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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。
In order to further study the aerodynamic model and identification method of complex flow field, “in-phase” and “anti-phase” derivatives were obtained by dynamic single pitch and single roll test data of conventional flying wing layout aircraft. Based on the unsteady mathematical model established by the state space method, the model parameters are identified by two-step linear regression, and the time-constant distribution of the characteristic with the error limit is given. Comparison between the results of mathematical model identification and the experimental data of large-amplitude large-angle motion shows that the results of this model are basically consistent with those of experimental aerodynamic data and can reflect the nonlinear and unsteady characteristics of the model at high angle of attack.