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The output torque estimation of MCMG for agile satellites

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Abstract

Studied in this paper are the attitude control law design and the output torque estimation problem of micro control moment gyros (MCMGs) for the agile satellites executing rapid attitude maneuver mission. An algorithm is proposed for estimating the output torques and the gimbal angular rates of MCMGs, which can help engineers to choose reasonable size for actuators so that the cost of satellite can be decreased. According to some special maneuver missions, a numerical example of attitude control system for a small satellite with MCMGs in pyramid configuration is studied, and the simulation results validate the proposed estimation algorithm.

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References

  1. Wie, B., Bailey, D., Heiberg, C.: Rapid multi-target acquisition and pointing control of agile satellite. AIAA-2000-4546 (2000)

  2. Zhang J.R., Rachid A., Zhang Y.: Attitude control for part actuator failure of agile small satellite. Acta Mech. Sinica 24(3), 463–468 (2008)

    Article  Google Scholar 

  3. Baudoin, A., et al.: Pléiades: a multi mission and multi cooperative program. In: 52nd International Astronautical Congress, 1–5 October 2001, Toulouse, France, IAF (2001)

  4. Lappas, V.J., Steyn, W.H., Underwood, C.I.: Practical results on the development of a control moment gyro based attitude control system for agile small satellites. In: The Sixteenth Annual AIAA/USU Conference on Small Setellites, 12–15 August 2002, Logan, UT, AIAA (2002)

  5. Lappas, V.J.: Design, analysis and in-orbit performance of the BILSAT-1 microsatellite twin CMG experimental cluster. AIAA-2004-5246, AIAA Guidance, Navigation, and Control Conference and Exhibit, 16–19 August 2004, Providence, RI, AIAA (2004)

  6. Zhang J.R., Xu S.J., Li J.F.: A new design approach of PD controller for attitude control of spacecraft. J. Aerosp. Sci. Technol. 9(4), 329–336 (2005)

    Article  MathSciNet  Google Scholar 

  7. Lappas, V.J., Steyn, W.H., Underwood, C.I.: Attitude control for small satellites using control moment gyro. In: 5th Cranfield DCSSS Conference, 14–18 July 2002, King’s College Cambridge, AIAA (2002)

  8. Wie B.: Space Vehicle Dynamics and Control. AIAA Education Series, Washington (1998)

    MATH  Google Scholar 

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Authors and Affiliations

  1. School of spacecraft engineering, Beijing Institute of Technology, 100081, Beijing, China

    Jingrui Zhang

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  1. Jingrui Zhang
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Correspondence to Jingrui Zhang.

Additional information

The project was supported by the National Natural Science Foundation of China (10872029), Excellent Scholars Fund of Beijing (20071D1600300398) and Excellent Young Scholars Research Fund of Beijing Institute of Technology (2007YS0202).

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Zhang, J. The output torque estimation of MCMG for agile satellites. Acta Mech Sin 26, 141–146 (2010). https://doi.org/10.1007/s10409-009-0314-y

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  • DOI: https://doi.org/10.1007/s10409-009-0314-y

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