ANALISIS KEKUATAN MEKANIS HASIL SAMBUNGAN
ANTARA KOMPOSIT DENGAN ALUMINIUM SHEET METAL
DENGAN MENGGUNAKAN PROSES HOLE CLINCHING
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Hana Hardiyantie, Ravenskya
Subject
T Technology (General)
Datestamp
2024-07-19 08:26:26
Abstract :
Aluminum and composite materials are the types of materials that are used to construct structures on aircraft airframes. It is not uncommon for both types of materials to be used together with the joining method. In the process of connecting between two types of material in an aircraft structure, it is mostly carried out by the riveting method. This process is carried out by making a hole in the two materials according to the rivet diameter and then the hole diameter is then filled with rivets and the riveting process is carried out. The process uses rivets so that it will relatively increase the weight of the structure because there is additional rivet material. In this study, using Aluminum 2024-T3 and Composite CFRP and the objectives are to determine the mechanical strength of the joint between the composite and aluminum sheet metal using the mechanical clinching and riveting processes. The method used is an experimental method, namely by making test specimens with composite and aluminum, solid rivet type fasteners and punches with single lap joint treatment to determine the connection of the riveting, then the drilling process is carried out with a hole diameter of 3.5 mm, for the clinching method with variations in the diameter of the punch. 3.5mm, 4.0mm and 4.5mm. Then do a drag test and test macro photos. From the tensile test on riveting, it was found that the average result at the maximum load was 1059 Newton, the average yield strength was 113 and the average tensile strength was 151. From the tensile test in clinching, it was found that the average maximum load was 1884 Newtons, the average yield strength was 233 and the average tensile strength was 344. From the results of tensile testing and macro photos, it was found that the ability to withstand loads (load) on the specimen tested by clinching was 825 Newton because the damage length (gap) value was obtained at the connection boundary with the test material.
Aluminum and composite materials are the types of materials that are used to construct structures on aircraft airframes. It is not uncommon for both types of materials to be used together with the joining method. In the process of connecting between two types of material in an aircraft structure, it is mostly carried out by the riveting method. This process is carried out by making a hole in the two materials according to the rivet diameter and then the hole diameter is then filled with rivets and the riveting process is carried out. The process uses rivets so that it will relatively increase the weight of the structure because there is additional rivet material. In this study, using Aluminum 2024-T3 and Composite CFRP and the objectives are to determine the mechanical strength of the joint between the composite and aluminum sheet metal using the mechanical clinching and riveting processes. The method used is an experimental method, namely by making test specimens with composite and aluminum, solid rivet type fasteners and punches with single lap joint treatment to determine the connection of the riveting, then the drilling process is carried out with a hole diameter of 3.5 mm, for the clinching method with variations in the diameter of the punch. 3.5mm, 4.0mm and 4.5mm. Then do a drag test and test macro photos. From the tensile test on riveting, it was found that the average result at the maximum load was 1059 Newton, the average yield strength was 113 and the average tensile strength was 151. From the tensile test in clinching, it was found that the average maximum load was 1884 Newtons, the average yield strength was 233 and the average tensile strength was 344. From the results of tensile testing and macro photos, it was found that the ability to withstand loads (load) on the specimen tested by clinching was 825 Newton because the damage length (gap) value was obtained at the connection boundary with the test material.
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