This paper presents a hybrid methodology for loads measurement on aircraft structures. It is based on both experimental data from the actual structure and numerical prediction from finite element models. The model is firstly adjusted based on a reduced amount of experimental data, so it can predict the structure load response in terms of simulated strain-gage bridge responses. Once adjusted, the model is loaded at several points while gathering the corresponding simulated strains responses. Based on regression analysis, the calibration coefficients are established to be used for in-flight load measurements. Comparing with the conventional calibration method, purely based on experimental tests, the new calibration methodology requires less calibration load cases, which makes the test setup also simpler. The new calibration method is applied to a horizontal empennage from a commercial aircraft, for which the conventional calibration was previously conducted, providing therefore the reference for both flight and ground test comparisons. A good correlation was found between the loads estimated by the conventional calibration and present method. Nowadays, virtual tests are getting importance for validation and demonstration purposes, and this work is adherent with this tendency.

本文介绍了一种用于飞机结构载荷测量的混合方法。它基于实际结构的实验数据和有限元模型的数值预测。该模型首先根据减少的实验数据量进行调整，因此它可以根据模拟的应变计桥梁响应来预测结构载荷响应。调整后，模型会在多个点加载，同时收集相应的模拟应变响应。基于回归分析，建立校准系数以用于飞行中载荷测量。与纯粹基于实验测试的传统校准方法相比，新的校准方法需要更少的校准负载情况，这使得测试设置也更简单。新标定方法应用于商用飞机的水平尾翼，之前进行了常规标定，因此为飞行和地面测试比较提供了参考。在通过传统校准和本方法估计的负载之间发现了良好的相关性。如今，虚拟测试对于验证和演示目的越来越重要，而这项工作也符合这种趋势。