CAJ | 학술논문

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。
이림근공간평류층비정유성충기낭체위연구대상，근거충기결구설계이론대충기낭체결구적최소압차화응력진행계산，건립평류층비정충기낭체결구유한원모형。재모형험증적기출상，채용비선성유한원방법대평류층비정충기낭체결구특성진행방진분석，득도료낭체결구재불동압차화조창재하작용하응력화변형분포급변화규률，병분석료결구가강배치대낭체응력화변형적영향，위평류층비정결구설계제공기술지탱화삼고의거。
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.