基于虚拟标定试验的翼身交点载荷方程研究

Research on Aircraft Wing-Fuselage Joint Load Equation Based on Virtual Calibration Test

本文重点研究了基于虚拟标定试验的翼身交点载荷方程及应用情况。通过建立虚拟标定试验样机,布置虚拟应变电桥,进行虚拟标定试验,得到翼身交点虚拟标定载荷方程。利用某型飞机地面简易标定试验结果,对虚拟标定载荷方程进行修正,获得该型飞机单机翼身交点载荷方程,并利用地面试验数据进行校验。由此方法获得的单机翼身交点载荷方程可用于单机载荷历程监控,并为结构故障预测与健康管理(SPHM)寿命预测提供满足精度要求的载荷输入条件。

The equations of wing-fuselage joint load based on virtual calibration test are analyzed and discussed. The virtual strain-gage bridges are set on the virtual test structures, and the virtual load-equations are obtained by multiple linear regression from the results of virtual calibration test. One aircraft is selected to be calibrated on ground with few load-cases, and the calibration test results are used to modify the virtual load-equations, then the individual aircraft wing-fuselage joint load-equations are obtained and verified by the results of ground test. The wing-fuselage joint loadmodels could be obtained and could be useful for individual aircraft load monitor. These wing-fuselage joint loads could be used as precisely input data for the life evaluation of structures in SPHM.