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Practical gust load alleviation and flutter suppression control laws based on a LQG methodologyA modified linear quadratic Gaussian (LQG) synthesis procedure has been used to design low-order robust multiloop controllers for a flexible airplane. The introduction of properly constructed fictitious Gauss-Markov processes in the control loops allowed meeting classical frequency-domain stability criteria using the direct synthesis procedures of modern time-domain control theory. Model reduction was used to simplify the control laws to the point where they could be easily implemented on onboard flight computers. These control laws provided excellent gust load and flutter mode control with good stability margins and compared very favorably to other control laws synthesized by the classical root-locus technique.
Document ID
19810036140
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gangsaas, D.
(Boeing Commercial Airplane Co. Seattle, WA, United States)
Ly, U.
(Boeing Commercial Airplane Co. Seattle, WA, United States)
Norman, D. C.
(Boeing Commercial Airplane Co. Seattle, Wash., United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 81-0021
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: St. Louis, MO
Start Date: January 12, 1981
End Date: January 15, 1981
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
81A20544
Funding Number(s)
CONTRACT_GRANT: NAS1-15325
Distribution Limits
Public
Copyright
Other

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