临近空间大型柔性充气囊体结构特性分析

以临近空间平流层飞艇柔性充气囊体为研究对象，根据充气结构设计理论对充气囊体结构的最小压差和应力进行计算，建立平流层飞艇充气囊体结构有限元模型。在模型验证的基础上，采用非线性有限元方法对平流层飞艇充气囊体结构特性进行仿真分析，得到了囊体结构在不同压差和吊舱载荷作用下应力和变形分布及变化规律，并分析了结构加强配置对囊体应力和变形的影响，为平流层飞艇结构设计提供技术支撑和参考依据。
Taking inflatable structures of stratospheric airships as the main study object, the minimum differential pressure and the stress of inflatable structures were computed according to its design theory and a finite element model of inflatable structure for stratospheric airship was established. On the basis of the model verification, nonlinear finite element method was applied to simulate inflatable structural performance so as to obtain the distribution and change laws of the deformations and stresses of inflatable structure with the variations of pressure load and gondola load. The effects of structural reinforcement devices on the stress and deformation of inflatable structure also were evaluated. The simulation results can serve as reference for the structural design of the stratospheric airship.