No Cover Image

Journal article 1281 views

Rapid Prediction of Worst-Case Gust Loads Following Structural Modification

H. Haddad Khodaparast, J. E Cooper, Hamed Haddad Khodaparast Orcid Logo

AIAA Journal, Volume: 52, Issue: 2, Pages: 242 - 254

Swansea University Author: Hamed Haddad Khodaparast Orcid Logo

Full text not available from this repository: check for access using links below.

Check full text

DOI (Published version): 10.2514/1.J052031

Abstract

An approach to reduce the computational effort required to determine the worst-case gust loads for aircraft is described, specifically when structural modifications are included as part of the design process. The Sherman–Morrison–Woodbury formula is employed to determine the gust response of the mod...

Full description

Published in: AIAA Journal
ISSN: 0001-1452 1533-385X
Published: 2014
Online Access: Check full text

URI: https://cronfa.swan.ac.uk/Record/cronfa15781
Tags: Add Tag
No Tags, Be the first to tag this record!
first_indexed 2013-09-07T01:58:40Z
last_indexed 2020-06-16T12:25:42Z
id cronfa15781
recordtype SURis
fullrecord <?xml version="1.0"?><rfc1807><datestamp>2020-06-16T08:40:58.0454972</datestamp><bib-version>v2</bib-version><id>15781</id><entry>2013-09-06</entry><title>Rapid Prediction of Worst-Case Gust Loads Following Structural Modification</title><swanseaauthors><author><sid>f207b17edda9c4c3ea074cbb7555efc1</sid><ORCID>0000-0002-3721-4980</ORCID><firstname>Hamed</firstname><surname>Haddad Khodaparast</surname><name>Hamed Haddad Khodaparast</name><active>true</active><ethesisStudent>false</ethesisStudent></author></swanseaauthors><date>2013-09-06</date><deptcode>AERO</deptcode><abstract>An approach to reduce the computational effort required to determine the worst-case gust loads for aircraft is described, specifically when structural modifications are included as part of the design process. The Sherman&#x2013;Morrison&#x2013;Woodbury formula is employed to determine the gust response of the modified structure using a reanalysis approach and to undertake an efficient modal reanalysis. The approach is demonstrated successfully using a simple wing and full-scale aircraft finite-element models to determine the worst-case &#x201C;1&#x2212;cosine1&#x2212;cosine&#x201D; gust following structural modification. Savings of about 56% were achieved for gust-response computations and 50% for the modal reanalysis.</abstract><type>Journal Article</type><journal>AIAA Journal</journal><volume>52</volume><journalNumber>2</journalNumber><paginationStart>242</paginationStart><paginationEnd>254</paginationEnd><publisher/><issnPrint>0001-1452</issnPrint><issnElectronic>1533-385X</issnElectronic><keywords/><publishedDay>28</publishedDay><publishedMonth>2</publishedMonth><publishedYear>2014</publishedYear><publishedDate>2014-02-28</publishedDate><doi>10.2514/1.J052031</doi><url/><notes/><college>COLLEGE NANME</college><department>Aerospace Engineering</department><CollegeCode>COLLEGE CODE</CollegeCode><DepartmentCode>AERO</DepartmentCode><institution>Swansea University</institution><apcterm/><lastEdited>2020-06-16T08:40:58.0454972</lastEdited><Created>2013-09-06T13:46:59.6625713</Created><path><level id="1">Faculty of Science and Engineering</level><level id="2">School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering</level></path><authors><author><firstname>H. Haddad</firstname><surname>Khodaparast</surname><order>1</order></author><author><firstname>J. E</firstname><surname>Cooper</surname><order>2</order></author><author><firstname>Hamed</firstname><surname>Haddad Khodaparast</surname><orcid>0000-0002-3721-4980</orcid><order>3</order></author></authors><documents/><OutputDurs/></rfc1807>
spelling 2020-06-16T08:40:58.0454972 v2 15781 2013-09-06 Rapid Prediction of Worst-Case Gust Loads Following Structural Modification f207b17edda9c4c3ea074cbb7555efc1 0000-0002-3721-4980 Hamed Haddad Khodaparast Hamed Haddad Khodaparast true false 2013-09-06 AERO An approach to reduce the computational effort required to determine the worst-case gust loads for aircraft is described, specifically when structural modifications are included as part of the design process. The Sherman–Morrison–Woodbury formula is employed to determine the gust response of the modified structure using a reanalysis approach and to undertake an efficient modal reanalysis. The approach is demonstrated successfully using a simple wing and full-scale aircraft finite-element models to determine the worst-case “1−cosine1−cosine” gust following structural modification. Savings of about 56% were achieved for gust-response computations and 50% for the modal reanalysis. Journal Article AIAA Journal 52 2 242 254 0001-1452 1533-385X 28 2 2014 2014-02-28 10.2514/1.J052031 COLLEGE NANME Aerospace Engineering COLLEGE CODE AERO Swansea University 2020-06-16T08:40:58.0454972 2013-09-06T13:46:59.6625713 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering H. Haddad Khodaparast 1 J. E Cooper 2 Hamed Haddad Khodaparast 0000-0002-3721-4980 3
title Rapid Prediction of Worst-Case Gust Loads Following Structural Modification
spellingShingle Rapid Prediction of Worst-Case Gust Loads Following Structural Modification
Hamed Haddad Khodaparast
title_short Rapid Prediction of Worst-Case Gust Loads Following Structural Modification
title_full Rapid Prediction of Worst-Case Gust Loads Following Structural Modification
title_fullStr Rapid Prediction of Worst-Case Gust Loads Following Structural Modification
title_full_unstemmed Rapid Prediction of Worst-Case Gust Loads Following Structural Modification
title_sort Rapid Prediction of Worst-Case Gust Loads Following Structural Modification
author_id_str_mv f207b17edda9c4c3ea074cbb7555efc1
author_id_fullname_str_mv f207b17edda9c4c3ea074cbb7555efc1_***_Hamed Haddad Khodaparast
author Hamed Haddad Khodaparast
author2 H. Haddad Khodaparast
J. E Cooper
Hamed Haddad Khodaparast
format Journal article
container_title AIAA Journal
container_volume 52
container_issue 2
container_start_page 242
publishDate 2014
institution Swansea University
issn 0001-1452
1533-385X
doi_str_mv 10.2514/1.J052031
college_str Faculty of Science and Engineering
hierarchytype
hierarchy_top_id facultyofscienceandengineering
hierarchy_top_title Faculty of Science and Engineering
hierarchy_parent_id facultyofscienceandengineering
hierarchy_parent_title Faculty of Science and Engineering
department_str School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering
document_store_str 0
active_str 0
description An approach to reduce the computational effort required to determine the worst-case gust loads for aircraft is described, specifically when structural modifications are included as part of the design process. The Sherman–Morrison–Woodbury formula is employed to determine the gust response of the modified structure using a reanalysis approach and to undertake an efficient modal reanalysis. The approach is demonstrated successfully using a simple wing and full-scale aircraft finite-element models to determine the worst-case “1−cosine1−cosine” gust following structural modification. Savings of about 56% were achieved for gust-response computations and 50% for the modal reanalysis.
published_date 2014-02-28T03:17:57Z
_version_ 1763750421851013120
score 11.016235

Similar Items