筒式偏心在轨分离角速度抑制方法  

Angular velocity depressing method of constrained and centroid biased on-orbit separation

作　　者：蒋超[1] 王兆魁[1] 张育林[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《航空学报》2015年第10期3382-3392,共11页Acta Aeronautica et Astronautica Sinica

基　　金：国家"863"计划(2012AA120603)~~

摘　　要：筒式偏心在轨分离是一类特殊的在轨分离问题,小卫星偏心安装而产生的分离力矩将导致分离角速度,进而影响小卫星的分离指向精度,甚至导致释放平台姿态失稳。而常规的姿态大角速度机动、姿态快速稳定控制方法难以在小卫星出筒前的极短时间内完成分离角速度抑制。因此,进行了卫星筒式偏心在轨分离动力学分析,基于分离角速度的产生,提出了抑制分离姿态干扰的前馈控制力矩法和角速度预偏置法。在此基础上,推导了关键控制参数的近似计算公式,给出了控制量的优化求解方法,并分析了控制干扰因素对抑制结果的影响。最后,通过仿真算例分析,对比验证了两种抑制方法的有效性,并给出了其工程应用的建议。The constrained and centroid biased on-orbit separation is a special kind of on-orbit separation problems.The offset between separation force acting line and the centroid of the release platform brings separation moment and leads to angular velocity.Then both the pointing precision of small satellite and the attitude stabilization of the release platform will be disturbed by on-orbit separation.However,it is difficult to depress the disturbances in quite a short time by general fast attitude maneuver or stabilizing methods.So,a method of angular velocity depressing of the constrained and centroid biased onorbit separation is researched.With the analysis of the separation dynamics,the feed-forward moment control method and the angular velocity offset method are presented.The calculation formulas of control parameters are derived and optimized.The influences caused by implementing factors are analyzed as well.Finally,the two angular velocity depressing methods are proved to be effective by numerical simulations,along with some suggestions in engineering application.

关 键 词：在轨分离 动力学 指向精度 前馈控制 非线性 脉宽脉频(PWPF)调制 

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]