学术论文

      考虑动力刚化的挠性航天器的动力学建模与分析

      Dynamic Modeling and Analysis for Flexible Spacecraft with Dynamic Stiffening

      摘要:
      本文以含有挠性太阳能帆板的卫星为研究对象,建立了考虑动力刚化效应的刚柔耦合动力学模型,并与传统的线性模型进行了对比.首先,通过Hamilton变分原理建立了考虑动力刚化效应的挠性卫星的姿态运动和结构振动的偏微分方程;之后,通过假设模态法对偏微分方程进行离散,得到离散化后的线性模型和动力刚化模型;最后,给出了某些特定外界激励下两种模型动力学响应的数值仿真结果.仿真结果表明,动力刚化效应将对卫星的柔性结构振动产生较大影响;在一定的外界激励下,采用线型模型的计算结果与动力刚化模型的计算结果之间存在较大偏差.
      Abstract:
      A satellite with flexible solar panels is studied in this paper.The rigid-flexible coupling dynamic model considering stiffening effect is proposed and compared with the traditional linear model.The partial differential equations of the attitude motion and structural vibration of the flexible satellite with considering stiffening effect are firstly derived from Hamilton's principle.Then the linear model and the dynamic stiffening model are obtained by discretizing the partial differential equations using assumption mode method.At last,numerical simulations of the dynamic responses of the two models under certain external excitation are presented.The results show that stiffening effect has a significant influence on the flexible structure vibration,and there will be a lot of deviation between the results computed by the linear model and dynamic model under a certain external excitation.
      作者: 方柳 [1] 刘玉亮 [2] 赵桂平 [1]
      Author: FANG Liu [1] LIU Yuliang [2] ZHAO Gui-ping [1]
      作者单位: 西安交通大学 航天航空学院,机械结构强度与振动国家重点实验室,西安 710049 大连理工大学 航空航天学院,辽宁 大连,116024
      刊 名: 兵器装备工程学报 ISTIC
      年,卷(期): 2017, 38(9)
      分类号: V411.4
      在线出版日期: 2018年1月3日
      基金项目: 国家自然科学基金项目