民用飞机舱门优化研究  

THE DOOR STIFFNESS RESEARCH OF CIVIL AIRCRAFT

作　　者：袁修起[1] 

机构地区：[1]上海飞机设计研究院结构设计研究部,上海201210

出　　处：《玻璃钢／复合材料》2014年第7期37-41,共5页Fiber Reinforced Plastics/Composites

摘　　要：针对一类民用飞机舱门结构的特点,采用蜂窝夹层结构形式进行设计。选定不同内外蒙皮厚度、不同蜂窝高度、加装加强垫板、填平蜂窝凹槽、局部抬高蜂窝高度等多种结构形式进行分析对比。为便于比较各种结构的优缺点建立了舱门结构的有限元模型,并对各组结构弯曲变形情况进行计算。计算结果表明,内蒙皮厚度和蜂窝高度对舱门刚度起主导作用,存在合适刚度的内蒙皮厚度和蜂窝高度使舱门在巡航状态下的弯曲变形符合要求。分析结果及所得结论为同类型飞机舱门的设计提供了借鉴,有一定的参考价值。Based on the structural characteristics of a class of typical civil aircraft door,several sandwich structures are designed and compared.Several conditions of sandwich structure are considered,i.e.structure of different inner and outer skin thickness,structure of different honeycomb height,structure of adding and no reinforcing plate,structure with and without honeycomb groove and raising the height of the local cellular.A finite element model of the honeycomb sandwich door is developed.A contrastive analysis of distorted displacement for different structure is obtained.The calculation implies that the thickness of inner skin and honeycomb height plays a dominant role on the door stiffness,and that there is a certain inner skin thickness and honeycomb height for the door,which will make door＇s bending deformation in cruise state meet the requirement.The analysis results and conclusion provide some design guide and reference value for the same kind of aircraft door.

关 键 词：民用飞机 舱门 蜂窝夹层 刚度 有限元 

分 类 号：V223.9[航空宇航科学与技术—飞行器设计]