Chinese Journal of Theoretical and Applied Mechani ›› 2017, Vol. 49 ›› Issue (3): 517-527.DOI: 10.6052/0459-1879-16-358

Special Issue: 力学学报创刊60周年专栏(2017年)

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Yang Zhijun1, Huang Rui1, Liu Haojie1, Zhao Yonghui1, Hu Haian1, Wang Le2   

  1. 1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
    2. China Academy of Launch Vehicle Technology, Beijing 100076, China
  • Received:2016-11-30 Online:2017-05-15 Published:2017-06-16
  • Contact: 10.6052/0459-1879-16-358


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.

Key words:

slender missile|aerodynamic model of reduced-order|recursive Wiener model|flutter boundary|limit cycle flutter

CLC Number: