Journal of Materials Science

, Volume 45, Issue 1, pp 192–200 | Cite as

Tensile properties and fracture behaviour of carbon fibre filament materials

  • Sweety Kumari
  • S. Nithya
  • N. Padmavathi
  • N. Eswara PrasadEmail author
  • J. Subrahmanyam


Monotonic tensile properties and fracture behaviour of carbon fibre filament materials, namely single/mono- and multi-filaments (two and four filaments) as well as virgin carbon tows have been evaluated and discussed. Micro composite or single fibre approach is used in this study, which facilitated the evaluation of tensile properties and nature of fracture of carbon filament materials in a relatively short time with a large number of inexpensive trials. Tensile tests have been conducted on these filament materials at ambient temperature and laboratory air atmosphere. Load–elongation and the corresponding stress–strain plots thus obtained have been analysed to understand the tensile behaviour. The peak tensile strength of single carbon filament is found to be 3.8 GPa, and the value of the resilience obtained is 19 MJ/m3. The peak tensile strength was found to increase moderately with further increase in number of filaments. However, the value of resilience was found to increase with increase in the number of fibres, which is attributed to the controlled failure of multi-filaments. On the other hand, the tensile strength of virgin carbon tow without matrix was found to be 1.13 GPa, and the value of the fracture energy was determined to be 9.9 MJ/m3, which is nearly one fourth or even less than the corresponding values of the mono- and multi-filaments. The data obtained in the case of the virgin carbon tows were further analysed to evaluate the Weibull statistical parameters.


Carbon Fibre Fracture Energy Single Fibre Weibull Modulus Corrected Stress 



The authors are indebted to Dr. AM Srirama Murty and Dr. G Malakondaiah, former and present Directors, respectively, Defence Metallurgical Research Laboratory (DMRL) for their constant encouragement, and kind permission to publish this article. The authors express their grateful thanks to Dr. M Srinivas and Dr. Vikas Kumar of DMRL for many useful suggestions. The authors are also grateful to Smt. G Rohini Devi, Scientist, Advanced Systems Laboratory, Hyderabad for the provision of the facilities to conduct some of the experiments for this study. Funding from DRDO is gratefully acknowledged.


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Copyright information

© Springer Science+Business Media, LLC 2009

Authors and Affiliations

  • Sweety Kumari
    • 1
  • S. Nithya
    • 3
  • N. Padmavathi
    • 2
  • N. Eswara Prasad
    • 4
    Email author
  • J. Subrahmanyam
    • 1
  1. 1.Defence Metallurgical Research LaboratoryHyderabadIndia
  2. 2.Advanced Systems LaboratoryHyderabadIndia
  3. 3.Department of Mechanical and Industrial EngineeringConcordia UniversityMontrealCanada
  4. 4.Regional Centre for Military Airworthiness (Materials), CEMILAC, DRDOHyderabadIndia

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