Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
5472880 | Aerospace Science and Technology | 2017 | 15 Pages |
Abstract
This paper investigates the problem of finite-time output feedback control for spacecraft attitude stabilization with attitude-only measurement. First, a finite-time filter is proposed to generate the pseudo-angular-velocity signal, which is fed to the controller, and then a continuous finite-time attitude controller is designed based on the proposed filter. The overall finite-time stability of entire filter-controller closed-loop system is given through the adding a power integrator technique. The rigorous proof shows that the attitude will converge to its equilibrium states in the absence of disturbance. When considering disturbance, states will be eventually stabilized to a residual set of equilibrium in a finite time. Numerical simulation results illustrate the proposed method can provide the fast transient response, energy-efficient and robust attitude control performance.
Related Topics
Physical Sciences and Engineering
Engineering
Aerospace Engineering
Authors
Boyan Jiang, Chuanjiang Li, Guangfu Ma,