飞翼布局飞行器大迎角非定常气动建模

Unsteady aerodynamic modelling based fly-wing configuration at high AOA

为进一步研究复杂流场气动力模型和辨识方法,通过常规飞翼布局飞行器动态单独俯仰和单独滚转试验数据获得"同相"和"反相"导数。在采用状态空间法建立非定常数学模型的基础上,利用两步线性回归辨识出模型参数,给出带有误差限的特征时间常数分布。数学模型辨识结果与大迎角大振幅运动的试验数据对比表明,该模型建模结果基本上与试验气动数据变化一致,能够反映模型大迎角时的非线性和非定常特性,具有可用性。

For searching aerodynamic model of the complex flow field and various identification methods, a wind tunnel experiment on the traditional fly-wing configuration SACCON included oscillatory tests in pitch and roll. According the experimental data, the ＂in-phase＂ and ＂out-of-phase＂ aerodynamic deriva- tives have been calculated. An unsteady mathematical representation has been built using state-space model, then the two-step linear regression method is taken for identification of the model parameters esti- mation and given the characteristic time constants with their standard square deviations. There is a good agreement between mathematically predicted and experimental aerodynamic derivatives obtained in the large amplitude forced oscillatory tests, and it fully proves model＇ s applicability simulating the unsteady and nonlinear effects of the model at high AOA.