Formation-Keeping Control of the Closed-Chain System

  • Panfeng HuangEmail author
  • Fan Zhang
Part of the Springer Tracts in Mechanical Engineering book series (STME)


The three-body closed-chain system cannot achieve the ideal LP equilibrium state under uncontrolled state, the main reasons are that there are slack and rebound phenomena in the tether between the three spacecraft, which is due to the low rotational rate of the tether system in the initial condition of LP equilibrium and the inability of the tether to withstand the pressure.


  1. 1.
    Wertz JR, Larson WJ (1999) Space mission analysis and design. California Microcosm Press, El SegundoGoogle Scholar
  2. 2.
    Kumar KD, Yasaka T (2004) Rotating formation flying of three satellites using tethers. J Spacecr Rocket 41(6):973–985CrossRefGoogle Scholar
  3. 3.
    Huang PF, Hu ZH, Meng ZJ et al (2015) Coupling dynamics modelling and optimal coordinated control of tethered spacerobot. Aerosp Sci Technol 41(2):36–46CrossRefGoogle Scholar
  4. 4.
    Wang DK, Huang PF et al (2014) Coordinated control of tethered space robot using mobile tether attachment point in approaching phase. Adv Space Res 54(6):1077–1091CrossRefGoogle Scholar
  5. 5.
    Wang DK, Huang PF et al (2015) Coordinated stabilization of tumbling targets using tethered space manipulators. IEEE Trans Aerosp Electron Syst 51(3):2420–2431CrossRefGoogle Scholar
  6. 6.
    Huang PF, Zhang F, Ma J (2015) Dynamics and configuration control of the maneuvering-net space robot system. Adv Space Res 55(4):1004–1014CrossRefGoogle Scholar
  7. 7.
    Huang PF, Hu ZH, Zhang F (2016) Dynamic modelling and coordinated controller designing for the manoeuvrable tether-net space robot system. Multibody Syst Dyn 36(2):115–141MathSciNetCrossRefGoogle Scholar
  8. 8.
    Vogel KA (2006) Dynamics and control of tethered satellite formations for the purpose of space-based remote sensing. Air Force Institute of Technology, OhioGoogle Scholar
  9. 9.
    Williams P (2006) Periodic optimal control of a spinning earth-pointing tethered satellite formation. In: Proceedings of the AIAA/AAS astrodynamics specialist conference and exhibit, Keystone, Colorado, AmericaGoogle Scholar
  10. 10.
    Mori O (2007) Formation and attitude control for rotational tethered satellite clusters. J Spacecr Rocket 44(1):211–220CrossRefGoogle Scholar
  11. 11.
    Hussein I, Schaub H (2009) Stability and control of relative equilibria for the three-spacecraft coulomb tether problem. Acta Astronaut 65(5):738–754CrossRefGoogle Scholar

Copyright information

© Springer Nature Singapore Pte Ltd. 2020

Authors and Affiliations

  1. 1.National Key Laboratory of Aerospace Flight Dynamics, School of Astronautics, Research Center for Intelligent RoboticsNorthwestern Polytechnical UniversityXi’anChina

Personalised recommendations