飞机复合材料结构装配中的力学行为研究进展  

Research Progress of Mechanical Behavior in Aircraft Composite Structure Assembly

作　　者：李梅平 张永亮[1] 刘宏伟 安鲁陵[2] 赵聪 赵付山 LI Meiping;ZHANG Yongliang;LIU Hongwei;AN Luling;ZHAO Cong;ZHAO Fushan(Shenyang Aircraft Corporation,Shenyang 110034,China;College of Mechanical and Electronic Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]沈阳飞机工业(集团)有限公司,辽宁沈阳110034 [2]南京航空航天大学机电学院,江苏南京210016

出　　处：《机械制造与自动化》2024年第6期20-27,共8页Machine Building & Automation

基　　金：国家自然科学基金项目(51975280)。

摘　　要：复合材料的综合性能优异,被广泛应用于现代飞机结构中。但受限于其较大的成型偏差和较弱的层间性能,在装配过程中复合材料结构往往出现局部应力过大甚至结构损伤的现象。在结构几何外形满足精度要求的同时,为了保证复合材料装配结构的完整性和力学性能,还需对复合材料结构装配力学行为进行深入研究。分析复合材料结构装配环节对装配应力的影响,从校形与夹紧、填隙补偿、螺栓连接等方面综述装配力学行为的研究,给出进一步的研究展望。Despite the fact that composite materials have excellent comprehensive properties and are widely used in modern aircraft structures,their structures often suffer from local excessive stress and even structural damage during the assembly process due to their large forming deviation and weak inter-laminar performance.In order to ensure the integrity and mechanical performance of composite assembly structure,it is of necessity to conduct in-depth research on the assembly mechanical behavior of composite structure,while the geometric shape of the structure meets the accuracy requirements.This paper analysis the influence of assembly process on assembly stress of composite structure,summarizes the research on assembly mechanical behavior from the aspects of sizing and clamping,gap compensation,bolt connection,etc.,and proposes further research prospects.

关 键 词：飞机 复合材料结构 装配 力学行为 

分 类 号：V262.4[航空宇航科学与技术—航空宇航制造工程]