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Optimum structural design with static aeroelastic constraintsThe static aeroelastic performance characteristics, divergence velocity, control effectiveness and lift effectiveness are considered in obtaining an optimum weight structure. A typical swept wing structure is used with upper and lower skins, spar and rib thicknesses, and spar cap and vertical post cross-sectional areas as the design parameters. Incompressible aerodynamic strip theory is used to derive the constraint formulations, and aerodynamic load matrices. A Sequential Unconstrained Minimization Technique (SUMT) algorithm is used to optimize the wing structure to meet the desired performance constraints.
Document ID
19890015800
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bowman, Keith B (Air Force Wright Aeronautical Labs. Wright-Patterson AFB, OH., United States)
Grandhi, Ramana V. (Wright State Univ. Dayton, OH., United States)
Eastep, F. E. (Dayton Univ. OH., United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1989
Publication Information
Publication: NASA. Langley Research Center, Recent Advances in Multidisciplinary Analysis and Optimization, Part 1
Subject Category
Aircraft Design, Testing And Performance
Accession Number
89N25171
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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