针对某型无人机复合材料尾翼轻量化问题，基于Hashin失效准则建立尾翼有限元模型，获得纤维增强复合蒙皮的损伤因子。在原设计尺寸基础上，以复合蒙皮综合失效指标、肋板屈服应力、尾翼最低阶屈曲模态因子等约束条件为前提，建立以复合材料铺层厚度、角度等因素为设计变量的尾翼质量优化数学模型，获得尾翼轻量化设计方案。与初步方案对比分析，优化后尾翼质量减少32.2%。
For the lightweight problem of composite tail of an unmanned aerial vehicle,the finite model of the tail was built based on Hashin failure criterion,the damage factor of the fiber-reinforced composite wing-covering was obtained. On the basis of the originally designed size and the constraint conditions such as comprehensive failure indicator of composite wing-covering,yield stress of ribs,lowest bulking mode factor of the tail,etc,the optimized model for reducing the weight of tail was built,in which the design variables consist of ply thickness,ply orientation angular and so on,the lightweight design scheme of the tail was established. The weight of the optimized tail is decreased by 32.2%in comparison with the initial design.
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