Abstract: 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.

Key words: aerodynamics, aerodynamic modeling, differential equation model, high angle of attack, model identification, parameter estimation