Aeroelastic control of oblique-wing aircraft

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Aeroelastic control of oblique-wing aircraft

Aeroelastic control of oblique-wing aircraft

Burken, J. J. / Gilyard, G. B. / Alag, G. S.

The U.S. Navy and NASA are currently involved in the design and development of an unsymmetric-skew-wing aircraft capable of 65 deg wing sweep and flight at Mach 1.6. A generic skew-wing aircraft model was developed for 45 deg 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.

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Title :

Aeroelastic control of oblique-wing aircraft

Contributors:

Burken, J. J. (author) / Gilyard, G. B. (author) / Alag, G. S. (author)

Publication date :

1986-01-01

Type of media :

Conference paper

Type of material :

No indication

Language :

English

Keywords :

Aircraft Stability And Control

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