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Modal control of relaxed static stability aircraftA method is developed that assigns a selected portion of a closed loop system eigenstructure in accordance with certain desirable criteria. The method is applied here to a relaxed static stability aircraft, the goal being to synthesize a control law that provides the unstable aircraft with handling qualities equal to or better than those of a comparable statically stable aircraft. It is shown that by using the target system eigenstructure, good flight characteristics are achieved by the unstable aircraft. It is also shown that improved characteristics can be obtained by assigning an orthogonal eigenvector structure.
Document ID
19820055409
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Rooney, R. H.
(Lockheed-California Co. Burbank, CA, United States)
Chung, J. C.
(Lockheed-California Co. Burbank, CA, United States)
Shapiro, E. Y.
(Lockheed-California Co. Burbank, CA, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 82-1524
Meeting Information
Meeting: Guidance and Control Conference
Location: San Diego, CA
Start Date: August 9, 1982
End Date: August 11, 1982
Accession Number
82A38944
Funding Number(s)
CONTRACT_GRANT: NAS1-15326
Distribution Limits
Public
Copyright
Other

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