The Investigation of Damage Mechanisms of Thermally Aged 4/3 Glare with Cone Beam Computed Tomography
Crimson Publishers Research Article Wings to the Research The Investigation of Damage Mechanisms of Thermally Aged 4/3 Glare with Cone Beam Computed Tomography Hamdi Fidan1, Mustafa Özgür Bora2*, Onur Çoban2 and Eyüp Akagündüz3 1Turkish Airlines Technic Inc, Turkey 2Kocaeli University, Faculty of Aeronautics and Astronautics, Turkey 3TUBITAK-MAM, Materials Institute, Turkey Abstract In this paper, the effect of thermal cycles on the flexural properties of 4/3 configured Glass Reinforced Aluminum (GLARE) has been evaluated with Cone Beam Computed Tomography (CBCT). GLARE is manufactured by Turkish Airlines Technic Inc. composite workshop with autoclave method. After manufacturing process, GLARE samples are subjected to thermal cycles (0, 25, 50, 100, 200 and 300 cycles) in a full function climatic chamber at temperature ranges -30 °C to +40 °C for 120min. Three- point bending tests are applied to thermally aged GLARE samples by using Zwick Z-250 universal test machine. The variation on the flexural modulus and strength values of GLARE samples is determined. From test results, the decrements of the flexural strength and modulus of GLARE samples are occurred for 300 thermal cycles as 4.95% and 4.85%, respectively. From CBCT observations, it is determined that *Corresponding author: Mustafa delaminationKeywords: and metallic layer fractures are the main damage mechanisms. Abbreviations:Ageing; Composites; Damage zone; Mechanical properties; Nondestructive technique Kocaeli,Özgür Bora, Turkey Kocaeli University, Faculty of Aeronautics and Astronautics, 41285, CBCT: Cone Beam Computed Tomography; FMLs: Fiber Metal Laminates; NDT: Non- Destructive Testing; SRM: Structure Repair Manuel; GLARE: Glass Reinforced Submission: Introduction Published: March 30, 2021 Structural weight of an aircraft has an extreme importance on fuel consumption, transport June 03, 2021 Volume 2 - Issue 1 capacity and flight performance due to the ratio (maximum payload)/(maximum take-off How to cite this article: weight).
[Show full text]