NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Digital-flutter-suppression-system investigations for the active flexible wing wind-tunnel modelActive flutter suppression control laws were designed, implemented, and tested on an aeroelastically-scaled wind tunnel model in the NASA Langley Transonic Dynamics Tunnel. One of the control laws was successful in stabilizing the model while the dynamic pressure was increased to 24 percent greater than the measured open-loop flutter boundary. Other accomplishments included the design, implementation, and successful operation of a one-of-a-kind digital controller, the design and use of two simulation methods to support the project, and the development and successful use of a methodology for on-line controller performance evaluation.
Document ID
19900010777
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Perry, Boyd, III (NASA Langley Research Center Hampton, VA, United States)
Mukhopadhyay, Vivek (NASA Langley Research Center Hampton, VA, United States)
Hoadley, Sherwood T. (NASA Langley Research Center Hampton, VA, United States)
Cole, Stanley R. (NASA Langley Research Center Hampton, VA, United States)
Buttrill, Carey S. (NASA Langley Research Center Hampton, VA, United States)
Houck, Jacob A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1990
Subject Category
Aircraft Stability And Control
Report/Patent Number
NAS 1.15:102618
NASA-TM-102618
Meeting Information
Meeting: AIAA 31st Structures, Structural Dynamics, and Materials Conference
Location: Long Beach, CA
Country: United States
Start Date: April 2, 1990
End Date: April 4, 1990
Accession Number
90N20093
Funding Number(s)
PROJECT: RTOP 505-63-21-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available