STUDY ON BENDING-TORSION FLUTTER OF WING OF A FULL COMPOSITE AIRCRAFT

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MEHRDAD SHOKRIEH MAHMOUD; TAHERI BEHROUZ F.A.

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Paper Information

Journal: INTERNATIONAL JOURNAL OF INDUSTRIAL ENGINEERING AND PRODUCTION MANAGEMENT (IJIE) (INTERNATIONAL JOURNAL OF ENGINEERING SCIENCE) (PERSIAN) Year:2001 | Volume:12 | Issue:3 Page(s): 11-22

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Title

STUDY ON BENDING-TORSION FLUTTER OF WING OF A FULL COMPOSITE AIRCRAFT

Author(s)

MEHRDAD SHOKRIEH MAHMOUD | TAHERI BEHROUZ F.A. | Issue Writer Certificate

Keywords

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Abstract

Aeroelasticity is the major source of various forms of instability in aircraft. For this reason. considering the effects of this phenomenon in design of airframe structures is essential. From various forms of instability. self-excitation vibration of wing which is called flutter is very important.The goal of this research is study of bending-torsion flutter of a wing of a full composite aircraft based on Joint aviation Requirements (JAR23). For this reason. it must be shown that the natural frequencies of bending and tensional vibration of the wing arc differ from each other. For achieving this goal a finite element software (NISA) is used.Two models of wing. based on lumped and consistent approaches arc made. To show thevalidity of the consistent model. a convergence analysis is performed. To verify the results obtained from the models. they are compared with an approximated solution after this step. flexural stiftiless. tensional stifti1ess and mass distribution along the frequenccies of the wing are obtained from the finite element model. In the next step. the frequencies of torsional and bending vibration of the wing are calculated by the lumped and consistent models and compared with each other.Finally based on JAR23 standard and the results obtained from the models. it is Concluded that there is no flutter for the wing of the full composite aircraft in the range of design speed.

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