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为准确描述过失速机动中非定常气动力特性,研究了以非线性微分方程为基本结构的非定常气动建模方法。基于动力学系统建模思想,分析揭示该模型的物理机理,并发展和改进了基于风洞强迫振荡试验的模型参数辨识方法:基于小振幅试验数据,采用线性回归参数辨识方法辨识确定气动模型中特征时间常数等线性参数;基于大振幅试验数据,采用遗传算法全局寻优辨识气动模型中非线性项参数。以带中心体三角翼模型为例进行气动建模与验证,研究结果表明:模型可精确预测不同机动下非定常气动特性;建模方法具有较强的工程可行性。
In order to accurately describe the unsteady aerodynamic characteristics of the stalling maneuver, the unsteady aerodynamic modeling method based on the nonlinear differential equation is studied. Based on the idea of dynamic system modeling, the physical mechanism of the model is revealed and the model parameter identification method based on wind tunnel forced oscillation test is developed and improved. Based on the small amplitude test data, the linear regression parameter identification method is used to identify the aerodynamic model Time constant and other linear parameters. Based on the large-amplitude test data, the global optimization of genetic algorithm is used to identify the nonlinear term parameters in the aerodynamic model. The aerodynamic modeling and verification are carried out with a center-body delta wing model. The results show that the model can accurately predict the unsteady aerodynamic characteristics under different maneuvers. The modeling method has strong engineering feasibility.