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Application of a flight test and data analysis technique to flutter of a drone aircraftModal identification results are presented that were obtained from recent flight flutter tests of a drone vehicle with a research wing equipped with an active flutter suppression system (FSS). Frequency and damping of several modes are determined by a time domain modal analysis of the impulse response function obtained by Fourier transformations of data from fast swept sine wave excitation by the FSS control surfaces on the wing. Flutter points are determined for two different altitudes with the FSS off. Data are given for near the flutter boundary with the FSS on.
Document ID
19810045107
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Bennett, R. M.
(NASA Langley Research Center Hampton, VA, United States)
Abel, I.
(NASA Langley Research Center Loads and Aeroelasticity Div., Hampton, Va., United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 81-0652
Meeting Information
Meeting: Conference on Structures, Structural Dynamics and Materials
Location: Atlanta, GA
Start Date: April 6, 1981
End Date: April 8, 1981
Accession Number
81A29511
Distribution Limits
Public
Copyright
Other

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