STRUCTURAL STRENGTH ANALYSIS OF COMPOSITE BLADE STIFFENED PANEL UNDER PULL-OUT TENSILE LOADING USING FINITE ELEMENT METHOD AND EXPERIMENTAL

• Main Author: Handoko
• Format: Theses
• Language: Indonesia
• Subjects: Teknik (Rekayasa, enjinering dan kegiatan berkaitan)
• Online Access: https://digilib.itb.ac.id/gdl/view/47415
• Institution: Institut Teknologi Bandung

Composite blade stiffened panels are structures that are widely used in aircraft structures such as wings and fuselage. Generally, the stiffener installation on the panel aims to add stiffeness so that the structure is more rigid, strong but light weight. Finding out the strength of the blade stiffened panel structure, simulation & test are needed. One of the test methods carried out is a tensile test. Determining the maximum load/strength, the test is carried out by giving a load until the structure is deformed or failure. The load is given to the tensile test in this study in the form of a displacement rate of 2 mm / minute [ASTM D3039]. In this study, numerical simulation by using finite element method was carried out to analyze progressive failure in the composite using quasi isotropic material in MSC Patran / Nastran software. The simulation results are in the form of maximum load and strength then compared with the results of the test. The results of the test, the average maximum load is 4232N at a displacement of 1.99 mm. While the maximum load simulation results that occur amounted to 4870 N for Maximum Stress failure criteria, 5119 N for Tsai Hill failure criteria and 5144 N for Tsai Wu failure criteria at a displacement of 1.1 mm. The difference between the experimental and simulation results are 13% for the criteria for failure of Maximum Stress, 17% Tsai Hill and 18% for Tsai Wu. The maximum strength of blade stiffened panel composite structure from experimental results is 45.9 MPa.