绳系释放时的航天器耦合动力学分析  

Coupling dynamics of spacecraft with deployment of a tether

作　　者：余本嵩[1] 金栋平[1] 庞兆君[1] 

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016

出　　处：《中国科学：物理学、力学、天文学》2014年第8期858-864,共7页Scientia Sinica Physica,Mechanica & Astronomica

基　　金：国家自然科学基金(批准号:50875124;11202094);长江学者和创新团队计划(编号:IRT0968);中国博士后科学基金(编号:2012M521070)资助项目

摘　　要：本文研究了绳系释放对于航天器刚体姿态的影响.基于离散的系绳黏弹性模型,建立了航天器和系绳间刚-柔耦合的时变非线性动力学模型.以Kissel释放控制律为例,研究了系绳自由释放及受控释放时航天器姿态动力学问题,揭示了绳系释放对于航天器本体姿态的影响规律.结果表明,系绳自由释放末的冲击可致航天器旋转,而受控系绳释放使航天器产生绕其局部平衡位置的振荡.航天器初始姿态对绳系航天器的释放动力学具有显著影响.The paper deals with the deployment dynamics of a tethered spacecraft with the consideration of attitude motion. The flexible tether is modeled through a sequence of lumped masses connected by viscoelastic dampers, and the spacecraft as a rigid body. According to Newton＇s law, the time-varying equations of motion of the system for deployment and retrieval are obtained. Then, the attitude dynamics of spacecraft during deployment are numerically investigated based on the Kissel＇s deployment strategy. The results show that the deployment dynamics is greatly dependent on the initial attitude angle of spacecraft. If without control action on tether＇s deployment, the impulse arisen form the velocity jump at the end of deployment will cause the spacecraft to rotate, and an oscillation occurs around the local equilibrium of spacecraft as the Kissel＇s control is applied during deployment of the tether.

关 键 词：刚-柔耦合 航天器姿态 绳系释放 动力学 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]