【摘要】 基于柔性机构设计的变形翼能够在飞机航行过程中随飞行条件的变化改变其形状，从而有效地改善飞机的气动性能并降低噪声。目前柔性机构的设计大多采用基于线弹性材料的拓扑优化方法，该方法设计的柔性机构变形较小，不能很好地满足机翼大角度变形需求。为解决上述问题，采用基于超弹性材料的拓扑优化方法来设计大变形机翼前后缘内部柔性驱动机构。另外，将机翼前缘蒙皮等效成多组悬臂梁模型，结合遗传算法设计变截面厚度蒙皮，利用弯曲成形法得到初始前缘蒙皮形状。根据机翼前后缘设计区域的特点，分别优化设计了合理的驱动力位置及大小。最后，根据拓扑优化所得的结果，设计制作变形翼样机并测试其变形效果。试验结果表明,变形翼样机具有良好的连续光滑大变形能力。更多还原

【Abstract】 The deformable wing based on flexible mechanism can change its shape with the change of flight conditions so as to effectively improve the aerodynamic aircraft performance and reduce the noise. At present, the topology optimization method based on linear elastic material is mostly used in the design for flexible mechanism. The deformation of flexible mechanism designed by this method is small, which cannot make the wing achieve large deformation angle. In order to solve the problems above, the topology optimization method based on hyperelastic materials is used to design the internal flexible mechanism of the leading edge and trailing edge. In addition, when the wing leading edge skin is equivalent to multiple groups of cantilever beam models, the skin with variable section thickness is designed combined with genetic algorithm, and the initial leading edge skin shape is obtained by bending forming method. According to the characteristics of the design area in the wing, the reasonable driving force position and size are optimized. Finally, according to the results of topology optimization, the prototype of deformable wing is designed and manufactured, and its deformation effect is tested. The experimental results show that the prototype of deformable wing has good ability of large deformation and continuous deformation.更多还原