摘要
本文研究卫星帆板展开过程中的撞击问题 ,用子结构方法和单向递推组集方法得到以铰坐标和柔性体模态坐标为系统广义坐标的撞击阶段柔性多体系统的动力学方程 ,由与撞击有关约束方程的Lagrange乘子导出了撞击力的计算公式 ,计算了卫星帆板在撞击过程中撞击力的最大值和卫星姿态角速度的变化规律。计算结果表明 ,对柔性体之间的碰撞 。
In this paper,the contact impact problem of satellite's plates is studied.The substrucure method and forward recursive formulation are used to obtain the equation of motion of flexible multibody system during impact expressed in relative coordinates.The impact force is obtained from the Lagrange multipliers associated with the contact constraints.Time histories of impact force and angular velocity of the satellite are presented.It shows that the angular velocity of the satellite fluctuates during the impact between flexible bodies.
出处
《宇航学报》
EI
CSCD
北大核心
2000年第3期34-38,共5页
Journal of Astronautics
基金
国家自然科学基金重点项目资助
关键词
碰撞锁定
卫星太阳能帆板
展开到位
Satellite's plates\ Substructure method\ Forward recursive formulation\ Impact force\ Angular velocity
