Journal
IEEE TRANSACTIONS ON AUTOMATIC CONTROL
Volume 56, Issue 11, Pages 2555-2566Publisher
IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC
DOI: 10.1109/TAC.2011.2108490
Keywords
Attitude control; hybrid control; output feedback; robustness; spacecraft
Funding
- National Science Foundation [ECCS-0925637, CNS-0720842]
- Air Force Office of Scientific Research [FA9550-09-1-0203]
- Div Of Electrical, Commun & Cyber Sys
- Directorate For Engineering [0925637] Funding Source: National Science Foundation
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It is well known that controlling the attitude of a rigid body is subject to topological constraints. We illustrate, with examples, the problems that arise when using continuous and (memoryless) discontinuous quaternion-based state-feedback control laws for global attitude stabilization. We propose a quaternion-based hybrid feedback scheme that solves the global attitude tracking problem in three scenarios: full state measurements, only measurements of attitude, and measurements of attitude with angular velocity measurements corrupted by a constant bias. In each case, the hybrid feedback is dynamic and incorporates hysteresis-based switching using a single binary logic variable for each quaternion error state. When only attitude measurements are available or the angular rate is corrupted by a constant bias, the proposed controller is observer-based and incorporates an additional quaternion filter and bias observer. The hysteresis mechanism enables the proposed scheme to simultaneously avoid the unwinding phenomenon and sensitivity to arbitrarily small measurement noise that is present in discontinuous feedbacks. These properties are shown using a general framework for hybrid systems, and the results are demonstrated by simulation.
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