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Effect of fiber tension on physical and mechanical properties of filament wound carbon/epoxy composite specimen

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Abstract

Composite pressure vessels and shells for aerospace applications demand enhanced structural performance with lesser inert mass. Optimum fiber tension during filament winding can significantly improve their structural performance; therefore, the fiber tension effect is studied on the carbon/epoxy composite specimen level. Fiber tension is varied from 0.5 to 6.0 kg during filament winding of composite specimens. Naval ordnance laboratory (NOL) ring and cylindrical shell specimens are made at different fiber tensions. The physical and mechanical properties of these specimens are investigated. Fiber volume fraction and hoop tensile strength of NOL ring specimens are increased by around 26% and 29%, respectively, at 4 kg fiber tension compared to 1 kg. The mass and thickness of the composite shells are reduced by around 19.5% and 24.5%, respectively, at 4 kg fiber tension compared to that of 1 kg. The experiment and result conclude an optimal fiber tension of 4 kg/ tow for efficient filament wound carbon/ epoxy composite specimen.

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Acknowledgement

The authors acknowledge the invaluable support and encouragement provided by the Director of Advanced Systems Laboratory (ASL) and the Technology Director of CPDC at ASL. The authors are immensely thankful to Dr. G Ramarao and his team at CPDC for providing tireless help in testing a large volume of specimens and sharing his hands-on experience during the whole exercise.

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Authors and Affiliations

  1. Advanced Systems Laboratory, Hyderabad, 500058, India

    Surjeet Kumar Sinha & Manoj Kumar Buragohain

  2. National Institute of Technology, Warangal, 506004, India

    Surjeet Kumar Sinha & P Subhash Chandra Bose

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  1. Surjeet Kumar Sinha
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  2. Manoj Kumar Buragohain
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  3. P Subhash Chandra Bose
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Correspondence to P Subhash Chandra Bose.

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Sinha, S.K., Buragohain, M.K. & Bose, P.S.C. Effect of fiber tension on physical and mechanical properties of filament wound carbon/epoxy composite specimen. Sādhanā 49, 116 (2024). https://doi.org/10.1007/s12046-024-02464-5

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  • DOI: https://doi.org/10.1007/s12046-024-02464-5

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