Experimental Test on Glare Composite of an Aircraft Structure Under Tensile Strength Failure
B. Nagaraj Goud1, K. Shiva Shankar2, B. Manideep3, K. Veeranjaneyulu4
1B. Nagaraj Goud, Assistant Professor, Department of Aeronautical Engineering, MLR Institute of Technology, Hyderabad (Telangana) India.
2K. Shiva Shankar, Assistant Professor, Department of Aeronautical Engineering, MLR Institute of Technology, Hyderabad (Telangana) India.
3B. Manideep, Assistant Professor, Department of Aeronautical Engineering, MLR Institute of Technology, Hyderabad (Telangana) India.
4K. Veeranjaneyulu, Assistant Professor, Department of Aeronautical Engineering, MLR Institute of Technology, Hyderabad (Telangana) India.
Manuscript received on November 18, 2019. | Revised Manuscript received on December 15, 2019. | Manuscript published on December 30, 2019. | PP: 674-677 | Volume-9 Issue-2, December, 2019. | Retrieval Number: B3005129219/2020©BEIESP | DOI: 10.35940/ijeat.B3005.129219
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: A Glass Aluminum fiber metal laminate GLARE is a set of materials manufactured by strong bonding glass/epoxy layers within the metal layers. The combined set of materials will be providing the better mechanical properties and weight reduction for an aircraft structure. The fiber metal laminate model was fabricated as per ASTM standards 200×30×5mm and then the experimental test under tensile loading test was conducted by using universal testing machine UTM as observed the stress-strain curve as the failure strength of GLARE reaching point and finally obtained results. Also to determine the mechanical properties and material characteristics of the unidirectional loading on E-glass fibers used to assemble GLARE for an aircraft structure.
Keywords: Fiber metal laminate, Mechanical properties, Universal testing machine, Tensile strength, Failure.