states of following spacecraft and the shape of fly-around formation was derived, and the analytic expres- sions of four fly-around formations and the impulse control scheme were proposed, Simulation results verify that four designed formations could be used in spacecraft slow fly-around and fast fly-around scenarios. The total fuel consumptions and distance errors of different formations were compared. Numerical results show that bi- teardrop formation has the smallest total impulse. The theory of spacecraft forced fly-around formation design and control is improved, and the results provide reference for engineering application.

关 键 词：在轨服务 受迫绕飞 C-W方程 脉冲控制 构型设计 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]