摘要
以某型飞机外翼结构为基础,提出了将复合材料应用于受压上壁板的技术方案,与原金属上壁板方案进行了总体分析及温度变形分析,并深入研究了金属与复合材料壁板受压区多钉连接和复合材料大开口区钉载分配的两项关键技术,为复合材料在未来型号应用及推广积累了经验。
Based on the wing-fuselage combination structure of an aircraft, this paper proposes an ap- proach to apply composites to compressed upper panel of the wing, followed by the comparison about overall analysis and temperature distortion between composites application and metallic application. In addition, it studies two key technologies：Load distribution of multiple bolt-jointed metal to com- posites panel and pin load distribution of composite laminate with large cutout. This work provides the engineering experience for the future application of composites to other aircrafts.
出处
《飞机设计》
2017年第1期24-27,共4页
Aircraft Design
关键词
复合材料
外翼
受压上壁板
多钉连接
大开口
composite
wing-fuselage combination
compressed upper panel
multiple bolt-jointed
large cutout
