针对多偏心螺栓组件在飞机上的连接需求以及多重偏心状况影响的研究缺失,本研究结合传统偏心螺栓分析步骤与多重偏心极限位置分析与简化方案,提出了一套新型多重偏心螺栓组件分析流程。根据该流程计算分析了某型飞机上双偏心螺栓组件的偏心特性,综合考虑了多种偏心状况对该组件力学性能的影响,并且根据极限应力状况下的工况对结构参数完成了优化分析。结果表明,在小偏心状况下对于结构整体受力影响不显著;在组件大偏心情况下,当组件偏心方向与载荷方向相垂直时偏心结构会出现极限应力状态。该研究充分说明了新型多重偏心螺栓组件分析流程的技术可行性,也为实际的飞机零部件装配提供了较好的参考。 In view of the lack of research on the connection requirements of multi-eccentric bolt assemblies on aircraft and the influence of multi-eccentricity conditions, a new type of multi-eccentric bolt assembly analysis procedure is proposed based on the analysis of traditional eccentric bolt analysis procedures and multiple eccentricity limit position analysis and simplification schemes. According to this process, the eccentric characteristic of double eccentric bolt assembly on a certain aircraft is calculated and analyzed. The influence of multiple eccentric conditions on the mechanical properties of the assembly is considered. The structural parameters are optimized and analyzed according to the working conditions under the ultimate stress condition. The results show that under the condition of small eccentricity, there is no significant effect on the overall stress of the structure. In the case of large eccentricity of the assembly, the ultimate stress state occurs in the eccentric structure when the eccentric direction of the assembly is perpendicular to the load direction. This study fully demonstrates the technical feasibility of the new multiple eccentric bolt assembly analysis process and provides a good reference for the actual assembly of aircraft parts.