PERBANDINGAN KEKUATAN STRUKTUR KOMPOSIT LAMINATE DENGAN STRUKTUR KOMPOSIT SANDWICH PADA FUSELAGE PESAWAT PUNA AD-01

Tanwirul Anhar, Mohammad (2021) PERBANDINGAN KEKUATAN STRUKTUR KOMPOSIT LAMINATE DENGAN STRUKTUR KOMPOSIT SANDWICH PADA FUSELAGE PESAWAT PUNA AD-01. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

PUNA AD 01 is a development of PUNA which has a mission to monitor an area and survey land in agriculture. One of the important parts of the PUNA AD 01 is the fuselage where this part is where the wings, tail ,and engine are attached, for the fuselage part uses a laminate and sandwich composite structure with foam as the core and fiberglass as the layer. It’s because the mission of the PUNA AD 01 causes the structure of the PUNA AD 01 fuselage to be strong, so there is a need for consideration in the use of the type of composite used in this fuselage. This study discusses the analysis of the comparison of laminate composite structure strength with sandwich composite structure on PUNA 01 aircraft fuselage with two loadings, namely weight and lift. The stress analysis process on the PUNA AD 01 fuselage uses the Simulia Abaqus software. This analysis has carried out by providing loading during cruise conditions for lift loads. From the results of the analysis, it showed that the maximum stress that occurs will later be used to calculate the strength of the structure and the margin of safety. So it can be known whether the structure is safe or not. After analyzing the fuselage structure of the PUNA AD 01 aircraft, the maximum stress was obtained based on the stress values o1, o2, T12 and Von misses, then the largest maximum stress value was obtained in the laminate composite with the largest maximum stress value obtained at lamina 6 90 0 at o1 load weight with a stress value of 1,397x108 N/m2 and the smallest value has obtained at lamina 4 90 0 at o2 lift force with a stress value of 5,673x103 N/m2 , while for sandwich composites with the largest maximum stress value has obtained in lamina 4 0 0 at T12 loads weight with a stress value of 5,722x109 N/m2 and the smallest value has obtained in lamina 3 core at the value of Von missess the lift force with a stress value of 6,607x102 N/m2 . After analyzing the fuselage structure of the PUNA AD 01 aircraft, it can be concluded that the sandwich composite structure and the laminate composite structure are safe based on the structural strength values obtained

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