【摘要】 气密顶板螺栓连接结构在飞机飞行中受到气密载荷的作用，连接的可靠性直接影响飞机的飞行安全。气密顶板原始连接结构受力后，螺栓连接区应变较大，局部受力不合理，无法满足使用要求，且连接结构组成零件多、传力路线复杂，因此迫切需要进行结构改进设计以满足飞机的实际使用要求。本文采用有限元软件分析了气密顶板原始连接结构的传载特性，并在此基础上对其进行了结构改进。理论分析结果显示，气密顶板连接结构经过两次结构改进设计后，螺栓连接区最大应变明显降低，高应变区域缩小。最后采用3D-DIC技术完成了气密顶板螺栓连接结构的应变测量，测量结果与有限元分析相一致，进一步明确了气密顶板连接结构的传载特性，验证了第二次改进结构的合理性。更多还原

【Abstract】 The bolt connection structure of airtight panel bears airtight load during the flight of the aircraft, and the connection reliability is very important for flight safety. To simplify the structure and the loading paths, the finite element software is used to analyze the load transfer characteristics of the original connection structure of the airtight panel, and on this basis, the structural improvement design are carried out to meet the actual use requirements of the aircraft. The finite element results and the optimized structures are verified by the 3D-DIC strain measurement test, by which the load transfer ability of the airtight panel connection structure is clarified. Further, the results of finite element analysis and strain measurement show that the maximum strain of the bolt connection area on the airtight panel connection structure after structural improvement is significantly reduced, and the area of high strain zone is decreased, which verify the rationality of the improved structure.更多还原