基于不同定位基准的复合材料护板容差分析研究

Research on Tolerance Analysis of Composite Shield Based on Different Positioning References

先进复合材料以比重小、强度高、疲劳性能好等优点在现代飞机中得到广泛的应用,复合材料零件热成型过程中的变形和厚度控制困难,部件定位方式和容差分配的合理性在很大程度上影响着飞机部件装配的质量和效率。以某复合材料护板装配为例,研究采用两种不同的数控铣边定位方案对部件容差分配及装配协调的影响,并使用MATLAB软件编程计算模拟各制造公差与最终装配容差之间的数学关系,为该部件数控铣边的定位方式和铣夹设计提供依据。

Advanced composite materials are widely used in modern aircraft due to their small specific gravity,high strength and good fatigue performance.The deformation and thickness control of composite parts during thermoforming is difficult,and the rationality of component positioning and tolerance distribution greatly affects the quality and efficiency of aircraft component assembly.In this paper,a composite material shield assembly is taken as an example to study the effect of two different CNC milling edge positioning schemes on the tolerance distribution in the whole assembly process,and use MATLAB software to calculate and simulate the simulation tolerance between each manufacturing tolerance and the final assembly tolerance.The mathematical relationship provides a basis for the positioning of the CNC milling edge and the design of the frame.