Rigid strengthening method for large aviation thin-wall component based on optimized layout of flexible tool

Rigid strengthening method for large aviation thin-wall component based on optimized layout of flexible tool

The invention discloses a flexible tool optimized layout-based aviation large thin-wall component rigidity strengthening method, which comprises the following steps of: establishing a thin-wall component-flexible tool system dynamic model by adopting a multi-body system transfer matrix method to obt...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: LI PENGCHENG, WANG ZHONGKANG, WANG LI, KONG LINGYI, YANG ZHUOHENG, JIA BAOGUO, TIAN WEI, MIAO YUNFEI
Format: Patent
Sprache:chi ; eng
Schlagworte:
CALCULATING
COMPUTER SYSTEMS BASED ON SPECIFIC COMPUTATIONAL MODELS
COMPUTING
COUNTING
ELECTRIC DIGITAL DATA PROCESSING
PHYSICS
Online-Zugang:Volltext bestellen
Tags: Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
container_end_page
container_issue
container_start_page
container_title
container_volume
creator LI PENGCHENG
WANG ZHONGKANG
WANG LI
KONG LINGYI
YANG ZHUOHENG
JIA BAOGUO
TIAN WEI
MIAO YUNFEI
description The invention discloses a flexible tool optimized layout-based aviation large thin-wall component rigidity strengthening method, which comprises the following steps of: establishing a thin-wall component-flexible tool system dynamic model by adopting a multi-body system transfer matrix method to obtain a total transfer equation and a total transfer matrix of a system; adopting a self-adaptive genetic algorithm, coding the number of supports and the positions of the supports based on the spatial geometric information of the thin-wall component and the flexible tool, substituting the coded number and the coded positions into a total transfer equation and a total transfer matrix, obtaining the inherent frequency of the system, calculating a target function value, and carrying out optimization operation on optimization parameters; and the optimal supporting scheme of the flexible tool for the thin-wall component is obtained through loop iteration. According to the method, rapid optimization of the flexible tool o
format Patent
fullrecord <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_CN117874943A</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>CN117874943A</sourcerecordid><originalsourceid>FETCH-epo_espacenet_CN117874943A3</originalsourceid><addsrcrecordid>eNqNirsOgkAQAGksjPoP6wdQEEjQ0hCNlYWxJwfswSbL7oVbn18vhR9gNZnMLBO-Uk8dRJtQehtQSHoY0QbtwOsE7KYewT3IGamADSTp0zFDq2NQQTFoXMQO5qjBaKTPLOzeejdQD57xRQ0jmCqvk4V3HHHz4yrZno636pxi0BpjcC0KWl1dsqzclcW-yA_5P88Xa6VCWA</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Rigid strengthening method for large aviation thin-wall component based on optimized layout of flexible tool</title><source>esp@cenet</source><creator>LI PENGCHENG ; WANG ZHONGKANG ; WANG LI ; KONG LINGYI ; YANG ZHUOHENG ; JIA BAOGUO ; TIAN WEI ; MIAO YUNFEI</creator><creatorcontrib>LI PENGCHENG ; WANG ZHONGKANG ; WANG LI ; KONG LINGYI ; YANG ZHUOHENG ; JIA BAOGUO ; TIAN WEI ; MIAO YUNFEI</creatorcontrib><description>The invention discloses a flexible tool optimized layout-based aviation large thin-wall component rigidity strengthening method, which comprises the following steps of: establishing a thin-wall component-flexible tool system dynamic model by adopting a multi-body system transfer matrix method to obtain a total transfer equation and a total transfer matrix of a system; adopting a self-adaptive genetic algorithm, coding the number of supports and the positions of the supports based on the spatial geometric information of the thin-wall component and the flexible tool, substituting the coded number and the coded positions into a total transfer equation and a total transfer matrix, obtaining the inherent frequency of the system, calculating a target function value, and carrying out optimization operation on optimization parameters; and the optimal supporting scheme of the flexible tool for the thin-wall component is obtained through loop iteration. According to the method, rapid optimization of the flexible tool o</description><language>chi ; eng</language><subject>CALCULATING ; COMPUTER SYSTEMS BASED ON SPECIFIC COMPUTATIONAL MODELS ; COMPUTING ; COUNTING ; ELECTRIC DIGITAL DATA PROCESSING ; PHYSICS</subject><creationdate>2024</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20240412&amp;DB=EPODOC&amp;CC=CN&amp;NR=117874943A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,309,781,886,25568,76551</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20240412&amp;DB=EPODOC&amp;CC=CN&amp;NR=117874943A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>LI PENGCHENG</creatorcontrib><creatorcontrib>WANG ZHONGKANG</creatorcontrib><creatorcontrib>WANG LI</creatorcontrib><creatorcontrib>KONG LINGYI</creatorcontrib><creatorcontrib>YANG ZHUOHENG</creatorcontrib><creatorcontrib>JIA BAOGUO</creatorcontrib><creatorcontrib>TIAN WEI</creatorcontrib><creatorcontrib>MIAO YUNFEI</creatorcontrib><title>Rigid strengthening method for large aviation thin-wall component based on optimized layout of