航天器受迫绕飞构型设计与控制

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。

Spacecraft forced fly-around formation design and control

In order to meet the requirements of spacecraft fly-around technology in on-orbit service mission,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 initial states of following spacecraft and the shape of fly-around formation was derived,and the analytic expressions 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 biteardrop 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.