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<p>Thin-walled, straight booms made of fibre-reinforced polymer composites and having a lenticular cross section are considerably used in large deployable mechanisms. Such structures can be coiled and stored efficiently and released during the deployment. The structural behaviour of the boom is substantially dependent on two independent variables: thickness and radius of curvature. This paper investigates the strain energy of thin-walled lenticular composite booms during the rolling and unrolling of boom with thicknesses of 0.4&#xa0;mm, 0.6&#xa0;mm and 0.8&#xa0;mm, and a radius of curvature ranging from 24 to 44&#xa0;mm. The finite element method employing ABAQUS software is used to evaluate the strain energy variation during rolling and deployment process. The validation of initial computational study results was done by comparing with the results obtained through analytical formula. It was observed that the strain energy value increases progressively during the rolling process and is subsequently released during deployment, with its magnitude significantly influenced by wall thickness and radius of curvature. The configuration with a wall thickness of 0.4&#xa0;mm and radius of curvature of 24&#xa0;mm achieves the maximum stored strain energy of 33.24&#xa0;J. The study shows that strain energy increased with increasing thickness and decreased with increasing radius of curvature. It was additionally deduced that strain energy began to have a lesser variation when testing radius of curvature above 34&#xa0;mm. Also, considering very small curvature radii (&lt; 5&#xa0;mm) may be an issue of feasibility when manufacturing. The results obtained highlights that the design should balance flexibility, stiffness and deployment reliability of such booms. The present study thus helps in the better understanding of the deployment process of such straight composite booms suitable for spacecraft mechanisms.</p>

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Strain Energy Variation During the Rolling and Deployment of a Lenticular Composite Boom: A Computational Study

  • 期刊论文

  • 发表日期：

    2026年3月27日

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  • S. Balamurali,
  • Siva Aswika,
  • VM. Sreehari,
  • Hariharan Sankara Subramanian,
  • Sidharth Tiwary,
  • Milind Undale,
  • Mariya Ratlami

摘要

Thin-walled, straight booms made of fibre-reinforced polymer composites and having a lenticular cross section are considerably used in large deployable mechanisms. Such structures can be coiled and stored efficiently and released during the deployment. The structural behaviour of the boom is substantially dependent on two independent variables: thickness and radius of curvature. This paper investigates the strain energy of thin-walled lenticular composite booms during the rolling and unrolling of boom with thicknesses of 0.4 mm, 0.6 mm and 0.8 mm, and a radius of curvature ranging from 24 to 44 mm. The finite element method employing ABAQUS software is used to evaluate the strain energy variation during rolling and deployment process. The validation of initial computational study results was done by comparing with the results obtained through analytical formula. It was observed that the strain energy value increases progressively during the rolling process and is subsequently released during deployment, with its magnitude significantly influenced by wall thickness and radius of curvature. The configuration with a wall thickness of 0.4 mm and radius of curvature of 24 mm achieves the maximum stored strain energy of 33.24 J. The study shows that strain energy increased with increasing thickness and decreased with increasing radius of curvature. It was additionally deduced that strain energy began to have a lesser variation when testing radius of curvature above 34 mm. Also, considering very small curvature radii (< 5 mm) may be an issue of feasibility when manufacturing. The results obtained highlights that the design should balance flexibility, stiffness and deployment reliability of such booms. The present study thus helps in the better understanding of the deployment process of such straight composite booms suitable for spacecraft mechanisms.