大展弦比飞机机翼弯曲变形分析和测试方法

将大展弦比飞机机翼简化为变截面悬臂梁结构。基于线性叠加原理,将变截面梁划分为n段,推导出梁挠度的计算方程。根据机翼实际尺寸,并考虑机翼自重和外挂载荷建立变截面梁模型,将梁划分为5段、10段、20段计算梁的挠度。利用ANSYS有限元软件中几何非线性迭代方法,分析变截面梁受均布载荷时的变形。理论计算结果和有限元仿真结果吻合,验证了该计算方法的有效性。为计算大展弦比飞机实际飞行过程中机翼实时弯曲变形,在机翼上布置应变计并进行地面标定试验,得到载荷与应变之间的关系方程和机翼各段的弯曲刚度。通过采集飞行实测应变数据,结合标定方程将机翼各测试切面应变-时间历程转化为载荷-时间历程,再利用挠度计算方程计算机翼的实时弯曲变形情况。为大展弦比飞机飞行过程中机翼变形测试提供了一种工程测试途径。

Analysis and test method for bending deformation of high aspect ratio aircraft wing

The high aspect ratio aircraft wing was simplified as a variable cross-section cantilever beam. Based on the principle of superposition theory, the variable section beam was divided into n sections, and the equation of loads and deflection was derived. According to the actual size and the external load of the wing, a model of variable section beam was established. The maximum deflection of the beam under distributed load was calculated at 5, 10 and 20 sections respectively. Comparing the deflection results with the results calculated by the geometric nonlinear method in ANSYS software, the simulated and calculated results were in good agreement with each other, which proved the validity of the method. In order to get the load distribution of the wing in actual flying, strain gauges were installed on the wing. The calibration experiment was carried out to establish the relation equation between load and strain, and get the stiffness of each part of the wing. After recording the strain-time history during the flight with data acquisition system, the strain-time history could convert to load-time history, and the bending deformation of the wing in actual flying could be calculated by using loads-deflection equation. This paper provides an engineering test method for the deformation of the high aspect ratio aircraft wing during the flight.