Composite Structure Configuration Analysis of A320 Fuselage at Different Fiber Orientation

• Main Author: Utama, Ilham
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/34567
• Institution: Institut Teknologi Bandung

Aviation Industries continues to get an increased number of consumer every year. These condition cause the demand from the operators to increase efficiency of the aircraft, in order to decrease the operational cost. One of the most popular methods to increase the efficiency of aircrafts is by using composite which has higher specific strength than preceding materials to achieve a reduction of aircraft weight. Composite is used in some parts of the aircraft such as wing, fuselage, tail, etc. This final project is focused on the top panels of Airbus A320’s fuselage. At aircraft design process, composite’s usage is depended by the load which is caused by aircraft’s operational. Some modification that could be done is by adjusting the composites thickness or composite fiber angle. Therefore, composite structure configuration analysis at different fiber and thickness is needed. Load case calculation is done by using theoritical approach. There are three failure criterion which is used such as Tsai-Hill criterion, skin buckling criterion, and shear buckling criterion. Tsai-Hill criterion is determined using numerical approach in Abaqus, while skin buckling criterion and shear buckling criterion are determined by using analytical approach. The load case calculation shows that 5G + cabin pressurization, 1G, lateral gust load, and 1.33 cabin pressurization are the most critical load cases for the top panel of fuselage. Furthermore, the theoritical calculation also shows that the most critical point in the top panels is at the panel which has similar distance to nose with front spar’s distance to the nose. From the analysis which is done at those panel, the thickness and layup of the composite are 4.416 mm and [(0/90/46/-46)3]S.