This article investigates the reduced attitude control problem of a rigid spacecraft subject to elliptical pointing constraints and parameter uncertainties. Specifically, a diffeomorphic projection is proposed to map the constraints from 2-sphere to elliptical 2-sphere while with the pointing direction preserved. Then, the constrained reduced attitude control problem is transformed into a conventional obstacle avoidance problem on the 2-dimensional (2-D) Euclidean space via the elliptical stereographic projection. Benefiting from properties of the diffeomorphism and Kodischek–Rimon navigation functions, a sufficient condition to exclude local minima is obtained. A constrained adaptive reduced attitude controller is further developed and it is shown that almost asymptotical stability of the resulting closed-loop system can be ensured in the sense of a measure zero set. Finally, numerical examples are furnished to illustrate the effectiveness of the proposed controller.
Adaptive Reduced Attitude Control for Rigid Spacecraft With Elliptical Pointing Constraints
IEEE Transactions on Aerospace and Electronic Systems ; 59 , 4 ; 3835-3847
2023-08-01
4460119 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch