dc.Location	2013 TA 169 T38
dc.Supervisor	Professor Robert Whalley
dc.contributor.author	Tavalla, Sahar Sadat
dc.date.accessioned	2013-11-14T10:57:02Z
dc.date.available	2013-11-14T10:57:02Z
dc.date.issued	2013-06
dc.description.abstract	This research includes the design of a multivariable control system for aircraft wings. Two objectives are desired. The first is to control the vibrational problem for low-speed flight by applying a feedback control strategy. The second goal is to demonstrate that the controller for this wing assembly dissipates the least energy by comparing an alternative controller design technique. Simple procedures using established methods relating the wing vibrational problems, are outlined. The control strategies invoked using a simplified flutter dynamic model. A compensator designed to provide enhanced flutter suppression was employed. The transient performance of the system was computed for various flight velocities. Comparison of the energy dissipation for the gain ratios investigated was obtained. Numerical simulation was used to demonstrate the effectiveness of the approach advocated.	en_US
dc.identifier.other	90082
dc.identifier.uri	http://bspace.buid.ac.ae/handle/1234/392
dc.language.iso	en	en_US
dc.publisher	The British University in Dubai (BUiD)	en_US
dc.subject	multivariable control system	en_US
dc.subject	aircraft wings	en_US
dc.subject	feedback control strategy	en_US
dc.subject	low-speed flight	en_US
dc.subject	alternative controller design technique	en_US
dc.subject	dynamic model	en_US
dc.subject	energy dissipation	en_US
dc.subject	numerical simulation	en_US
dc.title	Aircraft wing flutter control	en_US
dc.type	Dissertation	en_US

Aircraft wing flutter control

Files

Original bundle

License bundle

Collections