为了研究飞艇囊体结构的力学性能，建立了考虑裁切效应的囊体缩比模型.首先进行了织物膜材的双轴拉伸试验，根据试验结果拟合出材料力学参数的应力响应面并编写了材料模型子程序.利用Abaqus模拟了囊体裁切过程，建立了飞艇囊体初始构型的有限元模型，并对囊体充气过程进行了数值模拟.最后设计并制作了飞艇缩比模型并进行充气试验，测量了不同内压下膜面的变形特征.结果发现：考虑裁切效应得到的囊体初始构型和理想回转体模型存在明显的差异；裁切模型膜面变形最大值误差在12%以内，并且随着内压的增大，模型分析误差逐渐减小；裁切效应在飞艇精细化建模分析中具有不可忽略的作用.
In order to study the structural mechanical properties of the airship, a reduced scale airship model considering the cutting pattern effect was established. The biaxial tensile test of woven fabrics was carried out firstly. According to a series of biaxial tensile tests, the stress response surface of the mechanical parameters of envelop material was fitted and a material model subroutine was prepared. Based on the simulation of the cutting process with Abaqus, the finite element model of the initial configuration was established and the inflation process of the model was numerically simulated. Finally, the reduced scale airship model was designed and fabricated to perform the inflation test, and the deformation characteristics of the envelop under different internal pressures were measured. Results showed that there was an obvious difference between the initial configuration of the airship considering cutting effect and the ideal rotory model. The error of the gore’s maximum deformation of the cutting model was within 12% and decreased with the increase of the internal pressure. The cutting effect had a non-negligible role in the airship fine-modeling analysis.
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