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Integrated aerodynamic-structural design of a transport wingThe integrated aerodynamic-structural design of a subsonic transport wing for minimum weight subject to required range is formulated and solved. The problem requires large computational resources, and two methods are used to alleviate the computational burden. First, a modular sensitivity method that permits the usage of black-box disciplinary software packages, is used to reduce the cost of sensitivity derivatives. In particular, it is shown that derivatives of the aeroelastic response and divergence speed can be calculated without the costly computation of derivatives of aerodynamic influence coefficient and structural stiffness matrices. A sequential approximate optimization is used to further reduce computational cost. The optimization procedure is shown to require a relatively small number of analysis and sensitivity calculations.
Document ID
19890062104
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Grossman, B.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Haftka, R. T.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Kao, P.-J.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Polen, D. M.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Rais-Rohani, M.
(Virginia Polytechnic Institute and State University Blacksburg, United States)
Sobieszczanski-Sobieski, J.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1989
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 89-2129
Accession Number
89A49475
Funding Number(s)
CONTRACT_GRANT: NAG1-603
CONTRACT_GRANT: NSF DMC-86-15336
Distribution Limits
Public
Copyright
Other

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