【摘要】 在飞机结构确定性装配模式下,由于制孔偏差、外形偏差等因素的影响,零件的连接孔在连接时会产生同轴度偏差,较大时将导致局部产生装配应力,削弱结构的力学性能。针对飞机机体结构的确定性装配,将雅可比-旋量法与影响系数法相结合,确定了零件外形偏差、终孔定位偏差与临时紧固件连接的矩阵表达形式,提出了一种考虑偏差积累与零件变形的同轴度偏差计算模型,同时搭建了同轴度偏差装配实验系统。对比偏差实测数据、雅可比-旋量模型与本文模型的计算结果,本文建立的模型与实测数据的平均误差降低了8.89%,提高了确定性装配模式下机体结构的偏差计算精度,为优化装配工艺提供了更加可靠的理论依据。更多还原

【Abstract】 Under the deterministic assembly mode of aircraft structures, coaxiality deviations occur at the connecting holes of parts during assembly due to factors such as hole-making deviations and shape deviations. When these deviations are relatively large, they cause local assembly stress and weaken the mechanical properties of the structure.For the deterministic assembly of aircraft fuselage structures, this study combines the Jacobian-torsor method with the influence coefficient method to determine the matrix expressions of part shape deviations, final hole positioning deviations, and temporary fastener connections. It also proposes a coaxiality deviation calculation model that accounts for deviation accumulation and part deformation, while establishing an assembly experimental system for coaxiality deviation.By comparing the measured deviation data, the calculation results of the Jacobian-torsor model and those of the proposed model, it is found that the average error between the proposed model and the measured data is reduced by 8.89%. This improves the deviation calculation accuracy of the fuselage structure under the deterministic assembly mode and provides a more reliable theoretical basis for the optimization of assembly processes.更多还原