针对现有模型在非定常气动参数辨识中存在的局限性，该文对大迎角机动过程非定常气动特性进行了研究，提出了一种建模方法。该方法结合物理机理，以广义气动导数模型为基础，受到Wiener模型建模思想的启发，建立了动态特性和静态特性分解的模块化级联模型。通过平方相关系数评价各模型项对非定常特性的贡献，确定最终模型结构，并给出了参数估计中相关的数据处理方法。用类F-22模型的风洞试验数据验证了提出的辨识方法，结果表明：模型辨识精度高，相对误差可控制在5%以内，可以有效地描述工程中非定常气动参数。
Existing models cannot accurately identify aircraft at high angles of attack due to the unsteady aerodynamic characteristics high angle of attack flight. This paper presents a model using a dynamic block with a static block based on a general aerodynamic derivatives model, which was inspired by the modelling structure of the Wiener model. The model identification is then based on a squared correlation coefficient that estimates the contribution of each model term. The data processing procedure for the parameter estimations is given. Wind tunnel tests with a model similar to an F-22 are used to verify the method. The results show that the method is able to accurately identify the unsteady aerodynamic parameters with a relative error below 5%. The model can effectively describe the unsteady aerodynamic parameters.
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