太阳翼展开过程中锁定冲击载荷研究（英文）

摘要

针对一类典型太阳翼,采用NASTRAN和ADAMS软件建立了太阳翼展开锁定通用分析模型;提出了一种改进的铰链建模方法,能够考虑铰链的所有重要刚度系数;最后,研究了有限元模型导入柔性多体模型的模态数、计算步长、铰链刚度和模态阻尼等参数变化对锁定冲击载荷的影响。通过分析可知,计算时需选取足够多的模态数及足够小的计算步长,还要采用较小模态阻尼,以得到冲击载荷的保守设计值。此外,地面试验得到多组刚度测试结果时,应选取最大刚度试验值,以得到保守结果。研究表明,文章采用的太阳翼展开锁定模型能够得到更准确的冲击载荷结果,并易于实施。%A common deployment and latch-up analysis model for a typical solar wing is built,which combines the FE（finite element） models with NASTRAN and the multibody deployment and latch-up model with ADAMS.An improved method is presented to build the hinge models,which introduces all the important stiffness parameters of hinges.Finally the effects of certain computation parameters on latch-up impact loads are investigated,including：（a）the number of modes translated from FE model to multibody model,（b） analysis step size,（c） stiffness of the hinge and（d） modal damping ratio.The results show that an adequate number of modes and a small step size should be considered in order to get a reasonable result,and that the smaller damping ratio is recommended to be applied in the computation in order to gain conservative design loads.Besides,if various hinge stiffness values are obtained in the ground test,the biggest one should be chosen to get a conservative impact response.It is concluded that the general deployment and latch-up analysis model for solar wings presented in this paper can obtain more accurate impact results and be easily applied.