复合材料壁板铺层参数对大展弦比机翼气动弹性优化的影响  

Effect of laminate parameters of composite skin on aeroelastic optimization of high-aspect-ratio wing

作　　者：周磊[1] 万志强[1] 杨超[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《复合材料学报》2013年第5期195-200,共6页Acta Materiae Compositae Sinica

基　　金：国家自然科学基金(11172025)

摘　　要：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。This paper demonstrated design studies of aeroelastic optimization on composite skins of a high-aspect ratio wing, subject to aeroelastic constraints and strength/strain constraints. In optimization, the ply thickness of wing skin panels was adopted as design variables. The impacts of laminate proportion and unbalance laminate of wing skin panels on optimization results meeting all design constraints were discussed. The results indicate that the maximal vertical deformation and twist angle at wing tip and the flutter speed decrease with the proportion of 0~plies increasing, and there is less variation in the aileron efficiencies of the optimal results. The optimal distribution has made it clear that the unbalance level of the skin laminates has great effects on the static aeroelastic characteristics. The maximal twist angle at wing tip increases with the axis of stiffness moving forward, while the maximal vertical deformation at wing tip keeps almost unchanged, but the aileron efficiency decreases.

关 键 词：气动弹性 结构优化 铺层比例 铺层非均衡 复合材料机翼 

分 类 号：TB330.1[一般工业技术—材料科学与工程] V211.47[航空宇航科学与技术—航空宇航推进理论与工程]