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Integrated aeroservoelastic synthesis for roll controlThe objective of this study is to illustrate an integrated, parallel design procedure for optimal structural, aerodynamic, and aileron synthesis of an aircraft wing. The effects of combining weight minimization with structural tailoring (ply orientation and thickness) of a lifting surface, together with the wing geometry (sweep angle and taper ratio), and the aileron geometry (spanwise location and chordwise size) upon the lateral control effectiveness are discussed. Several optimization studies for the minimization of aileron hinge moment and wing weight, subject to a specified constant aircraft roll rate at a design airspeed (roll effectiveness), are performed.
Document ID
19940004720
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nam, Chang-Ho
(Purdue Univ. West Lafayette, IN, United States)
Weisshaar, Terrence A.
(Purdue Univ. West Lafayette, IN, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1990
Publication Information
Publication: NASA. Langley Research Center, The Third Air Force(NASA Symposium on Recent Advances in Multidisciplinary Analysis and Optimization
Subject Category
Aircraft Design, Testing And Performance
Accession Number
94N71475
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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