Compression-After-Impact analysis of carbon fiber reinforced composite laminate with different ply orientation sequences

This article explores the experimental and numerical study in ABAQUS/explicit of the post-impact damage progression in carbon/epoxy composite laminate under compression. LVI (Low-Velocity Impact) tests at three different energy levels followed by CAI (Compression-After Impact) tests are carried out as per ASTM standards. Damage envelopes are studied by NDE (Non-Destructive Evaluation) technique, using X-ray computed tomography. The results of the numerical study match well with the experimental study. It is seen that the CAI strength depends on the factors like properties of the constituent material, ply orientations and stacking sequence, and thickness of the laminate. It has been observed that even with the barely visible impacts, the compressive strength of the laminate has been reduced drastically. The mode of failure observed is buckling of the laminates in the damaged zone due to impact, especially at the back face of the specimen where damage was more. The size of the damaged zone increases as the impact energy increases and reduces the CAI strength of the laminate.

Automated summary

This article investigates the progression of post-impact damage in carbon/epoxy composite laminates under compression through experimental and numerical studies using ABAQUS/explicit. The results from experiments and numerical simulations show good agreement. It is found that the CAI strength of the laminates depends on various factors such as constituent material properties, ply orientations, stacking sequence, and laminate thickness. The study also reveals that even barely visible impacts can significantly reduce the compressive strength of the laminate.