flexible tool</title><description>The invention discloses a flexible tool optimized layout-based aviation large thin-wall component rigidity strengthening method, which comprises the following steps of: establishing a thin-wall component-flexible tool system dynamic model by adopting a multi-body system transfer matrix method to obtain a total transfer equation and a total transfer matrix of a system; adopting a self-adaptive genetic algorithm, coding the number of supports and the positions of the supports based on the spatial geometric information of the thin-wall component and the flexible tool, substituting the coded number and the coded positions into a total transfer equation and a total transfer matrix, obtaining the inherent frequency of the system, calculating a target function value, and carrying out optimization operation on optimization parameters; and the optimal supporting scheme of the flexible tool for the thin-wall component is obtained through loop iteration. According to the method, rapid optimization of the flexible tool o</description><subject>CALCULATING</subject><subject>COMPUTER SYSTEMS BASED ON SPECIFIC COMPUTATIONAL MODELS</subject><subject>COMPUTING</subject><subject>COUNTING</subject><subject>ELECTRIC DIGITAL DATA PROCESSING</subject><subject>PHYSICS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2024</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNirsOgkAQAGksjPoP6wdQEEjQ0hCNlYWxJwfswSbL7oVbn18vhR9gNZnMLBO-Uk8dRJtQehtQSHoY0QbtwOsE7KYewT3IGamADSTp0zFDq2NQQTFoXMQO5qjBaKTPLOzeejdQD57xRQ0jmCqvk4V3HHHz4yrZno636pxi0BpjcC0KWl1dsqzclcW-yA_5P88Xa6VCWA</recordid><startdate>20240412</startdate><enddate>20240412</enddate><creator>LI PENGCHENG</creator><creator>WANG ZHONGKANG</creator><creator>WANG LI</creator><creator>KONG LINGYI</creator><creator>YANG ZHUOHENG</creator><creator>JIA BAOGUO</creator><creator>TIAN WEI</creator><creator>MIAO YUNFEI</creator><scope>EVB</scope></search><sort><creationdate>20240412</creationdate><title>Rigid strengthening method for large aviation thin-wall component based on optimized layout of flexible tool</title><author>LI PENGCHENG ; WANG ZHONGKANG ; WANG LI ; KONG LINGYI ; YANG ZHUOHENG ; JIA BAOGUO ; TIAN WEI ; MIAO YUNFEI</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN117874943A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2024</creationdate><topic>CALCULATING</topic><topic>COMPUTER SYSTEMS BASED ON SPECIFIC COMPUTATIONAL MODELS</topic><topic>COMPUTING</topic><topic>COUNTING</topic><topic>ELECTRIC DIGITAL DATA PROCESSING</topic><topic>PHYSICS</topic><toplevel>online_resources</toplevel><creatorcontrib>LI PENGCHENG</creatorcontrib><creatorcontrib>WANG ZHONGKANG</creatorcontrib><creatorcontrib>WANG LI</creatorcontrib><creatorcontrib>KONG LINGYI</creatorcontrib><creatorcontrib>YANG ZHUOHENG</creatorcontrib><creatorcontrib>JIA BAOGUO</creatorcontrib><creatorcontrib>TIAN WEI</creatorcontrib><creatorcontrib>MIAO YUNFEI</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>LI PENGCHENG</au><au>WANG ZHONGKANG</au><au>WANG LI</au><au>KONG LINGYI</au><au>YANG ZHUOHENG</au><au>JIA BAOGUO</au><au>TIAN WEI</au><au>MIAO YUNFEI</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Rigid strengthening method for large aviation thin-wall component based on optimized layout of flexible tool</title><date>2024-04-12</date><risdate>2024</risdate><abstract>The invention discloses a flexible tool optimized layout-based aviation large thin-wall component rigidity strengthening method, which comprises the following steps of: establishing a thin-wall component-flexible tool system dynamic model by adopting a multi-body system transfer matrix method to obtain a total transfer equation and a total transfer matrix of a system; adopting a self-adaptive genetic algorithm, coding the number of supports and the positions of the supports based on the spatial geometric information of the thin-wall component and the flexible tool, substituting the coded number and the coded positions into a total transfer equation and a total transfer matrix, obtaining the inherent frequency of the system, calculating a target function value, and carrying out optimization operation on optimization parameters; and the optimal supporting scheme of the flexible tool for the thin-wall component is obtained through loop iteration. According to the method, rapid optimization of the flexible tool o</abstract><oa>free_for_read</oa></addata></record>
fulltext fulltext_linktorsrc
identifier
ispartof
issn
language chi ; eng
recordid cdi_epo_espacenet_CN117874943A
source esp@cenet
subjects CALCULATING
COMPUTER SYSTEMS BASED ON SPECIFIC COMPUTATIONAL MODELS
COMPUTING
COUNTING
ELECTRIC DIGITAL DATA PROCESSING
PHYSICS
title Rigid strengthening method for large aviation thin-wall component based on optimized layout of flexible tool
url https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2024-12-17T06%3A55%3A00IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=LI%20PENGCHENG&rft.date=2024-04-12&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3ECN117874943A%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true