ANALISIS DAN PERANCANGAN STRUKTUR ANISOGRID KOMPOSIT PADA SAYAP PESAWAT TEMPUR MENGGUNAKAN METODE ELEMEN HINGGA

• Main Author: Akbar Adi Satriya, Ilham
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/34090
• Institution: Institut Teknologi Bandung

Fighter aircraft used by the military have a much higher complexity and used of higher technology than civilian passenger aircraft. Fighter aircraft are required to have the ability to maneuver to achieve their mission. The use of material in the design of fighter aircraft involves the latest material, namely composite. Composites are chosen because they have good structural strength and are able to reduce the mass of the structure of the fighter. Wings are one of the important structures in the aircraft. In this research will be analyze and design of anisogrid composite wing structures of fighter aircraft. Anisogrid means the design concept of architecture based on the arrangement of structure resembling plots or grids that have different mechanical properties in all direction (AN-ISOtropic) in case differences in mechanical properties refers to the use of composite materials. The analysis process begins with a literature study, modeling the structure of a composite fighter wing anisogrid using finite element software, analysis of strain results, displacement, and failure indices, and optimization of the number of lamina arrangements. The results showed that the composite anisogrid structure was safe and able to handle the given load, with a strain of 0.00296 mm / mm and failure indices of 0.994. Failure indices are structural failure parameters, if the value of failure indices below one is said to be safe. In addition, the mass of the composite anisogrid structure (701.7-968.5 kg) was compared to the conventional composite multi-spar structure (539.7-989.7 kg). From this period, it can be seen that the anisogrid structure has a lighter maximum mass with a comparison percentage of 2.19%. In addition, the anisogrid structure is also better when compared to conventional multi-spar structures, by looking at the results of strain and displacement at the end of the wing with a percentage of 2.95% and 11.21% smaller.