ANALISIS KEKUATAN STRUKTUR WING PESAWAT UDARA NIR AWAK (PUNA) BERTENAGA ELEKTRIK TERHADAP BEBAN BENDING

Akram, M. Irfan (2023) ANALISIS KEKUATAN STRUKTUR WING PESAWAT UDARA NIR AWAK (PUNA) BERTENAGA ELEKTRIK TERHADAP BEBAN BENDING. Thesis thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

Wing is the main structure of an airplane wing that functions to produce lift. Wing on the UNCREW AIRCRAFT (PUNA) ELECTRICALLY POWERED must have a structure that meets the criteria of strength and stiffness and must be able to withstand the loads that occur, one of which is bending loads. Wing bending strength can be identified by bending testing. Bending test is a process of testing material by pressing it to get results in the form of data about the bending strength of a material being tested. The purpose of this final project is to determine the maximum load that can be resisted by wing. Wing (PUNA) made balsa wood and carbon fiber. The research method used is the experimental method, where the research starts from the preparation of tools and materials, the process of making the wings, and testing the wing accompanied by measurements and calculations. Wing testing uses the bending method and loading uses the schrenk method in which the method is quite accurate for aircraft wings to calculate the load distribution due to aerodynamic forces. For the process, the fulcrum is in the middle of the wing and each rib will be gradually loaded until the wing being tested breaks. From the test results obtained damage to the upper, rib 1 fracture, and fracture on the joiner. The wing deflection value before fracture is 19 mm and the maximum bending load of the wing is 97,5133 N.

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