Aeroelastic Control of Oblique-Wing Aircraft

Burken, John J. and Alag, Gurbux S. and Gilyard, Glenn B. (1986) Aeroelastic Control of Oblique-Wing Aircraft. Technical Report NASA TM-86808, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

The U.S. Navy and NASA are currently involved in the design and development of an unsymmetric-skew-wing aircraft capable of 65 degree wing sweep and flight at Mach 1.6. A generic skew-wing aircraft model was developed for 45 degree wing skew at a flight condition of Mach 0.70 and 3048 m altitude. At this flight condition the aircraft has a wing flutter mode. An active implementable control law was developed using the linear quadratic Gaussian design technique. A method of modal residualization was used to reduce the order of the controller used for flutter suppression.

EPrint Type:	NASA Technical Memorandum
Keywords:	Active flutter suppression, Oblique-wing aircraft, Robust reduced-order controller
Subjects:	(01 - 09) Aeronautics: (08) Aircraft Stability And Control
ID Code:	543
Deposited On:	25 January 2006
Additional Information:	12 pages. Prepared for presentation at the 1986 American Control Conference, Seattle, Washington, June 18-20, 1986. Gurbux S. Alag is affiliated with Western Michigan University, Kalamazoo, Michigan.