Skip to main content
SpringerLink
Log in

Failure-tolerant control for small agile satellites using single-gimbal control moment gyros and magnetic torquers

  • Research Paper
  • Published:
Acta Mechanica Sinica Aims and scope Submit manuscript

Abstract

This paper focuses on the attitude control problem of small agile satellites using single-gimbal control moment gyros (CMG) and magnetic torquers (MTQ). CMGs are regarded as effective torque generators for agile satellites because of their torque amplification capability. However, they are vulnerable to failure due to their complex inner mechanism. In this paper, different failure cases of CMGs are analyzed. A flexible failure-tolerant control strategy is developed by automatically redistributing the required control torque among the operating CMGs and MTQs, with a variable limiter to accommodate the actuator dynamics changes introduced by CMG failures. The performances of maneuvers about different directions under different failure cases are also discussed and examined. Numerical simulations demonstrate that the proposed strategy maintains certain agility in the cases of one or two CMGs failing. Moreover, a survival strategy with only one CMG left is also verified. Both sun-pointing stabilization and earth-pointing stabilization can be achieved in this case, which fulfill some basic mission requirements.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Similar content being viewed by others

References

  1. Lappas, V. J., Steyn, W. H., Under wood, C. I.: Attitude control for small satellite using control moment gyros. Acta Astronautica, 51(1–9), 101–111 (2002) DOI: 10.1016/S0094-5765(02)00089-9

    Article  Google Scholar 

  2. Roser, X., Sghedoni, M.: Control moment gyroscopes (CMG’s) and their application in future scientific missions. Proc. 3rd International Conf. on Spacecraft Guidance, Navigation, and Control system, 26–29 Nov., The Netherlands, 523–528 (1996)

  3. Salenc, C., Roser, X.: AOCS for agile scientific spacecraft with Mini-CMG’s. Proc. 4th ESA International Conf. on Spacecraft Guidance, Navigation, and Control system, 18–21 Nov., The Netherlands, 379–384 (1999)

  4. Fujihashi, K., Omagari, K., Matunaga, S.: Science and technology demonstration satellite “TSUBAME” and its attitude control system using micro CMGs. 26th International Symposium on Space Technology and Science, Hamamatsu, Japan, 1–8 June, 2008-d-48 (2008)

  5. Omagari, K., Usuda, T., Matunage, S.: Research of control moment gyros for micro-satellites and 3-DOF attitude dynamics simulator experiments. In: Proceeding of the 8th International Symposium on Artificial Intelligence, Robotics and Automation in Space, Munich, Germany, 5–8 Sep., ESA-SP603 (2005)

  6. Margulies, G., Aubrun, J. N.: Geometric theory of singlegimbal control moment gyro systems. Journal of the Astronautical Sciences, 26(2), 159–191 (1978)

    Google Scholar 

  7. Jin, L., Xu, S. J.: An improved constrained steering law for SGCMGs with DPC. Acta Mechanica Sinica, 25(5), 713–720 (2009) DOI: do]10.1007/s10409-009-0269-z

    Article  MathSciNet  Google Scholar 

  8. Lam, Q. M., Barkana, I.: Direct adaptive control treatment to loss of attitude control actuator. AIAA Guidance, Navigation and Control Conference and Exhibit, 20–23Aug., Hiton Head, South Caralina, AIAA 2007-6435 (2007)

  9. Cai, W. C., Liao, X. H., Song, Y. D.: Indirect robust adaptive fault-tolerant control for attitude tracking of spacecraft. Journal of Guidance, Control, and Dynamics, 31(5), 1456–1463 (2008) DOI: 10.2514/1.31158

    Article  Google Scholar 

  10. Zhang, J. R., Rachid, A., Zhang, Y.: Attitude control for part actuator failure of agile small satellite. Acta Mechanica Sinica, 24(4), 463–468 (2008)

    Article  Google Scholar 

  11. Lappas, V., Steyn, W., Underwood, C.: Control moment gyro gimbal angle compensation using magnetic control during external disturbances. AIAA Guidance, Navigation and Control Conference and Exhibit, 6–9 Aug., Montreal, Canada, AIAA 2001-4339 (2001)

  12. Wie, B.: Space Vehicle Dynamics and Control, (2nd. edn.), AIAA Education Series, AIAA, Chp.7&11 (2008)

  13. Wie, B., Bailey, D., Heiberg, D.: Rapid multitarget acquisition and pointing control of agile spacecraft. Journal of Guidance, Control, and Dynamics, 25(1), 96–104 (2002) DOI: 10.2514/2.4854

    Article  Google Scholar 

  14. Kurakawa, H.: A geometric study of single gimbal control moment gyros-singularity problems and steering law. Report of Mechanical Engineering Laboratory, 175 (1998)

  15. Lovera, M.: Global magnetic attitude control of inertially pointing spacecraft. Journal of Guidance, Control and Dynamics, 28(5), 1065–1072 (2005) DOI: 10.2514/1.11844

    Article  Google Scholar 

  16. Silani, E., Lovera, M.: Magnetic spacecraft attitude control: a survey and some new results. Control Engineering Practice, 13(3), 357–371 (2005) DOI:10.1016/j.conengprac.2003.12.017

    Article  Google Scholar 

Download references

Author information

Authors and Affiliations

  1. School of aeronautics and astronautics, Zhejiang University, 310027, Hangzhou, China

    Tao Meng

  2. Dept. of Mechanical and Aerospace Engineering, Tokyo Institute of Technology, Tokyo, Japan

    Saburo Matunaga

Authors
  1. Tao Meng
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Saburo Matunaga
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Tao Meng.

Rights and permissions

Reprints and permissions

About this article

Cite this article

Meng, T., Matunaga, S. Failure-tolerant control for small agile satellites using single-gimbal control moment gyros and magnetic torquers. Acta Mech Sin 28, 551–558 (2012). https://doi.org/10.1007/s10409-012-0044-4

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s10409-012-0044-4

Keywords

Search

Navigation