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Positioning variation modeling for aircraft panels assembly based on elastic deformation theory

机译:基于弹性变形理论的飞机面板总成位置变化建模

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摘要

Dimensional variation in aircraft panel assembly is one of the most critical issues that affects the aerodynamic performance of aircraft, due to elastic deformation of parts during the positioning and clamping process. This paper proposes an assembly deformation prediction model and a variation propagation model to predict the assembly variation of aircraft panels, and derives consecutive 3-D deformation expressions which explicitly describe the nonlinear behavior of physical interaction occurring in compliant components assembly. An assembly deformation prediction model is derived from equations of statics of elastic beam to calculate the elastic deformation of panel component resulted from positioning error and clamping force. A variation propagation model is used to describe the relationship between local variations and overall assembly variations. Assembly variations of aircraft panels due to positioning error are obtained by solving differential equations of statics and operating spatial transformations of the coordinate. The calculated results show a good prediction of variation in the experiment. The proposed method provides a better understanding of the panel assembly process and creates an analytical foundation for further work on variation control and tolerance optimization.
机译:由于部件在定位和夹紧过程中的弹性变形,飞机面板组件的尺寸变化是影响飞机空气动力性能的最关键问题之一。本文提出了一种装配变形预测模型和一个变化传播模型来预测飞机面板的装配变化,并推导出连续的3-D变形表达式,这些表达式明确描述了顺应性组件装配中发生的物理相互作用的非线性行为。从弹性梁的静力学方程推导装配变形预测模型,以计算面板构件因定位误差和夹紧力而产生的弹性变形。变量传播模型用于描述局部变量和整体装配变量之间的关系。通过求解静力学的微分方程和坐标的操作空间变换,可以获得由于定位误差导致的飞机面板的装配变化。计算结果显示了对实验变化的良好预测。所提出的方法可以更好地理解面板装配过程,并为进一步进行偏差控制和公差优化工作奠定了分析基础。

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