Model independent eigenaxis maneuvers using quaternion feedback
- 1 January 2001
- conference paper
- Published by Institute of Electrical and Electronics Engineers (IEEE)
- Vol. 3, 2339-2344 vol.3
- https://doi.org/10.1109/acc.2001.946101
Abstract
The main contribution of the paper is the derivation of a model independent feedback control law that causes a rigid body to execute a near eigenaxis maneuver. The degree of approximation is a function of the control gains and the initial attitude error. Using passivity techniques, the dependence of the control strategy on velocity information is eliminated. The technique used to derive the control strategy is a novel orthogonal decomposition of the unit quaternion into a component along the direction of the eigenaxis and a component that is orthogonal to that direction.Keywords
This publication has 7 references indexed in Scilit:
- Further passivity results for the attitude control problemIEEE Transactions on Automatic Control, 1998
- Attitude control without angular velocity measurement: a passivity approachIEEE Transactions on Automatic Control, 1996
- Near-minimum-time eigenaxis rotation maneuvers using reaction wheelsJournal of Guidance, Control, and Dynamics, 1995
- Adaptive quaternion feedback regulation for eigenaxis rotationsJournal of Guidance, Control, and Dynamics, 1994
- Quaternion-based rate/attitude tracking system with application to gimbal attitude controlJournal of Guidance, Control, and Dynamics, 1993
- Time-optimal three-axis reorientation of a rigid spacecraftJournal of Guidance, Control, and Dynamics, 1993
- Quarternion feedback regulator for spacecraft eigenaxis rotationsJournal of Guidance, Control, and Dynamics, 1989