Scholarlink

<p>Deployable space structures require low mass, high reliability, and precise actuation, particularly for long-duration satellite missions where failure cannot be tolerated. This paper presents a design and optimization framework for a composite slotted tube tape spring hinge used in solar panel deployment. A 12&#xa0;K T700 carbon fiber fabric with epoxy matrix was selected as the base material, and samples were fabricated and tested for viscoelastic behavior through shear relaxation. Relaxation-derived material parameters were incorporated into a finite element model to simulate long-term stiffness decay. The hinge geometry was optimized to enhance deployment speed, reduce overshoot, and ensure reliable performance over extended stowage periods. Simulation results showed a deployment time of 0.52s and a load-bearing capacity exceeding 1&#xa0;kg, even after 24 months of relaxation, meeting CubeSat requirements. The study demonstrates how time-dependent material modeling combined with geometry refinement can yield a lightweight, durable, and high-performance deployable mechanism for future satellite applications.</p>

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Design and Optimization of Tape Spring Hinges for Space Applications

  • 期刊论文

  • 发表日期：

    2026年1月13日

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  • Abdullah Tafzeel,
  • Muhammad Nouman Zafar,
  • Ruqia Ikram,
  • Yumna Qureshi

摘要

Deployable space structures require low mass, high reliability, and precise actuation, particularly for long-duration satellite missions where failure cannot be tolerated. This paper presents a design and optimization framework for a composite slotted tube tape spring hinge used in solar panel deployment. A 12 K T700 carbon fiber fabric with epoxy matrix was selected as the base material, and samples were fabricated and tested for viscoelastic behavior through shear relaxation. Relaxation-derived material parameters were incorporated into a finite element model to simulate long-term stiffness decay. The hinge geometry was optimized to enhance deployment speed, reduce overshoot, and ensure reliable performance over extended stowage periods. Simulation results showed a deployment time of 0.52s and a load-bearing capacity exceeding 1 kg, even after 24 months of relaxation, meeting CubeSat requirements. The study demonstrates how time-dependent material modeling combined with geometry refinement can yield a lightweight, durable, and high-performance deployable mechanism for future satellite applications.