【作者】 徐彦； 王培栋； 叶谦；

【Author】 XU Yan;WANG Peidong;School of Aeronautics and Astronautics, Zhejiang University;Dongfang College, Zhejiang University of Finance and Economics;

【机构】 浙江大学航空航天学院； 浙江财经大学东方学院；

【摘要】 为了实现航天器结构的大型化和轻质化,空间薄膜结构是理想的技术途径。在大型航天器结构特别是充气太空舱和充气再入缓冲器的柔性热防护中大量应用了层合薄膜,特别是铝-聚合物层合薄膜。本文主要开展铝-聚合物层合薄膜在空间热载荷作用下的褶皱形态数值模拟研究。基于I-DEAS/TMG软件建立热分析数值模型,确定在设计轨道运行的层合薄膜在轨外热流随时间的变化曲线,分析得到层合薄膜的瞬态温度场。基于非线性屈曲有限元分析,发展层合薄膜褶皱三维形态的数值分析方法,预测层合薄膜的热致褶皱三维形态。利用有限元软件ANSYS进行相关数值分析,采用SHELL181层合薄壳单元模拟层合薄膜,考虑薄膜初始几何缺陷和初始预应力作用。基于前述的热致褶皱形态分析方法,得到层合薄膜在轨运行过程中出现的褶皱分布范围和幅度。本文工作将为大型航天器结构的柔性热防护设计提供技术支撑。更多还原

【Abstract】 To design the large and light weight spacecraft structures, space membrane structure is an ideal technology. The laminated membranes especially Al-Kapton laminated membranes are widely used in large aerospace structures, such as inflatable modules and inflatable aerodynamic decelerators. This paper describes the numerical simulation investigation of thermally induced wrinkling in Al-Kapton laminated membranes. Based on the Heat transfer numerical analysis model of established in I-DEAS/TMG software, the change curves over time of orbital heat fluxes on the laminated membranes in the designed orbit were determined and the transient temperature field of the laminated membranes was analyzed.The nonlinear post-buckling analysis method, based on laminated thin-shell elements, is used to simulate the onset, growth and final configuration of wrinkles of Al-Kapton laminated membranes subjected to the thermal loads. The simulations are conducted with the ANSYS finite element package. SHELL181 laminated shell element is used to simulate laminated membranes and the effects of initial geometric imperfectionand initial pre-stress were considered. Based on the analysis method of thermally induced wrinkling for laminated membrane structures, the distribution range and amplitude of the wrinkling in the orbit are obtained. This work will provide technical support for the design of flexible thermal protection of large spacecraft.更多还原