A Process Method and Simulation Analysis of Spacecraft Wing Root Cable Fixing

  • Kai XuEmail author
  • Lijian Zhang
  • Hao Li
Conference paper
Part of the Lecture Notes in Electrical Engineering book series (LNEE, volume 550)


In order to avoid the situation that the cable is damaged during the unfolding and folding process of solar wings, a spacecraft solar wing root cable tying process is designed. Through the simulation of the root-hinge cable laying process, it is concluded that setting the appropriate reserved length and cable tie point, improving the installation flexibility of the wire harness, and the wire harness can be prevented from being stressed after the connector is plugged, thereby improving the service life of the cable. Then through the simulation of the motion of the root cable, it is concluded that the interference of the root cable is not affected during the deployment of the solar wing, and the correctness of the static simulation is verified, which provides a theoretical basis for the satellite assembly operation.


Multiple deployment of solar wing Root cable Process method Simulation analysis 


  1. 1.
    Fei, K.: Design and Performance Test of Repeated Folding and Locking Solar Wing Mechanism. Zhe jiang University of Technology, Hangzhou (2013)Google Scholar
  2. 2.
    Yang, J., Huang, H., Liu, Y., et al.: The evidential network for fault tree analysis with imprecise knowledge. Int. J. Turbo Jet Engines 29(2), 111–122 (2012)Google Scholar
  3. 3.
    Zhou, Z., Wu, Y., Wang, J., et al.: Development status and trend of the circular solar wing. Spacecr. Eng. 24(6), 116–122 (2015)Google Scholar
  4. 4.
    Zhang, L.: Design and Research of the Spacecraft Step-and-Expanding Solar Wing. Shanghai Jiaotong University, Shanghai (2012)Google Scholar
  5. 5.
    Li Entrusted: Tension design and analysis of the solar wing linkage device. Chin. Space Sci. Technol. 26(2), 52–57 (2006)Google Scholar
  6. 6.
    Eacret, D.L., White, S.: ST8 validation experiment: Ultraflex-175 solar array technology advance: deployment kinematics and deployed dynamics ground testing and model validation. In: AIAA 2010-1497. AIAA, Washington D.C. (2010)Google Scholar
  7. 7.
    Hua, D.: Design and Analysis of the Repetitive Locking and Release Mechanism of the Solar Wing. Harbin Institute of Technology, Harbin (2008)Google Scholar
  8. 8.
    Wang, X., Yan, H., Zhou, Z.: Development status and trend of two-dimensional multiple-expansion solar wing technology. In: Expandable Spatial Structure (2014)Google Scholar
  9. 9.
    Liu, Z., Wu, Y., Qi, H., et al.: Evaluation method for reliability of spacecraft solar wing expansion. Chin. Space Sci. Technol. 52–56 (2013)Google Scholar
  10. 10.
    Solar, J.: Dynamic Fault Tree Analysis of Solar Wing Drive Mechanism. The university of Electronic Science and Technology of China (2012)Google Scholar
  11. 11.
    Ren, S., Shang, H., Shang, H., Qi, H.: Simulation analysis of deployment dynamics of a two-dimensional unfolded solar wing. Spacecr. Eng. 21(4), 32–36 (2012)Google Scholar
  12. 12.
    Murphy, D.M.: MegaFlex-the scaling potential of UltraFlex technology. In: AIAA 2012-1581. AIAA, Washington D.C. (2012)Google Scholar
  13. 13.
    Xinggao, Z., Fengxi, C., Tingwei, L., et al.: Research on vibration test specifications of solar wing drive mechanism based on modal analysis. Min. Mach. 38(5), 171–173 (2017)Google Scholar
  14. 14.
    Hu, M., Li, W., Chen, W., et al.: Motion simulation and functional experiment of repeated folding mechanism of sectoral solar wing. Chin. J. Space Sci. 36(1), 92–98 (2016)Google Scholar

Copyright information

© Springer Nature Singapore Pte Ltd. 2019

Authors and Affiliations

  1. 1.Beijing Institute of Spacecraft Environment EngineeringBeijingChina
  2. 2.Beijing Engineering Research Center of the Intelligent Assembly Technology and Equipment for Aerospace ProductBeijingChina

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