Acoustic emission and strain gauge control of defects during static tests of composite spring of aircraft chassis

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Abstract

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.

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About the authors

L. N. Stepanova

FAI “Siberian Aeronautical Research Institute named after S. A. Chaplygin”

Author for correspondence.
Email: akustika2063@yandex.ru
Russian Federation, 630051, Novosibirsk, Polzunova st., 21

A. S. Laznenko

FAI “Siberian Aeronautical Research Institute named after S. A. Chaplygin”

Email: akustika2063@yandex.ru
Russian Federation, 630051, Novosibirsk, Polzunova st., 21

Е. S. Petrova

FAI “Siberian Aeronautical Research Institute named after S. A. Chaplygin”

Email: akustika2063@yandex.ru
Russian Federation, 630051, Novosibirsk, Polzunova st., 21

A. V. Kazakova

FAI “Siberian Aeronautical Research Institute named after S. A. Chaplygin”

Email: akustika2063@yandex.ru
Russian Federation, 630051, Novosibirsk, Polzunova st., 21

I. S. Ramazanov

FAI “Siberian Aeronautical Research Institute named after S. A. Chaplygin”

Email: akustika2063@yandex.ru
Russian Federation, 630051, Novosibirsk, Polzunova st., 21

V. V. Chernova

The Siberian Transport University

Email: akustika2063@yandex.ru
Russian Federation, 630049, Novosibirsk, D. Kovalchuk st., 191

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Supplementary files

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2. Fig. 1. Structural and power diagram of the spring chassis (a) and diagram of the stowage sections (b).

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3. Fig. 2. Layout of strain gauges and PAE: a — front view; b — top view.

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4. Fig. 3. Dependences of relative deformations on load, recorded by strain gauges during simulating landing with a lateral impact (a) and horizontal landing (b).

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5. Fig. 4. Dependences of relative deformations on load, recorded by single strain gauges during simulating landing with a side impact (a) and horizontal landing (b).

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6. Fig. 5. Location of AE signals in the spring during simulating a landing with a side impact (a) and a horizontal landing (b).

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7. Fig. 6. Dependences of the AE signal parameters on time, recorded by the PAE0–PAE3 sensors during the imitation of a landing with a side impact: a — MARSE energy parameter; b — median frequency; c — PD42 structural coefficient; d — two-interval coefficient. ♦ — PAE0; ■ — PAE1; ▲ — PAE2; ● — PAE3.

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8. Fig. 7. Dependences of the AE signal parameters on time, recorded by the PAE4–PAE7 sensors during the imitation of a landing with a side impact: a — MARSE energy parameter; b — median frequency; c — PD42 structural coefficient; d — two-interval coefficient. ♦ — PAE4; ■ — PAE5; ▲ — PAE6; ● — PAE7.

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9. Fig. 8. Dependences of the AE signal parameters on time, recorded by the PAE0 – PAE3 sensors during the horizontal landing simulation: a — MARSE energy parameter; b — median frequency; c — PD42 structural coefficient; d — two-interval coefficient. ♦ — PAE0; ■ — PAE1; ▲ — PAE2; ● — PAE3.

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10. Fig. 9. Dependences of the AE signal parameters on time, recorded by the PAE4 – PAE7 sensors during the horizontal landing simulation: a — MARSE energy parameter; b — median frequency; c — PD42 structural coefficient; d — two-interval coefficient. ♦ — PAE4; ■ — PAE5; ▲ — PAE6; ● — PAE7.

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11. Fig. 10. Area with spring defects identified during ultrasound testing with a Starmans DIO100 PA tomograph and marked in white.

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