飞机大攻角空间机动气动力建模研究

Aerodynamic Modeling of Spatial Maneuvering Aircraft at High Angle of Attac

准确的气动力模型是大攻角机动仿真与控制等飞行动力学问题研究的基础。针对纵向运动建立的非线性非定常气动力微分方程模型扩展应用于一般空间运动形式,在分析大攻角非定常流动机理和试验数据的基础上,发展了一种多自由度非线性非定常气动力数学模型,并探讨了模型辨识和参数估计问题。用全机构形的大攻角动态风洞试验数据对模型进行的验证表明所发展的气动力模型能够描述大攻角气动力主要的非线性和非定常特性。

Accurate aerodynamic models are necessary for researches on flight dynamics issues such as simulation and control of high angle-of-attack (AOA) maneuvers. The differential equation model of nonlinear unsteady aerodynamics, which has been set up for longitudinal maneuvers, is expended to general spatial maneuvers. Based on the analyse of high AOA unsteady flow mechanism and experiment data, a mathematical model of multi degree-of-freedom nonlinear unsteady aerodynamics is developed. Methods of model identification and parameter estimation are discussed. The model is validated by using dynamic wind-tunnel experiment data of aircraft configurations at high AOA. It is shown that the developed aerodynamic model can accurately describe the nonlinear and unsteady characteristics of high AOA aerodynamics.