民用飞机复合材料舱门优化设计

Optimized design of a composite door for civil airplane

复合材料因其具有比刚度大、比强度高、可设计性强等特点而被广泛应用到民用飞机结构上。针对宽体复合材料舱门设计方案,建立有限元模型进行初步分析,然后以刚度设计要求和强度设计要求为约束条件,对复合材料舱门结构的铺层比例进行了优化,达到了复合材料舱门的减重目的。优化后复合材料舱门的重量降低了10%以上,并且满足所有刚度和强度设计要求。本文所做研究为复合材料气密舱门减重提供了一种有效的方法,并且为类似结构的设计提出了参考建议,在工程上具有一定的指导意义。

Composite materials are widely used in civil aircraft structures because of their higher stiffness,strength and designability. Based on the design of the composite door for the wide-body aircraft,the finite element model was established.and the lay-up ratio of the composite door was optimized, which the design requirements of the stiffness and the strength are assigned as the constraints and the minimum weight is the target. The weight of the composite door is reduced by more than 10% and meets the design requirements of stiffness and strength.The research in this paper provides an effective method for weight reduction of composite air-tight doors, and provides suggestions for similar structure design.