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大展弦比复合材料机翼在大量减轻机体重量的同时,也极大地增加了机翼的柔性,对飞机的气动特性和安全性构成了不利影响。针对大展弦比复合材料机翼的气动变形行为,应用有限元及流固耦合计算方法,在计算、分析机翼刚心轴线随机翼柔性变形而产生的位移的基础上,提出了复合材料机翼的预变形设计分析方法,并就预变形机翼变形前后的气动性能与理想刚性机翼进行了对比分析。计算结果表明,在巡航状态下,预变形机翼能够在有效提升机翼升阻比的情况下,保证机翼的升阻比特性与设计要求相符,但在非巡航状态下,随着飞行速度的改变,预变形机翼的升阻比将有所下降。因此,预变形设计的适用对象应为长期处于巡航状态的飞机。
Large aspect ratio composite wing in a lot of weight to reduce body weight, but also greatly increased the flexibility of the wing, the aerodynamic characteristics and safety of the aircraft pose a negative impact. Aiming at the aerodynamic deformation behavior of composite wing with large aspect ratio, finite element method and fluid-solid coupling method are used to calculate and analyze the displacements caused by flexible deformation of wing core axis. Wing pre-deformation design and analysis methods, and pre-deformed wing deformation before and after the aerodynamic performance and ideal rigid wing comparative analysis. The calculation results show that the pre-deformed wing can ensure that the lift-drag ratio of the wing is in accordance with the design requirements under the condition of effectively improving the lift-drag ratio of the wing. However, in the non-cruising state, as the flight speed The change in lift-drag ratio of the pre-deformed wing will decrease. Therefore, the pre-deformation design should be suitable for long-cruising aircraft.