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논문 기본 정보
- 자료유형
- 학술저널
- 저자정보
- 발행연도
- 2004.2
- 수록면
- 203 - 210 (8page)
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초록· 키워드
오류제보하기
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.
목차
Abstract
1.Intronduction
2.Basic Dynamics and Control Theory
3.Tracking Controller Using Quaternion Output Only
4.Simulation and Analysis
5.Conclusions
Acknowledgment
References
참고문헌 (6)
참고문헌 신청
[학술지(정기간행물)] - / 1985 / Quaternion Feedback for Spacecraft Large Angle Maneuvers Journal of Guidance 8 : 360 ~ 365
[학술지(정기간행물)] - / 1989 / Quaternion Feedback Regulator for Spacecraft Eigenaxis Rotations Journal of Guidance 12 : 375 ~ 380
[학술지(정기간행물)] - / 1995 / Feedback Control Logic for Spacecraft Eigenaxis Rotations under Slew Rate and Control Constraints 18 (6) : 1372 ~ 1379
[학술지(정기간행물)] - / 1996 / Sliding Mode Control using Modified Rodrigues Parameters 19 (6) : 1381 ~ 1383
[학술지(정기간행물)] - / 1998 / Stability Analysis of a Missile Control System with a Dynamics Inversion Controller 21 (3) : 508 ~ 515
[학술지(정기간행물)] - / 1989 / Quaternion Feedback Regulator for Spacecraft Eigenaxis Rotations Journal of Guidance 12 : 375 ~ 380
[학술지(정기간행물)] - / 1995 / Feedback Control Logic for Spacecraft Eigenaxis Rotations under Slew Rate and Control Constraints 18 (6) : 1372 ~ 1379
[학술지(정기간행물)] - / 1996 / Sliding Mode Control using Modified Rodrigues Parameters 19 (6) : 1381 ~ 1383
[학술지(정기간행물)] - / 1998 / Stability Analysis of a Missile Control System with a Dynamics Inversion Controller 21 (3) : 508 ~ 515
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