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Model-following control for an oblique-wing aircraftA variable-skew oblique wing offers a substantial aerodynamic performance advantage for aircraft missions that require both high efficiency in subsonic flight and supersonic dash or cruise. The most obvious characteristic of the oblique-wing concept is the asymmetry associated with wing-skew angle which results in significant aerodynamic and inertial cross-coupling between the aircraft longitudinal and lateral-directional axes. This paper presents a technique for synthesizing a decoupling controller while providing the desired stability augmentation. The proposed synthesis procedure uses the concept of explicit model following. Linear quadratic optimization techniques are used to design the linear feedback system. The effectiveness of the control laws developed in achieving the desired decoupling is illustrated for a given flight condition by application to linearized equations of motion, and also to the nonlinear equations of six degrees of freedom of motion with nonlinear aerodynamic data.
Document ID
19860062754
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Alag, G. S.
(Western Michigan University Kalamazoo, MI, United States)
Kempel, R. W.
(University of Western Michigan Kalamazoo, MI, United States)
Pahle, J. W.
(University of Western Michigan Kalamazoo, MI, United States)
Bresina, J. J.
(University of Western Michigan Kalamazoo, MI, United States)
Bartoli, F.
(NASA Flight Research Center Edwards, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1986
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 86-2244
Accession Number
86A47492
Distribution Limits
Public
Copyright
Other

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