Executive Summary
A composite materials analysis evaluating the mechanical behavior of a symmetric HM carbon laminate using Classical Laminate Theory. Engineering constants, laminate strains, and ply stresses were computed across varying fiber orientations to assess anisotropic behavior and structural response under applied loading.
Mission Context
Composite structures rely heavily on fiber orientation to achieve desired stiffness and strength characteristics. Understanding how orientation affects mechanical response is critical for designing lightweight, high-performance aerospace components.
System Architecture
A symmetric laminate stacking sequence [+θ/−θ/+30/−30]s was analyzed using given HM carbon material properties. The system models multilayer composite behavior under a defined in-plane stress state.
Technical Analysis
Laminate stiffness matrices were constructed and used to compute effective engineering constants, strains, and ply-level stresses. Calculations were performed across a range of fiber orientation angles to evaluate how stiffness, deformation, and stress distribution vary with θ.
Validation and Performance
Results showed strong dependence of stiffness and strain response on fiber orientation. Maximum longitudinal stiffness occurred when fibers aligned with the loading direction, while shear response peaked near 45°. The analysis confirmed expected anisotropic behavior and load distribution across plies.
Role and Impact
Individual Project
- Laminate stiffness and property calculations
- Engineering constant evaluation
- Strain and stress analysis
- Fiber orientation parametric study
- Data visualization and interpretation