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Transonic Flutter Suppression Control Law Design, Analysis and Wind-Tunnel ResultsThe benchmark active controls technology and wind tunnel test program at NASA Langley Research Center was started with the objective to investigate the nonlinear, unsteady aerodynamics and active flutter suppression of wings in transonic flow. The paper will present the flutter suppression control law design process, numerical nonlinear simulation and wind tunnel test results for the NACA 0012 benchmark active control wing model. The flutter suppression control law design processes using classical, and minimax techniques are described. A unified general formulation and solution for the minimax approach, based on the steady state differential game theory is presented. Design considerations for improving the control law robustness and digital implementation are outlined. It was shown that simple control laws when properly designed based on physical principles, can suppress flutter with limited control power even in the presence of transonic shocks and flow separation. In wind tunnel tests in air and heavy gas medium, the closed-loop flutter dynamic pressure was increased to the tunnel upper limit of 200 psf. The control law robustness and performance predictions were verified in highly nonlinear flow conditions, gain and phase perturbations, and spoiler deployment. A non-design plunge instability condition was also successfully suppressed.
Document ID
20040086731
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Mukhopadhyay, Vivek (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 1999
Subject Category
Aerodynamics
Meeting Information
Meeting: International Forum on Aeroelasticity and Structural Dynamics 1999
Location: Williamsburg, VA
Country: United States
Start Date: June 22, 1999
End Date: June 25, 1999
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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