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复合材料具有比强度高、比刚度大、抗疲劳等诸多优异性能,在航空航天结构中得到了广泛的应用。复合材料在新研制的飞机上的应用比重也越来越高,在大型民用飞机Boeing787上,复合材料结构重量占到了全机结构重量的50%。复合材料层合板具有无与伦比的设计潜力,成为复合材料中使用最多的一种结构形式。本文以某型号飞机机翼翼盒为研究对象,建立了翼盒结构的有限元模型,以结构质量为目标函数,以位移、应变和屈曲因子为约束条件,并利用工程优化软件对复合材料翼面进行优化。整个翼面设计优化过程包括三个阶段:自由尺寸优化、层组尺寸优化和层叠次序优化。优化结果表明,通过三个阶段的优化,在满足刚度、强度和稳定性三种约束的要求下,明显减轻了翼面结构的质量。
Composite materials with high specific strength, stiffness, fatigue resistance and many other excellent performance in the aerospace structure has been widely used. Composite materials in the newly developed aircraft applications are also increasing the proportion of heavy aircraft in the large Boeing787, the weight of the composite structure accounted for 50% of the weight of the whole structure. Composite laminates have unparalleled design potential and are the most widely used form of composite structures. In this paper, the finite element model of the wing box is built on the wing box of a certain type of aircraft. The structural quality is taken as the objective function, and the displacement, strain and buckling factors are used as the constraint conditions. The engineering optimization software is applied to the composite wing optimize. The entire wing design optimization process consists of three phases: free size optimization, layer size optimization and cascade optimization. The optimization results show that the optimization of the three stages can obviously reduce the quality of the airfoil structure under the requirements of three kinds of constraints of stiffness, strength and stability.