کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
5472880 | 1520068 | 2017 | 15 صفحه PDF | دانلود رایگان |
عنوان انگلیسی مقاله ISI
Finite-time output feedback attitude control for spacecraft using “Adding a power integrator” technique
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کلمات کلیدی
موضوعات مرتبط
مهندسی و علوم پایه
سایر رشته های مهندسی
مهندسی هوافضا
پیش نمایش صفحه اول مقاله
چکیده انگلیسی
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.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Aerospace Science and Technology - Volume 66, July 2017, Pages 342-354
Journal: Aerospace Science and Technology - Volume 66, July 2017, Pages 342-354
نویسندگان
Boyan Jiang, Chuanjiang Li, Guangfu Ma,