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开展了大展弦比复合材料机翼气动弹性综合优化设计研究,以复合材料层合板铺层厚度为设计变量,以多种气动弹性约束与强度/应变约束为限制条件对结构进行优化设计,从铺层比例和铺层非均衡两方面分析了蒙皮铺层参数的影响。研究表明:在满足综合约束的条件下,随着0°铺层比例的增加,翼尖变形略微减小,颤振速度略有下降,副翼效率变化不大;蒙皮铺层非均衡程度主要影响机翼静气动弹性能,随着蒙皮非均衡引起的机翼刚轴绕翼根向前缘逐渐偏转,翼尖垂直变形变化不明显,但翼尖负扭转变形的绝对值加大,副翼效率下降。
Aeroelasticity optimization design of a large aspect ratio composite wing is carried out. The design parameters of the aeroelasticity of the composite material wing are given as the design variables. The structural design is optimized by using a variety of aeroelastic constraints and strength / strain constraints. The influence of the skinning parameters is analyzed from two aspects of the ply ratio and ply unbalance. The results show that with the increase of 0 ° ply ratio, wing tip deformation slightly decreases and flutter velocity slightly decreases, while the ailerons efficiency does not change much. The degree of non-equilibrium of skin ply is mainly Affect the dynamic performance of aerostatic wing, with the unbalanced skin caused by the wing rigid shaft around the wing root to the leading edge of the gradual deflection of the wingtip vertical deformation is not obvious, but the absolute value of the wingtip negative torsional deformation increases, deputy Wing efficiency decreased.