- Tytuł:
- Influence of the Fatigue Load Level and the Hole Diameter on the Laminate Structure’s Fatigue Performance
- Autorzy:
- Zalewska, M.
- Powiązania:
- https://bibliotekanauki.pl/articles/97951.pdf
- Data publikacji:
- 2018
- Wydawca:
- Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
- Tematy:
-
composite
fatigue
damage - Opis:
- 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.
- Źródło:
-
Fatigue of Aircraft Structures; 2018, 10; 21-30
2081-7738
2300-7591 - Pojawia się w:
- Fatigue of Aircraft Structures
- Dostawca treści:
- Biblioteka Nauki
Artykuł