Large deflection, nonlinear loads analysis, with application to large winglets

Large deflection, nonlinear loads analysis, with application to large winglets

The inclusion of static aeroelastic effects is essential to the accurate calculation of the aerodynamic properties of a wing, the resulting wing loads, and ultimately the mass of the wing. Within an industrial aircraft design cycle, the computational time required for structurally coupled nonlinear...

Full description

Bibliographic Details
Main Author: Broomfield, Susannah Elizabeth
Published: University of Bristol 2007
Subjects:
629.13432
Online Access:http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.492476
id ndltd-bl.uk-oai-ethos.bl.uk-492476
record_format oai_dc
spelling ndltd-bl.uk-oai-ethos.bl.uk-4924762015-03-20T05:43:04ZLarge deflection, nonlinear loads analysis, with application to large wingletsBroomfield, Susannah Elizabeth2007The inclusion of static aeroelastic effects is essential to the accurate calculation of the aerodynamic properties of a wing, the resulting wing loads, and ultimately the mass of the wing. Within an industrial aircraft design cycle, the computational time required for structurally coupled nonlinear flow solvers is impractical for the many different solutions required, even with the current development in computing power. The process currently used by most civilian aircraft manufacturers therefore makes use of time efficient linear panel methods for calculating the aerodynamics and modal data for calculating structural movements.University of Bristol.629.13432University of Bristolhttp://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.492476Electronic Thesis or Dissertation
collection NDLTD
sources NDLTD
topic 629.13432
spellingShingle 629.13432
Broomfield, Susannah Elizabeth
Large deflection, nonlinear loads analysis, with application to large winglets
description The inclusion of static aeroelastic effects is essential to the accurate calculation of the aerodynamic properties of a wing, the resulting wing loads, and ultimately the mass of the wing. Within an industrial aircraft design cycle, the computational time required for structurally coupled nonlinear flow solvers is impractical for the many different solutions required, even with the current development in computing power. The process currently used by most civilian aircraft manufacturers therefore makes use of time efficient linear panel methods for calculating the aerodynamics and modal data for calculating structural movements.University of Bristol.
author Broomfield, Susannah Elizabeth
author_facet Broomfield, Susannah Elizabeth
author_sort Broomfield, Susannah Elizabeth
title Large deflection, nonlinear loads analysis, with application to large winglets
title_short Large deflection, nonlinear loads analysis, with application to large winglets
title_full Large deflection, nonlinear loads analysis, with application to large winglets
title_fullStr Large deflection, nonlinear loads analysis, with application to large winglets
title_full_unstemmed Large deflection, nonlinear loads analysis, with application to large winglets
title_sort large deflection, nonlinear loads analysis, with application to large winglets
publisher University of Bristol
publishDate 2007
url http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.492476
work_keys_str_mv AT broomfieldsusannahelizabeth largedeflectionnonlinearloadsanalysiswithapplicationtolargewinglets
_version_ 1716793508276207616

Similar Items