International Journal of Aeronautical and Space Sciences

  • 제4권1호
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  • Pages.99-109
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  • 2003
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  • 2093-274X(pISSN)
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  • 2093-2480(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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Three-axis Attitude Control for Flexible Spacecraft by Lyapunov Approach under Gravity Potential

  • Bang, Hyo-Choong (Division of Aerospace Engineering Korea Advanced Institute of Science and Technology) ;
  • Lee, Kwang-Hyun (Division of Aerospace Engineering Korea Advanced Institute of Science and Technology) ;
  • Lim, Hyung-Chul (Division of Aerospace Engineering Korea Advanced Institute of Science and Technology)
  • 발행 : 2003.05.30
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초록

Attitude control law synthesis for the three-axis attitude maneuver of a flexible spacecraft model is presented in this study. The basic idea is motivated by previous works for the extension into a more general case. The new case includes gravitational gradient torque which has significant effect on a wide range of low earth orbit missions. As the first step, the fully nonlinear dynamic equations of motion are derived including gravitational gradient. The control law design based upon the Lyapunov approach is attempted. The Lyapunov function consists of a weighted combination of system kinetic and potential energy. Then, a set of stabilizing control law is derived from the basic Lyapunov stability theory. The new control law is therefore in a general form partially validating the previous work in some sense.

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참고문헌

  1. Wie, B., and Barba, P.M., "Quatemion Feedback for Spacecraft Large Angle Attitude Maneuver", Journal of Guidance, Control, and Dynamics, Vol. 8, 1989, pp. 360-365. https://doi.org/10.2514/3.19988
  2. Allen, M., Bernlli-Zazzera, F., and Scattolini, R. "Sliding Mode Control of a Large Flexible Structure", Control Engineering Practice, Vol. 8, 2000, pp. 861-871 https://doi.org/10.1016/S0967-0661(00)00004-6
  3. Liu, Q., and Wie, B., "Robust Time- Optimal Control of Uncertain Flexible Spacecraft", Journal of Guidance, Control, and Dynamics, Vol. 15, No.3, 1992, pp. 597-604. https://doi.org/10.2514/3.20880
  4. Singh, T., and Vadali, S.R., "Input-Shaped Control of Three- Dimensional Maneuvers of Flexible Spacecraft", Journal of Guidance, Control, and Dynamics, Vol. 6, No. 6, 1993, pp. 1061-1068.
  5. Fujii, H., and Ishijima, S., "Mission Function Control for Slew Maneuver of a Flexible Structure", Journal of Guidance, Control and Dynamics, Vol. 12, 1989, pp. 858-865. https://doi.org/10.2514/3.20492
  6. Junkins, J.L., Rahman, Z., and Bang, H., "Near-Minimum-Time Control of Distributed Parameter Systems: Analytical and Experimental Results", Journal of Guidance, Control, and Dynamics, Vol. 14, 1991, pp. 406-415 https://doi.org/10.2514/3.20653
  7. Suk, J., Moon, J., and Kim, Y., "Torque Shaping using Trigonometric Series Expansion for Slewing of Flexible Structures", Journal of Guidance, Control, and Dynamics, Vol. 21, No. 5, 1998.
  8. Junkins, J.L. and Bang, H.C., "Maneuver and Vibration Control of Hybrid Coordinate Systems using Lyapunov Stability Theory", Journal of Guidance, Control and Dynamics, Vol. 16, 1993, pp. 668-676. https://doi.org/10.2514/3.21066
  9. Sidi, M.J., Spacecraft Dynamics and Control, Cambridge University Press, 1997
  10. Wie, B., Space Vehicle Dynamics and Control, AIAA Education Series, AIAA, 1998.
  11. Kwon, Y.W., and Bang, H., The Finite Element Method using MATLAB, CRC Press, {Second Ed., 2000, pp. 497-508.