Probabilistic assessment of failure in adhesively bonded composite laminates
- Clarkson Univ., Potsdam, NY (United States)
- National Aeronautics and Space Administration, Cleveland, OH (United States). Lewis Research Center
Damage initiation and progressive fracture of adhesively bonded graphite/epoxy composites is investigated under tensile loading. A computer code is utilized for the simulation of composite structural damage and fracture. Structural response is assessed probabilistically during degradation. The effects of design variable uncertainties on structural damage progression are quantified. The Fast Probability Integrator is used to assess the response scatter in the composite structure at damage initiation. Sensitivity of the damage response to design variables is computed. Methods are general purpose in nature and are applicable to all types of laminated composite structures and joints, starting from damage initiation to unstable damage propagation and collapse. Results indicate that composite constituent and adhesive properties have a significant effect on structural durability. Damage initiation/progression does not necessarily begin in the adhesive bond. Design implications with regard to damage tolerance of adhesively bonded joints are examined.
- OSTI ID:
- 485109
- Report Number(s):
- CONF-970146--; ISBN 1-890277-03-7
- Country of Publication:
- United States
- Language:
- English
Similar Records
Progressive damage and fracture of adhesively bonded fiber composite pipe joints
Damage prognosis of adhesively-bonded joints in laminated composite structural components of unmanned aerial vehicles