ANALISIS DAN OPTIMASI STRUKTUR ANISOGRID KOMPOSIT SAYAP PESAWAT TEMPUR DENGAN KRITERIA KEGAGALAN STATIK, BUCKLING DAN FLUTTER MENGGUNAKAN METODE ELEMEN HINGGA

• Main Author: Muhammad Naufal Ramadhan, Teuku
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/61782
• Institution: Institut Teknologi Bandung

In this undergraduate thesis, an analysis and optimization is carried out on a fighter wing model with a composite anisogrid configuration. The analysis was conducted to determine the response of the anisogrid sandwich structure to static load, buckling, and flutter. Anisogrid structure means the structure is designed in a grid-like arrangement that has different mechanical strength properties in all directions (anisotropic), in this case differences in mechanical properties in certain directions refer to the use of composite materials. The wing structure is designed with the arrangement of spars on the wingbox which has an anisogrid configuration. This undergraduate thesis is a continuation of the undergraduate thesis conducted by Ilham [1] and Bakti [2] who performed static strength analysis on a model of a fighter aircraft wing with orthogonal and anisogrid configurations. In this undergraduate thesis analysis of static, buckling and flutter will be carried out on the wing of a fighter aircraft with an anisogrid configuration to find the wing strenght against static load, buckling, and flutter. The wing structure will then be optimized with the limitation of static failure, buckling, and flutter speed to obtain the optimal thickness of the wing structure. The results show that the anisogrid wing can whitstand from static load, buckling, and flutter at speed below 500 m/s using triangle distribution load with half wing mass of 504,1 kg, using Schrenk’s distribution load with half wing mass of 571,1 kg, and using constant distribution load with half wing mass of 706,8 kg