Abstract
The use of solar panels for generating power of satellite demands deployable structures which can be folded before launch and be deployed while in space. A hinge is a simple deployable structure that can be used as a driving device for deploying solar panels. Hinge made of polystyrene-interleaved carbon fibre composites having shape memory capability was proposed and investigated. It has been shown that the interleaved composites are able to be deformed from flat shape to U-shape at elevated temperature (re-shaping stage) and then able to maintain its deformed shape at room temperature. Moreover, the composites have ability to recover to its original shape once re-heated in an unconstrained state (shape recovery stage). The concept was conducted by attaching two panels on both sides of the interleaved composites (hinge) during those stages to see the shape memory capability. The outputs of this work are the spring back angle after the re-shaping stage and the final angle after shape recovery stage. The predictive analysis using simple beam theory is compared to the experimental results. The results showed the possibility of interleaved carbon fibre composites to be used in deployable structures.
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Acknowledgements
We gratefully acknowledge the financial support for Dharu Smaradhana provided by LPDP. We thank Prof. Paul Robinson from The Composite Centre, Imperial College London, for guidance, all facilities and specimens in carrying out this research.
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Smaradhana, D.F., Santoso, B. (2020). Interleaved Carbon Fibre Composites with Shape Memory Capability for Use in Hinge Deployment. In: Sabino, U., Imaduddin, F., Prabowo, A. (eds) Proceedings of the 6th International Conference and Exhibition on Sustainable Energy and Advanced Materials. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-15-4481-1_14
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DOI: https://doi.org/10.1007/978-981-15-4481-1_14
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