【摘要】 为完成快速部署无人机充气机翼设计与分析，考虑翼型重合程度、蒙皮质量及加工工艺等因素对充气机翼设计的影响，对充气机翼进行优化设计。结合柔性薄膜理论，建立充气悬臂机翼的等效梁模型，提出一种充气机翼蒙皮应力计算及分析方法。对不同内外压差、气动载荷下的蒙皮应力分布及机翼充气压差对临界气动载荷的影响进行分析。研究结果表明：蒙皮弦向应力极值出现在机翼中部和后缘气室，而展向应力极值出现在机翼上下翼面翼根处，这可为充气机翼的优化设计及强度设计提供必要的参考依据。更多还原

【Abstract】 In order to complete the design and analysis of the inflatable wing of rapid deployment unmanned aerial vehicle(UAV), considering the influence of airfoil overlap degree, skin mass and processing technology on the design of the inflatable wing, the inflatable wing was optimized. Based on the flexible membrane theory, the equivalent beam model of inflatable cantilever wing was established, and a method for calculating and analyzing the skin stress of inflatable wing was proposed. The skin stress distribution under different internal and external pressure differences and aerodynamic loads was analysised. The influence of the wing charging pressure difference on the critical aerodynamic load was analyzed. The results show that the tangential stress extreme value of skin appears in the middle and trailing edge air chamber of the wing, while the spanwise stress extreme value appears at the root of the upper and lower wing surface of the wing, which provides reference for the optimization design and strength design of the inflatable wing.更多还原