| Citation: | XIAO Zhipeng, QIAN Wenmin, ZHOU Leiet al. Aeroelastic optimization design of composite wing for large aircraft with panel stiffness matching[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(8): 1629-1635. doi: 10.13700/j.bh.1001-5965.2017.0613(in Chinese)
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A method of aeroelastic optimization design with consideration of panel stiffness matching was developed for the composite wing of large aircraft. The optimization was performed based on the sensitivity algorithm, and the objective was to minimize the structural mass subject to the constraints of panel stiffness matching, flutter speed, deformation at wingtip, design allowable and manufacturability. The composite wings were designed in the case of critical load conditions. The influences of various panel stiffness matching requirements on optimal design results were studied and they were compared with the conventional optimal design results. The results indicate that the structural weight will increase with consideration of panel stiffness matching. However, it has an advantage in local buckling design, damage tolerance design and manufacturing of large composite panel. The optimal design results can be significantly affected by the design ranges of panel stiffness matching, so these design ranges should be properly determined according to the requirements of design and manufacturing. The design allowable of compression is a crucial constraint of the aeroelastic optimization design for composite wing.
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