大迎角非定常气动参数辨识研究

Unsteady aerodynamic identification of aircraft at high angles of attack

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.