| 飞机大攻角非定常气动力建模与辨识 |
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| 引用本文： | 汪清,蔡金狮.飞机大攻角非定常气动力建模与辨识[J].航空学报,1996,17(4):391-398. |
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| 作者姓名： | 汪清 蔡金狮 |
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| 作者单位： | 中国空气动力研究与发展中心!四川绵阳，621000，中国空气动力研究与发展中心!四川绵阳，621000 |
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| 基金项目： | 国防科技预研跨行业基金资助项目 |
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| 摘 要： | 采用一阶微分方程描述由非线性非定常效应引起的气动力增量 ,从而建立了一种新的飞机大攻角非定常气动力数学模型。研究了模型在缓变运动下的线化形式和动导数表达式。讨论了模型参数的辨识问题。算例证实了所建立的气动力数学模型的正确性和所述模型参数辨识方法的有效性
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| 收稿时间： | 1994-09-15; |
UNSTEADY AERODYNAMIC MODELING AND IDENTIFICATION OF AIRPLANE AT HIGH ANGLES OF ATTACK |
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| Wang Qing,Cai Jinshi.UNSTEADY AERODYNAMIC MODELING AND IDENTIFICATION OF AIRPLANE AT HIGH ANGLES OF ATTACK[J].Acta Aeronautica et Astronautica Sinica,1996,17(4):391-398. |
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| Authors: | Wang Qing Cai Jinshi |
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| Institution: | China Aerodynamics Research and Development Center,Mianyang,Sichuan,621000 |
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| Abstract: | A new mathematical model of unsteady aerodynamics of airplane at high angles of attack is developed, with employment of a one order differential equation to describe the aerodynamic increment caused by nonlinear unsteady effects. The linearized form of the model and the expression for dynamic derivatives are researched. The identification problem of the parameters in the model is discussed. At last, the accuracy of the aerodynamic mathematical model and the effectiveness of the parameter identification method presented in the paper are illustrated in the calculation example. |
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| Keywords: | aerodynamics at high angles of attack unsteady aerodynamics parameter identification |
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