Title:
A New Approach to Integrated Wing Design in Conceptual Synthesis and Optimization

Simple item page
dc.contributor.author DeLaurentis, Daniel A. en_US
dc.contributor.author Cesnik, Carlos Eduardo Stolf en_US
dc.contributor.author Lee, Jae-Moon en_US
dc.contributor.author Mavris, Dimitri N. en_US
dc.contributor.author Schrage, Daniel P. en_US
dc.contributor.corporatename American Institute of Aeronautics and Astronautics
dc.contributor.corporatename Georgia Institute of Technology. Aerospace Systems Design Laboratory
dc.date.accessioned 2005-05-26T14:03:40Z
dc.date.available 2005-05-26T14:03:40Z
dc.date.issued 1996-09 en_US
dc.description Presented at the 6th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, Bellevue, WA, September 4-6, 1996. en_US
dc.description.abstract Design-oriented analysis has become increasingly important as more and more problems traditionally solved in isolation are being approached from a multidisciplinary point of view. One such problem is the aeroelastic optimization of supersonic transport wings. Whereas simplified analytical techniques may not be sophisticated enough, and complex numerical models may be too cumbersome, this paper puts forward a new approach to achieving a balance between modeling fidelity and required accuracy. Higher fidelity analysis techniques, usually associated with design stages where key geometric variables have been fixed, are used to model a design space consisting of these important geometric variables. This is accomplished through the combined use of a Design of Experiment/Response Surface Method technique and parametric analysis tools (including an automated finite element grid generation procedure). The result is a prediction method for the structural weight of an aeroelastically optimized wing for use in an Integrated Product and Process Development environment, where cost, performance, and manufacturing trades can be accomplished. The technique is to be demonstrated on the aeroelastic design of a wing for a generic High Speed Civil Transport, based on a select set of planform and airfoil design variables. Finally, a framework for evaluating new technologies within the aeroelastic optimization is outlined. en_US
dc.format.extent 94284 bytes
dc.format.mimetype application/pdf
dc.identifier.uri http://hdl.handle.net/1853/6371
dc.language.iso en_US en_US
dc.publisher Georgia Institute of Technology en_US
dc.publisher Georgia Institute of Technology
dc.publisher.original American Institute of Aeronautics and Astronautics (AIAA)
dc.relation.ispartofseries ASDL;AIAA-96-4000 en_US
dc.relation.ispartofseries ASDL;AIAA-96-4000
dc.subject Wing structural design en_US
dc.subject Design analysis tools en_US
dc.subject Multi-disciplinary optimization/analysis en_US
dc.subject Aeroelasticity en_US
dc.subject Optimization en_US
dc.subject Supersonic transports en_US
dc.subject Wing geometry en_US
dc.subject Design of experiments en_US
dc.subject Response Surface Equations en_US
dc.subject Performance prediction en_US
dc.subject Weight en_US
dc.subject Integrated product and process development en_US
dc.subject Airfoil profiles en_US
dc.title A New Approach to Integrated Wing Design in Conceptual Synthesis and Optimization en_US
dc.type Text
dc.type.genre Paper
dspace.entity.type Publication
local.contributor.author Mavris, Dimitri N.
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
local.contributor.corporatename Aerospace Systems Design Laboratory (ASDL)
local.contributor.corporatename College of Engineering
relation.isAuthorOfPublication d355c865-c3df-4bfe-8328-24541ea04f62
relation.isOrgUnitOfPublication a348b767-ea7e-4789-af1f-1f1d5925fb65
relation.isOrgUnitOfPublication a8736075-ffb0-4c28-aa40-2160181ead8c
relation.isOrgUnitOfPublication 7c022d60-21d5-497c-b552-95e489a06569
Files
Original bundle
Now showing 1 - 1 of 1
Thumbnail Image
Name:
AIAA-96-4000.pdf
Size:
92.07 KB
Format:
Adobe Portable Document Format
Description:
Download
Collections
Research Publications