Stratospheric airship possesses huge volume; while the thickness of the envelope is much smaller than the length of the airship. Large deformation or even damage can easily take place under a certain exterior load. In order to provide the basis for the strength design of the airship envelope, the circumferential and axial stress equations of the envelope were established under internal and external differential pressures. The overall stress distribution of the envelope under circumferential and axial stresses was analyzed quantitatively through Von Mises stress approach. Then a finite element model of the airship envelope was established. The stress distribution of the envelope was obtained through the nonlinear finite element simulation in ANSYS. The validation of the theoretical equations was verified by the comparison of the theoretical stress values and the simulation results, which provides a reference for the estimate of the envelope stress distribution.%关于飞艇蒙皮强度优化设计问题,平流层飞艇体积巨大,而蒙皮厚度远小于飞艇长度,结构在受载情况下容易发生较大变形甚至破坏.为了给飞艇蒙皮强度设计提供依据,建立了飞艇蒙皮在只受内外压差载荷作用下的环向和轴向应力方程,用Von Mises应力来定量描述蒙皮在环向和轴向应力作用下的整体受力情况.然后建立了飞艇蒙皮的计算模型,通过在ANSYS中进行非线性仿真分析得到蒙皮各点的受力情况,并将理论应力值与有限元仿真结果进行了对比,结果验证了理论方程的有效性,为飞艇蒙皮的应力估算提供参考.
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