Scholarlink

<p>Deployable structures play a crucial role in space applications, where compact storage and reliable deployment are essential for efficient operation. Shape memory polymer composites (SMPC) present a promising alternative due to their lightweight nature, high strain recovery, and adaptive stiffness. This work presents a comprehensive study of the viscoelastic properties of carbon fibre reinforced shape memory epoxy composites (CFREP) using temperature-step/hold multi-frequency dynamic mechanical analysis (DMA). The experimental study was conducted by performing DMA testing on the composites using a 3-point bend loading and a temperature step-and-hold multi-frequency loading condition. At a given frequency of 1&#xa0;Hz and a range of temperatures, the storage modulus (E′), loss modulus (E′′) and dissipation factor (tanδ) were studied as important viscoelastic properties. A study was conducted into the effects of temperature and multi- frequency loading (0.1 to 10&#xa0;Hz) on the CFREP composite E′, E′′ and glass transition temperature (T<sub>g</sub>). Further the variation of stiffness with temperature in CFREP composite was predicted using Mahieux Reifsnider stiffness-temperature model. Results show strong temperature- and frequency-dependent viscoelastic behavior, with 1.0 wt% CFREP exhibiting optimal stiffness and damping characteristics. Cole-Cole analysis confirms effective fibre-matrix interaction, while the Mahieux-Reifsnider model successfully predicts stiffness variation with temperature. An SMPC-based hinge integrated with a spring-loaded pin-locking mechanism is proposed for the controlled deployment of solar arrays in antenna systems. The integration of SMPC-hinges in space structures offers significant advantages, including reduced weight, mechanical simplicity, and enhanced reliability, making them highly suitable for next-generation satellite applications.</p>

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Viscoelastic and stiffness modelling of CF dispersed shape memory epoxy composites: a deployable solar concept

  • 期刊论文

  • 发表日期：

    2026年2月21日

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  • Avadesh Yadav,
  • Satish Kumar,
  • Abhishek Kumar

摘要

Deployable structures play a crucial role in space applications, where compact storage and reliable deployment are essential for efficient operation. Shape memory polymer composites (SMPC) present a promising alternative due to their lightweight nature, high strain recovery, and adaptive stiffness. This work presents a comprehensive study of the viscoelastic properties of carbon fibre reinforced shape memory epoxy composites (CFREP) using temperature-step/hold multi-frequency dynamic mechanical analysis (DMA). The experimental study was conducted by performing DMA testing on the composites using a 3-point bend loading and a temperature step-and-hold multi-frequency loading condition. At a given frequency of 1 Hz and a range of temperatures, the storage modulus (E′), loss modulus (E′′) and dissipation factor (tanδ) were studied as important viscoelastic properties. A study was conducted into the effects of temperature and multi- frequency loading (0.1 to 10 Hz) on the CFREP composite E′, E′′ and glass transition temperature (Tg). Further the variation of stiffness with temperature in CFREP composite was predicted using Mahieux Reifsnider stiffness-temperature model. Results show strong temperature- and frequency-dependent viscoelastic behavior, with 1.0 wt% CFREP exhibiting optimal stiffness and damping characteristics. Cole-Cole analysis confirms effective fibre-matrix interaction, while the Mahieux-Reifsnider model successfully predicts stiffness variation with temperature. An SMPC-based hinge integrated with a spring-loaded pin-locking mechanism is proposed for the controlled deployment of solar arrays in antenna systems. The integration of SMPC-hinges in space structures offers significant advantages, including reduced weight, mechanical simplicity, and enhanced reliability, making them highly suitable for next-generation satellite applications.