仿蝉翅膀气动力及扭矩特性的分析

Analysis of force and moment characteristics of bionic cicada wing

为仿蝉微飞行器(MAV)设计了一款翅展33 mm的翅膀,并采用准静态模型对该翅膀的气动力及扭矩特性进行了仿真分析;同时还分析了以上特性与攻角幅度之间的关系.力特性仿真结果表明,在超前模式典型拍动参数下,一对翅膀能提供26 g左右的平均升力,足于平衡质量为十几克的仿蝉微飞行器;同时提供合适的剩余升力供机动.扭矩仿真结果表明,翅膀转动模式对转动扭矩的影响很大,而对拍动扭矩影响较小;攻角幅值对转动和拍动扭矩的影响均比较大,但是超前模式下的转动扭矩却几乎不受攻角幅值的影响.为检验仿真结果的可信度,与相关文献类似实验的测量数据进行了比较.结果表明,仿真所得气动力曲线与相比较的实验结果曲线形状相似,特征点位置和幅度吻合较好.

A simplified 33 mm wing was designed for the cicada-like micro aero vehicle （MAV）. Analyses and simulations of both instantaneous and average force and moment characteristics were carried out in typical wing rotation models with quasi-steady blade elements model, and the functions of these characteristics to the amplitude of the attack angle were investigated as well. The results showed that one pair of this wing can provide 26 g lift force in the advanced model, which not only was enough to support the vehicle itself, but also could provide appropriate force for maneuver. Moment simulation results showed that the rotation model of wing affected the rotational moment very much, but affected the stroke moment very little, and the amplitude of the attack angle affected both the rotational and stroke moment very much, except the rotational moment in the advanced model. Comparison between the proposed simulation results and the experimental results of relative articles was put forward to check the validity. The result showed that the figures were quite similar to each other, and both the positions and amplitudes of corresponding key points matched very well.