Composite Fuselage Project

Objective
Design, manufacture, and test a 24” E-glass/Nomex composite fuselage section for SAMPE.

Overview

Analytical modeling (CLT) + ABAQUS FEM + full-scale experimental validation.

Key Results

• 38% deflection reduction after laminate optimization.
• 2591 lbf at 1” deflection (≥150% of design load).
• ±2 mm dimensional accuracy after 275°F, 40 psi, 90 min autoclave cure.

Methods

• CLT + Tsai-Wu for sizing.
• ABAQUS shell model for stiffness and failure checks.
• Manufacturing: 7781 E-glass prepreg, 32% RC, Nomex 48 kg/m³ core, vacuum bag + autoclave.
• Testing: three-point bend, load–deflection capture and FEM comparison.

Repo Map

Next

• Progressive failure modeling in ABAQUS.
• Python loop for laminate optimization.
• Add DIC strain mapping.

Author: Siddardth Pathipaka · siddardth1524@gmail.com · LinkedIn: siddardth-pathipaka