复合材料增压舱双圆截面交点连接设计分析  

Panel Splices Design and Analysis of Double Bubble Intersection in Composite Pressure Cabin

作　　者：钟小丹[1] 陈普会[1] 刘利阳[2] 王进[2] 

机构地区：[1]南京航空航天大学飞行器先进设计技术国防重点学科实验室,江苏南京210016 [2]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《航空学报》2013年第10期2357-2363,共7页Acta Aeronautica et Astronautica Sinica

摘　　要：按照连接设计要求及机身压差载荷水平,开展了复合材料增压舱双圆截面交点连接设计研究。采用壳-梁耦合有限元模型对两种双圆交点连接构型方案在压差载荷作用下的面外位移进行分析。在此基础上,对其中的对接连接构型方案进行强度校核:通过Fastener单元提取连接结构的钉载分布后,采用单钉模型进行细节结构强度校核,进而评估整个连接区的失效载荷。研究结果表明,采用对接的连接设计方案,双圆交点区在压差载荷下的横向变形较小,该设计方案能够满足设计要求。According to the design criteria of mechanical joints and differential pressure load, a study is performed on panel splices design of a double bubble intersection in a composite pressure cabin structure. Two different panel splices of the double bubble intersection in a composite fuselage are designed under differential pressure loads, and the transverse dis- placement of the panels is analyzed by a shell-beam finite element model. Then the strength of butt joint concept is checked. The load distribution of the multiple-bolted joints in the structure is first calculated by using fastener elements; then the failure strength of the panel splices is assessed by failure analysis on single-bolted joints at critical locations. The result demon- strates that the butt joint design concept can improve the transverse displacement of the panels significantly under differential pressure loads and satisfy the design requirements,

关 键 词：双圆截面 增压舱 复合材料 多钉连接 失效分析 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]