The article presents the results of tests of the aircraft landing gear support spring made of Toray T800 prepreg and 30 KhGSA steel. The cases of its testing by acoustic emission, ultrasonic methods and strain gauge during the simulation of horizontal aircraft landing and during the simulation of landing with a side impact are considered. During the spring tests, strain gauge was used, tensile, compressive and torsional deformations were studied. The changes in the main informative parameters of acoustic emission signals (MARSE energy parameter, median frequency, structural and two-interval coefficients) were analyzed. The defect type was determined using a modified structural coefficient. This made it possible to increase the speed of information processing, since its decrease corresponded to the matrix destruction, and its increase corresponded to the fiber destruction. The location of acoustic emission signal sources corresponding to the structure area with the greatest relative deformations was obtained. It was noted that when simulating a horizontal landing of an aircraft, after removing the load, residual deformations were observed in the spring material.
L.N. Stepanova (2025) studied this question.