Active controls for flutter suppression and gust alleviation in supersonic aircraft

E. Nissim, I. Lottati

Research output: Contribution to journalArticlepeer-review


Application 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.

Original languageEnglish
Pages (from-to)345-351
Number of pages7
JournalJournal of Guidance, Control, and Dynamics
Issue number4
StatePublished - Jul 1980
Externally publishedYes

Bibliographical note

Funding Information:
The work reported herein is a part of a study supported by NASA through its Aeroelasticity Branch at the Langley Research Center (under Grant NSG 7373). The numerical data for the 2707-300 airplane was supplied by the Boeing Company.


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