Journal of Mechanical Science and Technology

  • 제18권2호
  • /
  • Pages.203-210
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  • 2004
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  • 1738-494X(pISSN)
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  • 1976-3824(eISSN)
대한기계학회 (The Korean Society of Mechanical Engineers)
권호 표지

Nonlinear Attitude Control for a Rigid Spacecraft by Feedback Linearization

  • 발행 : 2004.02.01
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초록

Attitude control law design for spacecraft large angle maneuvers is investigated in this paper. The feedback linearization technique is applied to the design of a nonlinear tracking control law. The output function to be tracked is the quaternion attitude parameter. The designed control law turns out to be a combination of attitude and attitude rate tracking commands. The attitude-only output function, therefore, leads to a stable closed-loop system following the given reference trajectory. The principal advantage of the proposed method is that it is relatively easy to produce reference trajectories and associated controller.

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참고문헌

  1. Crassidis, J. L. and Markley, F. L., 1996, 'Sliding Mode Control using Modified Rodrigues Parameters,' Journal of Guidance, Control, and Dynamics, Vol. 19, No. 6, pp. 1381-1383 https://doi.org/10.2514/3.21798
  2. Lin, C. F., 1994, Advanced Control Systems Design, Prentice-Hall
  3. Schumacher, C., 1998, Stability Analysis of a Missile Control System with a Dynamics Inversion Controller, Journal of Guidance, Control, and Dynamics, Vol. 21, No. 3, pp. 508-515 https://doi.org/10.2514/2.4266
  4. Vadali, S. R., 1986, Variable Structure Control of Spacecraft Large Angle Maneuvers,' Journal of Guidance, Control, and Dynamics, Vol. 9, No. 2, pp. 235-239 https://doi.org/10.2514/3.20095
  5. Wie, B. and Barba, P. M., 1985, 'Quaternion Feedback for Spacecraft Large Angle Maneuvers,' Journal of Guidance, Control, and Dynamics, Vol. 8, No. 3, pp. 360-365 https://doi.org/10.2514/3.19988
  6. Wie, B. and Lu, J., 1995, 'Feedback Control Logic for Spacecraft Eigenaxis Rotations under Slew Rate and Control Constraints,' Journal of Guidance, Control, and Dynamics, Vol. 18, No. 6, pp. 1372-1379 https://doi.org/10.2514/3.21555
  7. Wie, B., Weiss, H. and Arapostathis, A., 1989, 'Quaternion Feedback Regulator for Spacecraft Eigenaxis Rotations,' Journal of Guidance, Control, and Dynamics, Vol. 12, No. 3, pp. 375-380 https://doi.org/10.2514/3.20418