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Modeling and Optimization for Morphing Wing Concept Generation IIThis report documents a series of investigations to develop an approach for structural sizing of various morphing wing concepts. For the purposes of this report, a morphing wing is one whose planform can make significant shape changes in flight - increasing wing area by 50% or more from the lowest possible area, changing sweep 30 or more, and / or increasing aspect ratio by as much as 200% from the lowest possible value. These significant changes in geometry mean that the underlying load-bearing structure changes geometry. While most finite element analysis packages provide some sort of structural optimization capability, these codes are not amenable to making significant changes in the stiffness matrix to reflect the large morphing wing planform changes. The investigations presented here use a finite element code capable of aeroelastic analysis in three different optimization approaches -a "simultaneous analysis" approach, a "sequential" approach, and an "aggregate" approach.
Document ID
20080009777
Document Type
Contractor Report (CR)
Authors
Skillen, Michael D. (Purdue Univ. West Lafayette, IN, United States)
Crossley, William A. (Purdue Univ. West Lafayette, IN, United States)
Date Acquired
August 24, 2013
Publication Date
February 1, 2008
Subject Category
Aircraft Design, Testing and Performance
Report/Patent Number
NASA/CR-2008-214902/PT1
Funding Number(s)
CONTRACT_GRANT: NNL06AA04G
WBS: WBS 659877.02.07.05.9S51.02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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