摘要
分析了伸展单元的几何结构及动力学特点 ,引入与伸展运动有关的广义伸展坐标 ,提出滑移伸展单元的运动学描述方法 ,基于 Lagrange原理 ,建立了这类飞行器的动力学模型 ,最后仿真研究了这类系统独特的动力学行为。
The geometrical structure and dynamic characteristics of a sleeve deployable unit are analyzed, a kind of general deploying coordinate is posed and a new method to describe the motion of a flexible sleeve deployable unit is put forward. The dynamic model of this kind of spacecraft is established based on Lagrange principle and computer simulation is executed to predict the dynamic behavior.
出处
《导弹与航天运载技术》
2000年第2期23-28,共6页
Missiles and Space Vehicles
基金
航天863高技术空间站领域项目
