Aeroelastic control of oblique-wing aircraftThe 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.
Document ID
19870026067
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Burken, J. J. (NASA Flight Research Center Edwards, CA, United States)
Gilyard, G. B. (NASA Flight Research Center Edwards, CA, United States)
Alag, G. S. (Western Michigan University Kalamazoo, MI, United States)