微型扑翼飞行器诱导角与几何攻角的研究

Research on Induced Angle and Geometric Angle of Attack of Flapping-Wing Micro Air Vehicles

摘要:

基于准稳态模型和动量理论,探讨了微型扑翼飞行器诱导角和最佳几何攻角的计算问题。针对高斯-牛顿法求解诱导角方程时存在的不收敛问题,使用能保证计算过程收敛的列文伯格-马夸尔特算法求解,得到实验样机的诱导角为15°。实验样机的实际升力为40g,忽略诱导角后准稳态模型理论升力为46g,而考虑诱导角的理论升力为37g,验证了计算诱导角可以提高准稳态模型预测升力的准确性。基于实验样机翅膀被动扭转的实际,采用最小二乘法计算出实际最佳几何攻角为55°,能有效指导微型飞行器翅膀的设计,从而提高飞行器最大升力和飞行效率。

Abstract:

Based on the quasi-steady-state model and momentum theory, the calculation of the induced angle and the optimal geometric angle of attack of the flapping-wing micro air vehicle was discussed. Aiming at the non-convergence problem of the Gauss-Newton method in solving the induced angle equation, the Levenberg-Marquardt algorithm was used to guarantee the convergence of the calculation process, and the induced angle of the experimental prototype is obtained as 15°. The practical lift of the experimental prototype is 40g, while after ignoring the induced angle, the theoretical lift of the quasi-steady-state model is 46g, and the theoretical lift considering the induced angle is 37g. It is verified that calculating the induced angle can improve the accuracy of the quasi-steady-state model for predicting lift. According to the actual linear twist of the wing, the least square method is used to calculate the actual best geometric angle of attack at about 55°, which can effectively guide the design of the wing, thereby improving the maximum lift and flight efficiency of the flapping-wing micro air vehicles.