Open AccessExperimental Analysis of carbon fiber reinforcement T-Shaped stiffened composite Cleat/Panel with aluminum panel using UTM
Author(s) -
Ravindra Jambhorkar,
K.M. Nawasagare,
Subim Khan,
Avinash M. Badadhe
Publication year - 2021
Publication title -
international journal of engineering sciences
Language(s) - English
Resource type - Journals
ISSN - 0976-6693
DOI - 10.36224/ijes.140204
Subject(s) - composite number , fuselage , structural engineering , materials science , composite material , bending , ultimate tensile strength , reinforcement , fiber , aluminium , buckling , carbon fibers , carbon fiber composite , engineering
T-shaped composite cleat are used in thin walled structures including aircraft fuselage with wings, with the skin carrying membrane loads and the stiffeners carrying bending loads and resisting skin buckling. The project includes T-shaped stiffened Aluminum cleat will be used for analysis purpose along with Carbon fiber composite reinforcement T-stiffened composite cleat. The carbon fiber reinforced T-stiffened panels were manufactured with carbon fiber arranged in a [45/0/45/0/45] s ply pattern. The model of T-stiffened composite reinforces panels and T -stiffened Aluminum panel is made in Catia V5R20. Static structural of specimen will be perform using ACP tool in ANSYS 19 software. In experimentation, tensile test of both specimens have been performed on UTM. The comparative analysis was carried out between the Analytical and experimental results. After manufacturing, the comparative analysis result and conclusion was drawn.