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Active controls for flutter suppression and gust alleviation in supersonic aircraftApplication is made in the present paper of the recently developed relaxed aerodynamic energy concept and synthesis techniques to the definition of appropriate active control systems for the low-speed flutter model of the B-2707-300 supersonic cruise airplane. The effectiveness of the resulting activated systems is analytically tested for flutter suppression, wing root bending moment alleviation, and ride control (fuselage accelerations). The results obtained indicate that considerable increase in flutter speeds can be obtained by the various control systems, using a single trailing-edge control. In all cases, the flutter suppression control system led to a substantial reduction in both wing root bending moments and in fuselage and wing accelerations.
Document ID
19800056576
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Nissim, E.
(Technion - Israel Inst. of Tech. Haifa, Israel)
Lottati, I.
(Technion - Israel Institute of Technology Haifa, Israel)
Date Acquired
August 10, 2013
Publication Date
August 1, 1980
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 79-0792
Accession Number
80A40746
Funding Number(s)
CONTRACT_GRANT: NSG-7373
Distribution Limits
Public
Copyright
Other

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