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Paper Information

Journal:   JOURNAL OF SCIENCE AND TECHNOLOGY OF COMPOSITES (JSTC)   June 2019 , Volume 6 , Number 1 ; Page(s) 79 To 87.

Static and dynamic analysis of composite thin walled beam with curvilinear fiber

Author(s):  ZAMANI ZAHRA*, Haddadpour Hasan
* School of Mechanical Engineering, Golpayegan University of Technology, Golpayegan, Iran
In this study, the static and dynamic analysis of composite wing is investigated using analytical method. The wing is modeled as a cantilevered thin walled beam with a single-cell closed cross section and the circumferentially asymmetric stiffness (CAS) configuration. The non-classical effects such as transverse shear, warping restraint, rotary inertia, nonuniform torsional model and material anisotropy are considered in the beam model. The governing equations were derived by means of the extended Hamilton’ s principle and are solved based on the extended Galerkin’ s method. From the validation process, the obtained results are in good agreement with the numerical results and experimental data. In this paper, a linear spanwise variation of the fiber orientation along the thin-walled beam span resulting in a variable-stiffness structure is investigated for the first time. Therefore, two fiber path definitions will be used with linear fiber orientation variation and with constant curvature of the fiber path. Numerical results indicate that eigenfrequencies and bending-torsion couplings depend on fiber angle, resulting improvements of wings with curvilinear fiber over conventional, straight ones through the variation of fiber angle along the beam span and increase of the design space.
Keyword(s): Thin walled composite beam Aircraft wing,Curvilinear fiber,Non-classical effect
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