| Citation: | MAO Sen, YANG Chao, XIE Changchuan, et al. Comparative analysis of linear/nonlinear static aeroelasticity of fishbone flexible wing[J]. Journal of Beijing University of Aeronautics and Astronautics, 2021, 47(6): 1299-1310. doi: 10.13700/j.bh.1001-5965.2020.0307(in Chinese)
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Fishbone flexible wing is a excellent design of active morphing camber wing. Ithas low chordwise bending stiffness and high stiffness along the thickness direction of airfoil, and it has strong geometric nonlinearity and significant aeroelastic effect when undergoing active deformation with large deformation. The traditional linear static aeroelastic analysis method is not fit for this problem. Therefore, this paper takes the public fishbone flexible wing model of Bristol University as the research object, adopts the nonlinear aeroelastic analysis method which is based on non-planar Vortex Lattice Method (VLM) and nonlinear finite element analysis and the traditional linear aeroelastic analysis method which is based on linear finite element analysis and planar VLM to analyze the static aeroelasticity of the fishbone wing under large deformation and compare the results. Similarly, the aerodynamic calculation results of the non-planar VLM and XFOIL software used in this paper are verified. The results show that the aeroelastic effect of the fishbone flexible wing under large deformation is significant. Compared to the results of traditional linear static aeroelasticity analysis method, the lift coefficient of fishbone wing under large deformation by nonlinear static aeroelasticity analysis method is 8.28% smaller at most, and the moment coefficient is 6.86% smaller at most. The real deformation under the aerodynamic load can be obtained accurately and quickly by the nonlinear aeroelasticity analysis method proposed in this paper, which is more valuable for practical engineering application.
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