A novel smooth quaternion-based attitude tracking control

被引:0
作者
Septanto, Harry [1 ]
Suprijanto, Djoko [2 ]
机构
[1] Badan Riset & Inovasi Nasl, Jakarta, Indonesia
[2] Inst Teknol Bandung, Fac Math & Nat Sci, Jl Ganesha 10, Bandung, Indonesia
关键词
Attitude tracking; Quaternion; Smooth control law; Asymptotically stable in the large; Unwinding phenomenon; Integral Input-to-State Stable; SPACECRAFT; STABILIZATION; ROBUST;
D O I
10.1016/j.asr.2024.09.068
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
The fact that two antipodal points in the quaternion characterize the same physical attitude depicts that the design of the global attitude control system is uneasy. This study deals with a smooth quaternion-based attitude tracking control system that is composed of a differential equation known as the augmented dynamical system. The augmented dynamical system plays such an important role that it is possible to conduct a novel perspective on viewing the set containing all possible motions as not a manifold. Therefore, the topological obstruction does not exist. The designed attitude tracking control system has a guarantee of stability in the large within a set containing all possible motions. It is able to avoid the unwinding phenomenon, and it is noise-induced chattering-free since there is no discontinuity. Furthermore, we show that the smooth attitude tracking control system has an integral input-to-state stability (iISS) guarantee in the presence of uncertainties in the moment of inertia and environmental disturbance. Simulations carried out show the effectiveness of the designed attitude tracking control system. (c) 2024 COSPAR. Published by Elsevier B.V. All rights are reserved, including those for text and data mining, AI training, and similar technologies.
引用
收藏
页码:2307 / 2322
页数:16
相关论文
共 49 条
[1]   A characterization of integral input-to-state stability [J].
Angeli, D ;
Sontag, ED ;
Wang, Y .
IEEE TRANSACTIONS ON AUTOMATIC CONTROL, 2000, 45 (06) :1082-1097
[2]   H∞ inverse optimal attitude tracking on the special orthogonal group SO(3) [J].
Aslam, Farooq ;
Haydar, M. Farooq .
INTERNATIONAL JOURNAL OF CONTROL, 2023, 96 (12) :3155-3167
[3]   Robust attitude tracking on the Special Orthogonal Group SO (3) using PD-type state feedback and linear matrix inequalities [J].
Aslam, Farooq ;
Haydar, M. Farooq .
EUROPEAN JOURNAL OF CONTROL, 2022, 68
[4]  
Bai QS, 2022, INT J DYNAM CONTROL, V10, P1707, DOI 10.1007/s40435-022-00913-9
[5]   Experimental verification and comparison of fuzzy and PID controllers for attitude control of nanosatellites [J].
Bello, A. ;
Olfe, K. S. ;
Rodriguez, J. ;
Ezquerro, J. M. ;
Lapuerta, V. .
ADVANCES IN SPACE RESEARCH, 2023, 71 (09) :3613-3630
[6]   A topological obstruction to continuous global stabilization of rotational motion and the unwinding phenomenon [J].
Bhat, SP ;
Bernstein, DS .
SYSTEMS & CONTROL LETTERS, 2000, 39 (01) :63-70
[7]   Rigid-Body Attitude Control USING ROTATION MATRICES FOR CONTINUOUS, SINGULARITY-FREE CONTROL LAWS [J].
Chaturvedi, Nalin A. ;
Sanyal, Amit K. ;
McClamroch, N. Harris .
IEEE CONTROL SYSTEMS MAGAZINE, 2011, 31 (03) :30-51
[8]   Continuous quaternion based almost global attitude tracking [J].
Conord, Thomas ;
Peaucelle, Dimitri .
5TH IEEE CONFERENCE ON CONTROL TECHNOLOGY AND APPLICATIONS (IEEE CCTA 2021), 2021, :487-492
[9]   Sliding mode control using modified Rodrigues parameters [J].
Crassidis, JL ;
Markley, FL .
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 1996, 19 (06) :1381-1383
[10]   Linearization in satellite attitude control with modified Rodriguez parameters [J].
Doruk, R. Oezguer .
AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY, 2009, 81 (03) :199-203