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Aeroelastic Tailoring of the NASA Common Research Model via Novel Material and Structural ConfigurationsThis work explores the use of tow steered composite laminates, functionally graded metals (FGM), thickness distributions, and curvilinear rib/spar/stringer topologies for aeroelastic tailoring. Parameterized models of the Common Research Model (CRM) wing box have been developed for passive aeroelastic tailoring trade studies. Metrics of interest include the wing weight, the onset of dynamic flutter, and the static aeroelastic stresses. Compared to a baseline structure, the lowest aggregate static wing stresses could be obtained with tow steered skins (47% improvement), and many of these designs could reduce weight as well (up to 14%). For these structures, the trade-off between flutter speed and weight is generally strong, although one case showed both a 100% flutter improvement and a 3.5% weight reduction. Material grading showed no benefit in the skins, but moderate flutter speed improvements (with no weight or stress increase) could be obtained by grading the spars (4.8%) or ribs (3.2%), where the best flutter results were obtained by grading both thickness and material. For the topology work, large weight reductions were obtained by removing an inner spar, and performance was maintained by shifting stringers forward and/or using curvilinear ribs: 5.6% weight reduction, a 13.9% improvement in flutter speed, but a 3.0% increase in stress levels. Flutter resistance was also maintained using straightrotated ribs although the design had a 4.2% lower flutter speed than the curved ribs of similar weight and stress levels were higher. These results will guide the development of a future design optimization scheme established to exploit and combine the individual attributes of these technologies.
Document ID
20140007306
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Jutte, Christine V. (Craig Technologies Cape Canaveral, FL, United States)
Stanford, Bret K. (NASA Langley Research Center Hampton, VA, United States)
Wieseman, Carol D. (NASA Langley Research Center Hampton, VA, United States)
Moore, James B. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
June 11, 2014
Publication Date
January 13, 2014
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA Paper-2014-0344
NF1676L-16610
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
Location: National Harbor, MD
Country: United States
Start Date: January 13, 2014
End Date: January 17, 2014
Sponsors: American Society for Composites, American Inst. of Aeronautics and Astronautics, American Helicopter Society, Inc., American Society of Civil Engineers, American Society of Mechanical Engineers
Funding Number(s)
WBS: WBS 432938.11.01.07.43.40.08
Distribution Limits
Public
Copyright
Public Use Permitted.

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