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Wind tunnel investigation of active controls technology applied to a DC-10 derivativeApplication of active controls technology to reduce aeroelastic response offers a potential for significant payoffs in terms of aerodynamic efficiency and structural weight. As part of the NASA Energy Efficient Transport program, the impact upon flutter and gust load characteristics has been investigated by means of analysis and low-speed wind tunnel tests of a semispan model. The model represents a DC-10 derivative with increased wing span and an active aileron surface, responding to vertical acceleration at the wing tip. A control law satisfying both flutter and gust load constraints is presented and evaluated. In general, the beneficial effects predicted by analysis are in good agreement with experimental data.
Document ID
19800050892
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Winther, B. A.
(Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Shirley, W. A.
(Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Heimbaugh, R. M.
(Douglas Aircraft Co. Long Beach, Calif., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 80-0771
Meeting Information
Meeting: Structures, Structural Dynamics, and Materials Conference
Location: Seattle, WA
Start Date: May 12, 1980
End Date: May 14, 1980
Accession Number
80A35062
Funding Number(s)
CONTRACT_GRANT: NAS1-15327-02
Distribution Limits
Public
Copyright
Other

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