Combined Static and Fatigue Tests of the Full-Scale Structure of a Transport Aircraft

The article discusses a non-traditional approach in strength tests of the full-scale structure of a transport aircraft, which consists of combining static and fatigue tests on one object. The test object included a full span wing with installed pylons, the middle part of the fuselage and the main landing gear. The tests were carried out on the bench, which allowed reproducing both static cases of loading and variable loads of flight cycles. To confirm the static strength, the structure of wing half span was loaded with limit loads and simultaneous strain measurement. The data of strain gauges verified the finite element model (FEM), on the basis of which the prediction of the stress-strain state of the structure was made with the ultimate loads. To confirm the strength capacity of the upper wing panels under the stability conditions, tests of full-size wing panels were carried out. After loading with the limit load, fatigue tests were carried out which are required to confirm the service life.