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

作　　者：许常兵 张卫平[1] 沈一博 牟家旺 陈子豪 XU Changbing;ZHANG Weiping;SHEN Yibo;MOU Jiawang;CHEN Zihao(National Key Laboratory of Science and Technology on Micro Nano Fabrication;Department of Micro Nano Electronics,Shanghai Jiaotong University,Shanghai 200240,CHN)

机构地区：[1]上海交通大学微米纳米加工技术国家级重点实验室,上海200240 [2]上海交通大学电子信息与电气工程学院微纳电子学系,上海200240

出　　处：《半导体光电》2021年第2期207-211,共5页Semiconductor Optoelectronics

基　　金：教育部基金项目(6141A02022627);上海市科委项目(19511104202,19DZ2291103);预研基金项目(1816311ZT005020)。

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。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 40 g,while after ignoring the induced angle,the theoretical lift of the quasi-steady-state model is 46 g,and the theoretical lift considering the induced angle is 37 g.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.

关 键 词：微型扑翼飞行器 空气动力学 列文伯格-马夸尔特算法 最佳几何攻角 

分 类 号：TP212[自动化与计算机技术—检测技术与自动化装置]