对气动力学建模精度的测试研究，有助于进一步设计仿鸟扑翼飞行控制器和对系统运动进行稳定性分析。传统各向同性气动力系数建模方法精度不足，很难用于仿鸟扑翼飞行器试验样机气动力性能的定量预报。通过对不同刚度弹性平板机翼气动力测试，对基于伪稳态气动理论的扑翼气动力建模精度进行了分析。基于飞行器机体位置固定条件下静态扑翼气动力的测试结果，将气动力解析计算模型的气动力系数进行修正，修正后的气动力系数考虑了弹性平板翼弦向刚度且展现出各向异性的特征。通过对试验样机进行拉杆动态飞行测试，验证了修正后扑翼气动力建模方法的精度和有效性。所述工作对开展仿鸟扑翼飞行器优化设计和加快试验样机改进具有参考价值。

The test of aerodynamic modeling accuracy is helpful in the further design of the controller of bird-scale flapping-wing vehicles and the analysis of motion stability of the system. The traditional modeling method based on isotropic aerodynamic coefficients is not accurate enough to quantitatively predict the aerodynamic performance of experimental prototypes of bird-scale flapping-wing vehicles. The accuracy of the aerodynamic modeling of the flapping wing based on the pseudo steady state aerodynamic theory is tested by testing and analyzing the aerodynamic forces of the elastic flat wings with different stiffness. Based on the static aerodynamic test results of the flapping wing with fixed body position，the aerodynamic coefficients in the analytical calculation model are modified. The revised aerodynamic coefficients take into account the chordal stiffness of the elastic flat wing and show anisotropic characteristics. The accuracy and effectiveness of the modified flapping wing aerodynamic modeling method are verified by dynamic flight test of the experimental prototype. The above work has reference value for to the optimization design of flapping-wing vehicles and the improvement of experimental prototype.