Spacecraft attitude control using non-singular finite time convergence fast terminal sliding mode
by Pyare Mohan Tiwari; S. Janardhanan; Masuq-un-Nabi
International Journal of Instrumentation Technology (IJIT), Vol. 1, No. 2, 2012

Abstract: In this work, a finite time convergent, non-singular continuous time sliding mode controller is proposed to control the attitude of rigid spacecraft. The proposed controller is derived using non-singular fast terminal sliding mode (NFTSM) with power rate reaching law. The fast convergence with finite time stability is ensured both in reaching phase as well in sliding phase, and is proved using Lyapunov-type theorem. The effectiveness of proposed controller is verified by numerous simulation results. The results show that attitude control system is made globally stable and robust enough to negate model uncertainties, bounded disturbances, and actuator saturation problems with a control input of continuous nature.

Online publication date: Wed, 17-Sep-2014

The full text of this article is only available to individual subscribers or to users at subscribing institutions.

 
Existing subscribers:
Go to Inderscience Online Journals to access the Full Text of this article.

Pay per view:
If you are not a subscriber and you just want to read the full contents of this article, buy online access here.

Complimentary Subscribers, Editors or Members of the Editorial Board of the International Journal of Instrumentation Technology (IJIT):
Login with your Inderscience username and password:

    Username:        Password:         

Forgotten your password?


Want to subscribe?
A subscription gives you complete access to all articles in the current issue, as well as to all articles in the previous three years (where applicable). See our Orders page to subscribe.

If you still need assistance, please email subs@inderscience.com