黄锐

个人信息Personal Information

教授 博士生导师

招生学科专业:
力学 -- 【招收博士、硕士研究生】 -- 航空学院
航空宇航科学与技术 -- 【招收硕士研究生】 -- 航空学院
机械 -- 【招收博士、硕士研究生】 -- 航空学院

主要任职:飞行器流体物理全国重点实验室学术委员会委员,中国振动工程学会理事,中国航空学会变体飞行器分会、中国振动工程学会模态分析与试验专委会、非线性振动专委会等四个专业委员会副主任委员/委员

其他任职:SCI期刊《Acta Mechanica Sinica》期刊责任编辑、《力学进展》、《振动工程学报》、《力学学报》和《动力学与控制》等四种期刊的青年编委

性别:男

毕业院校:Nanjing University of Aeronautics and Astronautics

学历:南京航空航天大学

学位:工学博士学位

所在单位:航空学院

联系方式:ruihwang@nuaa.edu.cn

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Aeroelastic Model of Reduced-Order for a Slender Missile

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所属单位:航空学院

发表刊物:Lixue Xuebao

摘要:In the design phase of slender missiles, it is essential to predict their aeroelastic/aeroservoelastic behaviors accurately. The accurate prediction, however, is faced with the tough problem of CFD for the aerodynamic loads on slender missiles. How to establish the aerodynamic models of reduced-order is the key technology to break through the bottleneck in the transonic aeroelastic analysis and control of the slender missiles. Although the aerodynamic reducedorder methods have made important progress in predicting the aerodynamic loads and aeroelastic response of the twodimensional airfoil, still there are few research reports about the aerodynamic reduced-order models of the more complex airplane models. In this study, the recursive Wiener model of reduced-order is constructed for the aerodynamic loads on a slender missile according to the training data of CFD, while the parameters of the model can be estimated via the predictorbased subspace identification algorithm and Levenberg-Marquardt algorithm. The recursive Wiener model of reducedorder can be integrated with the finite element model of the missile structure so that the aeroelastic/aeroservoelastic model of reduced-order is established for the missile. The accuracy of the aeroelastic models of reduced-order is tested under different Mach number in the numerical simulations. The numerical simulations show that the aeroelastic models of reduced-order can accurately predict the unsteady aerodynamic loads and the aeroservoelastic frequency response of the slender missile model under different flight conditions. © 2017, Editorial Office of Chinese Journal of Theoretical and Applied Mechanics. All right reserved.

ISSN号:0459-1879

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发表时间:2017-05-18

合写作者:杨执钧,F70206622,赵永辉,70200091,Wang, Le

通讯作者:黄锐