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World’s first spaceflight on-orbit demonstration of a flexible solar array system based on shape memory polymer composites

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Abstract

With a 10% reversible compressive strain in more than 10 deformation cycles, the shape memory polymer composites (SMPCs) could be used for deployable structure and releasing mechanism. In this paper, without traditional electro-explosive devices or motors/controllers, the deployable SMPC flexible solar array system (SMPC-FSAS) is studied, developed, ground-based tested, and finally on-orbit validated. The epoxy-based SMPC is used for the rolling-out variable-stiffness beams as a structural frame as well as an actuator for the flexible blanket solar array. The releasing mechanism is primarily made of the cyanate-based SMPC, which has a high locking stiffness to withstand 50 g gravitational acceleration and a large unlocking displacement of 10 mm. The systematical mechanical and thermal qualification tests of the SMPC-FSAS flight hardware were performed, including sinusoidal sweeping vibration, shocking, acceleration, thermal equilibrium, thermal vacuum cycling, and thermal cycling test. The locking function of the SMPC releasing mechanisms was in normal when launching aboard the SJ20 Geostationary Satellite on 27 Dec., 2019. The SMPC-FSAS flight hardware successfully unlocked and deployed on 5 Jan., 2020 on geostationary orbit. The triggering signal of limit switches returned to ground at the 139 s upon heating, which indicated the successful unlocking function of SMPC releasing mechanisms. A pair of epoxy-based SMPC rolled variable-stiffness tubes, which clapped the flexible blanket solar array, slowly deployed and finally approached an approximate 100% shape recovery ratio within 60 s upon heating. The study and on-orbit successful validation of the SMPC-FSAS flight hardware could accelerate the related study and associated productions to be used for the next-generation releasing mechanisms as well as space deployable structures, such as new releasing mechanisms with low-shocking, testability and reusability, and ultra-large space deployable solar arrays.

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Authors and Affiliations

  1. Center for Composite Materials and Structures, Harbin Institute of Technology, Harbin, 150080, China

    Xin Lan, FengHua Zhang, LinLin Wang, SiDa Hao, Xue Wan & JinSong Leng

  2. Department of Aerospace Science and Mechanics, Harbin Institute of Technology, Harbin, 150001, China

    LiWu Liu, ZhengXian Liu, QiFeng Li, Fan Peng, WenXu Dai & YanJu Liu

  3. Institute of Telecommunication Satellite, China Academy of Space Technology, Beijing, 100094, China

    Yong Tang, Mian Wang & YanYan Hao

  4. State Key Laboratory of Space Power-Sources Technology, Shanghai Institute of Space Power-sources, Shanghai, 200245, China

    Yang Yang & Cheng Yang

Authors
  1. Xin Lan
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  2. LiWu Liu
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  3. FengHua Zhang
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  7. Fan Peng
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  9. WenXu Dai
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  10. Xue Wan
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  11. Yong Tang
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  13. YanYan Hao
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  14. Yang Yang
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  15. Cheng Yang
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  16. YanJu Liu
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  17. JinSong Leng
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Corresponding author

Correspondence to JinSong Leng.

Additional information

The authors appreciate the direction and help from Institute of Telecommunication Satellite, China Academy of Space Technology (CAST), and the support from State Key Laboratory of Space Power-Sources Technology where the flexible blanket solar array was specially developed for SMPC-FSAS project. This work was supported by the National Natural Science Foundation of China (Grant No. 11632005).

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Lan, X., Liu, L., Zhang, F. et al. World’s first spaceflight on-orbit demonstration of a flexible solar array system based on shape memory polymer composites. Sci. China Technol. Sci. 63, 1436–1451 (2020). https://doi.org/10.1007/s11431-020-1681-0

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  • DOI: https://doi.org/10.1007/s11431-020-1681-0

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