Influence of the Fatigue Load Level and the Hole Diameter on the Laminate Structure’s Fatigue Performance

• Autorzy: Zalewska M.

Identyfikatory

DOI

10.2478/fas-2018-0002

• Języki publikacji: EN

Abstrakty

EN

Damage tolerance of composite aircraft structure is one of the main areas of research, important when a new product is being developed. There are a number of variables, such as damage characteristics (dent depth, delamination area) and loading parameters (load type, amplitude of cyclic loading, load sequence) that need to be investigated experimentally [1]. These tests of composite materials are usually performed at an element level and are carried out in order to validate the analytical model, developed to predict the full-scale component’s behaviour. The paper presents the results of compression testing of the [36/55/9] carbon fibre/epoxy laminate, manufactured with the Automated Fibre Placement technology (AFP) and subjected to static and fatigue loads. The laminate compression loading mode was achieved through sandwich 4-point flexure. At the stage of fatigue testing, two parameters were investigated: the damage size, simulated by the hole diameter and the fatigue load level. Based on the test results, the laminate fatigue load limit equal to 75% of the OHC failure load was evaluated. By collating the static and fatigue tests results, the damage tolerance characteristic of the considered laminate was created.

Słowa kluczowe

EN

composite; fatigue; damage

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Fatigue of Aircraft Structures
• Rocznik: 2018
• Tom: Iss. 10
• Strony: 21--30
• Opis fizyczny: Bibliogr. 8 poz., rys., tab., wykr.

Twórcy

autor

Zalewska M.

• Institute of Aviation, Warsaw, Poland

Bibliografia

• [1] Tomblin, J. S., Lacy, T., Smith, B., Hooper, S., Vizzini, A., Lee, S., Review of Damage Tolerance for Composite Sandwich Airframe Structures, Final Report, DOT/FAA/AR-99/49, 1999.
• [2] CMH-17, Composite Materials Handbook, Volume 1. Polymer Matrix Composites Guidelines for Characterization of Structural Materials. SAE International, 2012.
• [3] Tomblin J. S., Senevirante W. P., Durability And Damage Tolerance Testing of a Beechcraft Starship Forward-Wing With Large Damages, Final Report, DOT/FAA/TC-13/26, 2017.
• [4] Adams D. O., Kuramoto B., Damage tolerance test method development for sandwich composites.
• [5] Gang Z., Leung H., Zheng C., Robinson B., New four-point bending based method for impact damage tolerance assessment of sandwich structure, Chinese Society for Composite Materials, 2017.
• [6] ASTM standard D7249/D7249M, Standard Test Method for Facesheet Properties of Sandwich Constructions by Long Beam Flexure, ASTM International, 2018.
• [7] European Aviation Safety Agency, 2010, AMC 20-29 Composite Aircraft Structure.
• [8] ASTM standard ASTM D7137/D7137M, Standard Test Method for Compressive Residual Strength Properties of Damaged Polymer Matrix Composite Plates, ASTM International, 2017.

Uwagi

PL

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2019).