Optimization of a Hybrid Carbon/Glass Composites Afterbody of the Amphibious Plane with Finite Element Analysis
Keywords:composite material, hybrid carbon/glass fiber composites, light sport aircraft, composite fuselage, FEA
The main objective of this research is to find the optimized lay up for the
afterbody of the amphibious plane which can carried load according to ASTM F2245
(Standard Specification for Design and Performance of a Light Sport Airplane).
The finite element analyses of hybrid carbon/glass composites are carried out using
ANSYS ACP under assumption that the hybrid carbon/glass fiber composites could
combine the strong sides of carbon and glass fiber reinforced polymer to balance between
strength, weight and cost to achieve the requirement for each design of the aircraft.
While the stress of the carbon and glass fiber in the structure are within the safety limit,
the results show that the weight is minimum when the laminate ply pattern consists of 3.18
mm foam core (D) sandwiched by 3 layers of carbon woven fabrics on both side
[(±45)C(0/90)C(±45)CD̅]S. While the laminate ply pattern with 3.18 mm foam core
sandwiched by 2 layers of carbon and 1 layer of glass woven fabric
[(±45)C(0/90)C(±45)GD̅]S on both side have a good balance between weight and cost.
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