摘要
针对柔性航天器振动影响飞行器姿态稳定性和精度。为了解决上述问题,提出了多柔体航天器的动力学建模。首先,根据工程实现的假设振型法,采用拟坐标拉格朗日方程,推导出带有刚体模态的二阶系统刚柔耦合动力学模型,其中,为了减少模型计算量,通过坐标变换将刚体模态和柔性模态解耦,利用一种刚体模态解耦的二阶不稳定系统的模型降阶方法,并对航天器多柔体系统动力学方程进行了仿真分析,结果飞行姿态稳定,满足了精度要求,表明了动力学建模与模型降阶法的有效性和正确性。
The dynamics modeling and model reduction of flexible multibody spacecraft are concerned.Firstly,the motion equation and linearization equation of multibody system are derived based on Lagrangian approach in terms of quasi-coordinates based on assuming mode method.Then,in order to decrease computation,a novel model reduction of unstable second order systems is developed with respect to the equations of flexible spacecraft,which is based on decouple of rigid and flexible body mode.Finally,the rigid-flexible couple property and the precision of model reduction are investigated.The simulation results demonstrate that the suggested approach is valid and efficient compared with other model reduction.
出处
《计算机仿真》
CSCD
北大核心
2011年第6期80-83,108,共5页
Computer Simulation
关键词
多柔体动力学
航天器动力学建模
模型降阶
Flexible multibody dynamics
Spacecraft dynamics modeling
Model reduction
