含多间隙柔性可展帆板动力学建模及仿真  

Dynamic Modeling and Simulation of a Flexible Deployable Solar Array with Multiple Clearances

作　　者：邱雪松[1] 任志博 桂朋 魏亚坤 QIU Xue-song;REN Zhi-bo;GUI Peng;WEI Ya-kun(School of Mechanical Engineering,Yanshan University,Qinhuangdao 066004,Chin)

机构地区：[1]燕山大学机械工程学院,秦皇岛066004

出　　处：《宇航学报》2018年第7期724-731,共8页Journal of Astronautics

基　　金：国家自然科学基金(51305384)

摘　　要：为研究柔性和多级铰链间隙对帆板展开过程动力学特性的影响,以月球车两级往复可展太阳帆板为研究对象,采用修正Coulomb模型表述摩擦力,通过接触碰撞力描述间隙,运用有限元法进行帆板柔性化,进而建立多间隙-柔性耦合的动力学模型。采用变步长伦哥库塔法进行数值求解,模拟帆板展开过程,分析了多间隙和柔性对帆板质心加速度、铰链间隙碰撞力等参数的影响。结果表明,在保证展开机构刚度要求的前提下,帆板柔性可补偿因铰间隙引起的加速度波动,减弱间隙处碰撞的剧烈程度,减小碰撞力幅值,进而改善帆板展开机构的动态特性。研究结果可用于指导月球车两级往复可展太阳帆板等同类型的可展机构动态优化设计。In order to research the influence of the flexible and hinges clearance on the dynamic performance of a solar array during deployment,a lunar rover with a repeatable an unfolded two-stage solar array is used as the research subjects.The modified Coulomb model is taken to describe the friction and to express the clearance in terms of collision force. The finite element method is used for the flexible pannels. A dynamic model which makes the multi-clearance flexible coupling is established. In this paper,the Runge-Kutta method with variable step is applied to the numerical simulation of the deployment of the panel. The effects of the multiple clearances and flexibility on the acceleration of the mass center and the impact force of the hinges clearance are analyzed. The results show that under the premise of ensuring the stiffness requirements of the launching mechanism,the appropriate flexibility of the array can compensate acceleration fluctuation caused by the hinges clearance,weaken the sharp degree of the collision at the clearance and reduce the impact force amplitude,thereby improving the dynamic characteristics of the deployable mechanism. The results can be used to guide the dynamic optimization design of the flexible deployable panels with multiple clearances.

关 键 词：间隙 柔性 多体动力学 可重复展开帆板 

分 类 号：V442[航空宇航科学与技术—飞行器设计] V476.3