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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2018, Vol. 39 ›› Issue (3): 221539-221539.doi: 10.7527/S1000-6893.2017.21539

• Solid Mechanics and Vehicle Conceptual Design • Previous Articles     Next Articles

Panel flutter of variable stiffness composite laminates in supersonic flow

OUYANG Xiaosui, LIU Yi   

  1. School of Aerospace Engineering and Applied Mechanics, Tongji University, Shanghai 200092, China
  • Received:2017-06-21 Revised:2017-12-07 Online:2018-03-15 Published:2017-12-07
  • Supported by:
    National Level Program

Abstract: Panel flutter behaviour of variable stiffness laminates in high supersonic flow is of great interest in design. The nonlinear flutter behaviour of variable stiffness composite laminates with curvilinear fibers in high supersonic flow is investigated, and effects of boundary condition and ply orientation are studied. The classical lamination theory along with the von-Karman large deflection strain-displacement relationship is used for structural modeling, and the linear piston theory is used for aerodynamic modeling. The aeroelastic model of panel flutter is established based on the principle of virtual work and the finite element method, which is then solved by Newmark method. The flutter behavior under different boundary conditions and ply orientation are obtained. The results show that the critical dynamic pressure decreases as the path orientations in the center and vertical edges of a plate (T0 or T1) increases, and the limit cycle amplitude increases as T0 or T1 increases under the same dynamic pressure. It also turns out that the designability of composite laminates can be improved by using curvilinear fibers, the flutter behaviour of variable stiffness composite laminates can be changed by varying the fiber orientation.

Key words: nonlinear panel flutter, supersonic flow, variable stiffness composites, curvilinear fiber laminates, variable angle tow

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