Splice joints for composite aircraft fuselages and other structures
Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first pa...
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| creator | Stulc Jeffrey F Clapp Brian C Rolfes Neal G Chan Wallace C |
| description | Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion. |
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| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US9738371B2</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US9738371B2</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US9738371B23</originalsourceid><addsrcrecordid>eNqNyrENAjEMAMA0FAjYwQtQQIqHlheI_qF-WcaBoBBHtrM_DQNQXXPLME6tZGJ4S65ukESB5NPEsjNgVlJMDqkbF3yyAdYHiL9YwVw7eVe2dVgkLMabn6sAl_NtvG65yczWkLiyz_fpOMRDHHanffyjfAFcWjLd</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Splice joints for composite aircraft fuselages and other structures</title><source>esp@cenet</source><creator>Stulc Jeffrey F ; Clapp Brian C ; Rolfes Neal G ; Chan Wallace C</creator><creatorcontrib>Stulc Jeffrey F ; Clapp Brian C ; Rolfes Neal G ; Chan Wallace C</creatorcontrib><description>Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.</description><language>eng</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; COSMONAUTICS ; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR ; GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT ; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR ; HELICOPTERS ; PERFORMING OPERATIONS ; TRANSPORTING</subject><creationdate>2017</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&date=20170822&DB=EPODOC&CC=US&NR=9738371B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76516</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20170822&DB=EPODOC&CC=US&NR=9738371B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Stulc Jeffrey F</creatorcontrib><creatorcontrib>Clapp Brian C</creatorcontrib><creatorcontrib>Rolfes Neal G</creatorcontrib><creatorcontrib>Chan Wallace C</creatorcontrib><title>Splice joints for composite aircraft fuselages and other structures</title><description>Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>COSMONAUTICS</subject><subject>DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR</subject><subject>GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT</subject><subject>HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR</subject><subject>HELICOPTERS</subject><subject>PERFORMING OPERATIONS</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2017</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNyrENAjEMAMA0FAjYwQtQQIqHlheI_qF-WcaBoBBHtrM_DQNQXXPLME6tZGJ4S65ukESB5NPEsjNgVlJMDqkbF3yyAdYHiL9YwVw7eVe2dVgkLMabn6sAl_NtvG65yczWkLiyz_fpOMRDHHanffyjfAFcWjLd</recordid><startdate>20170822</startdate><enddate>20170822</enddate><creator>Stulc Jeffrey F</creator><creator>Clapp Brian C</creator><creator>Rolfes Neal G</creator><creator>Chan Wallace C</creator><scope>EVB</scope></search><sort><creationdate>20170822</creationdate><title>Splice joints for composite aircraft fuselages and other structures</title><author>Stulc Jeffrey F ; Clapp Brian C ; Rolfes Neal G ; Chan Wallace C</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US9738371B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2017</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>COSMONAUTICS</topic><topic>DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR</topic><topic>GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT</topic><topic>HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR</topic><topic>HELICOPTERS</topic><topic>PERFORMING OPERATIONS</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>Stulc Jeffrey F</creatorcontrib><creatorcontrib>Clapp Brian C</creatorcontrib><creatorcontrib>Rolfes Neal G</creatorcontrib><creatorcontrib>Chan Wallace C</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Stulc Jeffrey F</au><au>Clapp Brian C</au><au>Rolfes Neal G</au><au>Chan Wallace C</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Splice joints for composite aircraft fuselages and other structures</title><date>2017-08-22</date><risdate>2017</risdate><abstract>Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
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| subjects | AEROPLANES AIRCRAFT AVIATION COSMONAUTICS DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR HELICOPTERS PERFORMING OPERATIONS TRANSPORTING |
| title | Splice joints for composite aircraft fuselages and other structures |
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