Chaudhuri, Anirban and Bhat, Seetharama M (2005) Output Feedback-Based Discrete-Time Sliding-Mode Controller Design for Model Aircraft. In: Journal of Guidance Control and Dynamics, 28 (1). pp. 177-181.
![]() |
PDF
getpdf.pdf Restricted to Registered users only Download (243kB) | Request a copy |
Abstract
Model aircraft provide a low-cost test bed for the design and validation of control algorithms. The control system should improve the transient response and have good disturbance-rejection properties. The stability derivatives of the aircraft vary due to in-flight velocity fluctuations and the controller should be invariant to such perturbations. Weight and power requirements of the aircraft payload restrict the number of onboard sensors and so a limited number of output measurements can be used for feedback.
Item Type: | Journal Article |
---|---|
Publication: | Journal of Guidance Control and Dynamics |
Publisher: | American Institute of Aeronautics and Astronautics |
Additional Information: | The copyright for this article belongs to American Institute of Aeronautics and Astronautics. |
Keywords: | Feedback-Based;Discrete-Time Sliding-Mode;Controller;Design;Model Aircraft |
Department/Centre: | Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering) |
Date Deposited: | 25 Aug 2008 |
Last Modified: | 19 Sep 2010 04:18 |
URI: | http://eprints.iisc.ac.in/id/eprint/2800 |
Actions (login required)
![]() |
View Item |