Aeroelastic instability of composite wings by the consideration of different structural constitutive assumptions |
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| Institution: | 1. Department of Physics, Faculty of Science and Technology, Umeå University, 901 87, Umeå, Sweden;2. Combustion and Turbulence Research Laboratory (CTL), Department of Aerospace Engineering, Amirkabir University of Technology (Tehran Polytechnic), Hafez Ave, Tehran, 15875-4413, Iran;1. Google[X], 2175 Monarch St, Alameda, CA 94501, United States;2. Department of Aerospace Engineering and Engineering Mechanics, The University of Texas at Austin, Austin, TX 78712, United States;1. Clean Energy Processes (CEP) Laboratory, Department of Chemical Engineering, Imperial College London, London SW7 2AZ, UK;2. Department of Engineering, University of Cambridge, Trumpington Street, Cambridge CB2 1PZ, UK;3. Department of Mechanical Engineering, University College London, London WC1E 7JE, UK;1. Technological Institute of Aeronautics - ITA, São José dos Campos, SP, Brazil;2. Universidade Estadual Paulista - UNESP, Bauru, SP, Brazil;1. State Key Laboratory for Manufacturing Systems Engineering, Xi''an Jiaotong University, 710049 Xi’an, Shaanxi, People’s Republic of China;2. Collaborative Innovation Center of High-end Manufacturing Equipment, Xi''an Jiaotong University, 710049 Xi’an, Shaanxi, People’s Republic of China |
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| Abstract: | The aeroelastic instability of composite wings modeled as Circumferentially Asymmetric Stiffness (CAS) thin-walled composite beams with closed cross-section is carried out. The objective has been to investigate the effects of different assumptions of constitutive equations on the aeroelastic instability behavior. Non-classical effects such as restrained warping and transverse shear are included in the beam model. The unsteady incompressible airloads are presented using Wagner׳s function. A comparison of the results based on different constitutive equations for a number of configurations including three types of stacking sequence for a box cross-section and two types of stacking sequence for a biconvex cross-section, is performed. The effects of the values of twist as well as twist-bending stiffness coefficients have been studied carefully on the results. As an outcome of this investigation it is revealed that the different choices of structural constitutive equations which result in different values of stiffness quantities; namely, twist and twist-bending stiffness, significantly affect the predicted results. For example, a difference of up to 45% in the aeroelastic critical speed has been observed between different sets of constitutive equations in some cases. |
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| Keywords: | Aeroelastic instability Composite wing Thin-walled composite beam Constitutive equations |
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