飞机大迎角机动非线性气动力模型的辨识

Identification of Nonlinear Aerodynamic Model for Maneuvering Aircraft at High Angle of Attack

给出一种基于最大似然辨识的方法，用以分析飞机模型大迎角大幅值强迫简谐振动获得的气动力和力矩数据。在泛函分析和非定常气动力线性理论的基础上，通过合理的简化建立了能够包括气动力动态失速和涡流破裂及显著气动迟滞效应的非线性气动力模型表达式。并应用飞机模型的试验数据验证了该方法的计算结果。实际计算结果表明该非线性气动力模型能够较为精确地计算飞机模型大幅值迎角简谐振动产生的气动力响应。

A method based on Maximum likelihood identification is developed to analyze the force and moment data obtained in large amplitude forced oscillation tests at high angles of attack.On the basis of functional analysis and the linear aerodynamic theories,the aerodynamic models including in dynamic stall,vortex breakdown,hysteresis effect are built up by rational simplified assumption.Using a set of aerodynamic respon ses data to harmonic motions at different frequencies demonstrates the results of the method.It is shown the nonlinear aerodynamic model given by the article can accurately calculate aerodynamic responses of aircraft models in large amplitude forced oscillation tests at high angles of attack.