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随着飞机结构设计技术不断发展,大型飞机机翼结构设计广泛采用大展弦比超临界机翼设计。该类机翼翼载大、弹性变形明显,导致单点加载的加载量级偏小、迟滞区和非线性问题显著,基于单点加载试验数据建立的载荷方程可信度降低,预测精度差。多点、高载、自动协调控制加载技术为载荷校准试验提供了更为高效、准确的途径。本文通过应用自动协调加载测试系统进行某型运输机机翼载荷校准试验,对试验数据进行处理,建立该型机机翼载荷模型,并使用校验试验数据对载荷模型进行了误差分析。
With the continuous development of aircraft structural design technology, large-scale aircraft wing structure design widely used large aspect ratio supercritical wing design. The wings of this kind of wing are large and the elastic deformation is obvious. As a result, the loading level of single point load is small and the hysteresis zone and nonlinear problem are significant. The reliability of load equation established based on the single point loading test data is reduced and the prediction accuracy is poor. Multi-point, high-load, automatic coordinated control of loading technology for load calibration test provides a more efficient and accurate way. In this paper, a self-aligning load test system is used to carry out the wing crane load calibration test for a certain type of transport aircraft. The experimental data are processed and the wing model of the aircraft is established. The error of the load model is analyzed by using the calibration test data.