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Structural optimization for joined-wing synthesisThe differences between fully stressed and minimum-weight joined-wing structures are identified, and these differences are quantified in terms of weight, stress, and direct operating cost. A numerical optimization method and a fully stressed design method are used to design joined-wing structures. Both methods determine the sizes of 204 structural members, satisfying 1020 stress constraints and five buckling constraints. Monotonic splines are shown to be a very effective way of linking spanwise distributions of material to a few design variables. Both linear and nonlinear analyses are employed to formulate the buckling constraints. With a constraint on buckling, the fully stressed design is shown to be very similar to the minimum-weight structure. It is suggested that a fully stressed design method based on nonlinear analysis is adequate for an aircraft optimization study.
Document ID
19930036359
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gallman, John W.
(NASA Ames Research Center Moffett Field, CA, United States)
Kroo, Ilan M.
(Stanford Univ. CA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: AIAA(USAF)NASA/OAI Symposium on Multidisciplinary Analysis and Optimization, 4th, Cleveland, OH, Sept. 21-23, 1992, Technical Papers. Pt. 2 (A93-20301 06-66)
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 92-4761
Accession Number
93A20356
Distribution Limits
Public
Copyright
Other

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