Composite bonded patch for fuselage panel

Published on 14 May 2021. Written by Gurudutt

Fiber-reinforced polymer composite is the preferred material for the construction of aircraft and spacecraft. Even used as structural materials for the development of fuselage and due to its applications in the various field, it is used as a primary source for designing aircraft.

Aircraft safety is improving by analyzing the defects in the fuselage and catastrophic failure investigations on aircraft structural components. The primary cause of failure identification and the analysis enable recommendations for corrective action.

Project Description:

Carbon Fiber: Carbon Fiber made up of carbon crystals aligned in a longitudinal axis. These crystals have long and flattened ribbons such that they form a closed structure. In turn, these ribbons also align in the respective axis with themselves within fibers. These fibers (containing flat ribbons of carbon crystals) in turn bundled by the manufacturer in a bunch of fibers and are woven into carbon cloth, made into a bent and swirled.
Adhesive: The fiber composites are bonded to themselves and numerous different substrates, with the help of cutting-edge adhesive formulation. These adhesives are available in the form of liquids, pastes and also as films for composite bonding. It provides the maximum strength, stability, and resistance on the exposure to high temperature.
Epoxy: When two or more objects with the different properties have to adhere to each other for a long duration, the best way to accomplish that is with epoxy

Parameters for calculation of composite Panel
Ultimate tensile strength = 1600Mpa
Density = 1800 kg/m³
Poisson’s ratio = 0.75
Elongation = 1.6%
Factor of safety = 1.5
Cross sectional area A = 200*2 = 400 mm²

Parameters for calculation of composite strip
Ultimate tensile strength = 377 Mpa
Tensile modulus E = 799 Mpa
Density = 1800 kg/m³
Poisson’s ratio = 0.75
Factor of safety = 1.5
Cross sectional area A = 25*2 = 50 mm²

Methodology:

Material selection is done based on the need.
Evaluate the damage and find the repair technique
3D modeling of the composite panel is done.
Apply the boundary conditions for analysis
An analysis of the repaired panel is done.
Fabrication and testing of best repair technique
Comparison of results and validation

Future Work:

The future works that can be done in this project are:

Compressive test for the various aerodynamic loading
Bending test for the various aerodynamic loading.

This project is on carbon composite but in the future, it can be carried on aramid and glass fiber also.

Kit required to develop Composite bonded patch for fuselage panel:

Technologies you will learn by working on Composite bonded patch for fuselage panel:

Composite bonded patch for fuselage panel

Any Questions?

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