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Attitude Control of Underactuated and Momentum-Biased Satellite Using State-Dependent Riccati Equation Method

  • Jaehyun Jin
Original Paper

Abstract

This paper deals with the attitude control problem of an underactuated satellite controlled by two reaction wheels. The angular momentum of the satellite is assumed to be non-zero or biased. Under these conditions, rotation to arbitrary attitude (roll, pitch, and yaw) is not possible, but direction or limited attitude control (roll and pitch) is possible. For such control, a nonlinear controller is proposed to utilize the angular momentum as gyroscopic torque. The controller is designed using the State-Dependent Riccati Equation (SDRE) method. This SDRE method provides a systematic way to design nonlinear controllers for diverse combinations of two reaction wheels. The proposed method has been verified by numerical simulations and the designed control system works satisfactorily.

Keywords

Satellite attitude control Underactuated Momentum bias Two reaction wheels State-dependent Riccati equation method 

Notes

Acknowledgements

This paper was supported by Sunchon National University’s Center for Aerospace Engineering Research in 2018.

References

  1. 1.
    Crouch PE (1984) Spacecraft attitude control and stabilization: application of geometric control theory to rigid body models. IEEE Trans Autom Control 29(4):321–331.  https://doi.org/10.1109/TAC.1984.1103519 CrossRefzbMATHGoogle Scholar
  2. 2.
    Petersen C, Leve F, Kolmanovsky I (2016) Underactuated spacecraft switching law for two reaction wheels and constant angular momentum. J Guid Control Dyn 39(9):2086–2099.  https://doi.org/10.2514/1.G001680 CrossRefGoogle Scholar
  3. 3.
    Horri N, Palmer P, Hodgart S (2012) Practical implementation of attitude-control algorithms for an underactuated satellite. J Guid Control Dyn 35(1):40–45.  https://doi.org/10.2514/1.54075 CrossRefGoogle Scholar
  4. 4.
    Krishnan H, McClamroch NH, Reyhanoglu M (1995) Attitude stabilization of a rigid spacecraft using two momentum wheel actuators. J Guid Control Dyn 18(2):256–263.  https://doi.org/10.2514/3.21378 CrossRefzbMATHGoogle Scholar
  5. 5.
    Tsiotras P, Longuski J (1995) A new parameterization of the attitude kinematics. J Astronaut Sci 43(3):243–262MathSciNetGoogle Scholar
  6. 6.
    Tsiotras P, Doumtchenko V (2000) Control of spacecraft subject to actuator failures: state of the art and open problems. J Astronaut Sci 48(2–3):337–358Google Scholar
  7. 7.
    Chaurais J, Ferreira H, Ishihara J, Borges R (2015) Attitude control of an underactuated satellite using two reaction wheels. J Guid Control Dyn 38(10):2010–2017.  https://doi.org/10.2514/1.G000145 CrossRefGoogle Scholar
  8. 8.
    Boyer F, Alamir M (2007) Further results on the controllability of a two-wheeled satellite. J Guid Control Dyn 30(2):611–619.  https://doi.org/10.2514/1.21505 CrossRefGoogle Scholar
  9. 9.
    Kwon S, Shimomura T, Okubo H (2011) Pointing control of spacecraft using two SGCMGs via LPV control theory. Acta Astronaut 68(7–8):1168–1175.  https://doi.org/10.1016/j.actaastro.2010.10.001 CrossRefGoogle Scholar
  10. 10.
    Kasai S, Kojima H, Satoh M (2013) Spacecraft attitude maneuver using two single-gimbal control moment gyros. Acta Astronaut 84:88–98.  https://doi.org/10.1016/j.actaastro.2012.07.035 CrossRefGoogle Scholar
  11. 11.
    Jin J, Hwang I (2011) Attitude control of a spacecraft with single variable-speed control moment gyroscope. J Guid Control Dyn 34(6):1920–1925.  https://doi.org/10.2514/1.53012 CrossRefGoogle Scholar
  12. 12.
    Yoon H, Tsiotras P (2006) Spacecraft line-of-sight control using a single variable speed control moment gyro. J Guid Control Dyn 29(6):1295–1308.  https://doi.org/10.2514/1.18777 CrossRefGoogle Scholar
  13. 13.
    Cloutier J (1997) State-dependent Riccati equation techniques: an overview. In: Proceedings of the 1997 american control conference, Vol 2, Albuquerque, NM, USA, June 4–6, 932–936.  https://doi.org/10.1109/acc.1997.609663
  14. 14.
    Çimen T (2012) Survey of state-dependent Riccati equation in nonlinear optimal feedback control synthesis. J Guid Control Dyn 35(4):1025–1047.  https://doi.org/10.2514/1.55821 CrossRefGoogle Scholar
  15. 15.
    Ozawa R, Takahashi M (2018) Agile attitude control and singularity avoidance/escape by the SDRE method using a biased state-dependent weighting matrix. Appl Sci 8(1):140.  https://doi.org/10.3390/app8010140 CrossRefGoogle Scholar
  16. 16.
    Massari M, Zamaro M (2014) Application of SDRE technique to orbital and attitude control of spacecraft formation flying. Acta Astronaut 94(1):409–420.  https://doi.org/10.1016/j.actaastro.2013.02.001 CrossRefGoogle Scholar
  17. 17.
    Rhee S, Ko H, Jang W, Son J (2009) Roll/yaw momentum management method of pitch momentum biased spacecraft. J Korean Soc Aeronaut Space Scie (in Korean) 37(7):669–677Google Scholar
  18. 18.
    Bang H, Choi H (2002) Attitude control of a bias momentum satellite using moment of inertia. IEEE Trans Aerosp Electron Syst 38(1):243–250.  https://doi.org/10.1109/7.993243 CrossRefGoogle Scholar
  19. 19.
    Williams R, Lawrence D (2007) Linear state-space control systems. Wiley, Hoboken, New Jersey, USA, pp 250–252CrossRefGoogle Scholar
  20. 20.
    Fritzson P (2014) Principles of object-oriented modeling and simulation with modelica 3.3: a cyber-physical approach. 2nd edn. IEEE Press, Piscataway, New Jersey, USA, pp 909–975Google Scholar

Copyright information

© The Korean Society for Aeronautical & Space Sciences and Springer Nature Singapore Pte Ltd. 2018

Authors and Affiliations

  1. 1.Department of Aerospace Engineering/Center for Aerospace Engineering ResearchSunchon National UniversitySuncheonSouth Korea

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