This paper addresses the problem of designing an angular velocity observer and an output feedback attitude controller with finite-time convergence and disturbances for spacecraft. First, two new concepts of finite-time stability are proposed and defined as the local fast-finite-time stability and the fast-finite-time uniformly ultimately boundness, which can be seen as the extensions of the traditional fast-finite-time stability. Then, based on these two concepts of stability, a fast-finite-time observer is designed to estimate the unknown angular velocity. Next, based on the estimation of the angular velocity, a nonsingular and continuous attitude control algorithm is proposed to achieve the finite-time stability or finite-time boundness. With consideration of the observation errors and disturbances in the closed-loop system, a rigorous analysis of the proposed strategy is provided through Lyapunov approach. It shows that the observation errors and the spacecraft attitude will converge to a region of zero in finite time. Numerical simulation studies are presented to illustrate the effectiveness of the proposed observer-based attitude control scheme.
Continuous Finite-Time Attitude Control for Rigid Spacecraft Based on Angular Velocity Observer
IEEE Transactions on Aerospace and Electronic Systems ; 54 , 3 ; 1082-1092
2018-06-01
617297 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Disturbance observer based finite-time attitude control for rigid spacecraft under input saturation
Online Contents | 2014
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