Spliced laminate for aircraft fuselage
A laminated body panel for aircraft applications comprises first and second metal layers and an adhesive layer. First and second sections in each metal layer are generally coplanar and separated by a splice line. A first splice line in a first metal layer is generally parallel to a second splice lin...
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| creator | GUNNINK JAN W OOST ROB C. V GARESCHE CARL E GREIDANUS BUWE V. W ROEBROEKS GERANDUS H. J. J |
| description | A laminated body panel for aircraft applications comprises first and second metal layers and an adhesive layer. First and second sections in each metal layer are generally coplanar and separated by a splice line. A first splice line in a first metal layer is generally parallel to a second splice line in a second metal layer, and spaced laterally from the second splice line. An adhesive layer between the metal layers preferably contains reinforcing fibers bridging across the splice lines. An aircraft fuselage or wing or empennage made with spliced body panels of the invention has fewer joints and weighs less than one made with narrower body panels containing unspliced metal layers. |
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J</creatorcontrib><description>A laminated body panel for aircraft applications comprises first and second metal layers and an adhesive layer. First and second sections in each metal layer are generally coplanar and separated by a splice line. A first splice line in a first metal layer is generally parallel to a second splice line in a second metal layer, and spaced laterally from the second splice line. An adhesive layer between the metal layers preferably contains reinforcing fibers bridging across the splice lines. An aircraft fuselage or wing or empennage made with spliced body panels of the invention has fewer joints and weighs less than one made with narrower body panels containing unspliced metal layers.</description><edition>6</edition><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 ; LAYERED PRODUCTS ; LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT ORNON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM ; PERFORMING OPERATIONS ; TRANSPORTING</subject><creationdate>1995</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=19950704&DB=EPODOC&CC=US&NR=5429326A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=19950704&DB=EPODOC&CC=US&NR=5429326A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>GUNNINK; JAN W</creatorcontrib><creatorcontrib>OOST; ROB C. 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V</creatorcontrib><creatorcontrib>GARESCHE; CARL E</creatorcontrib><creatorcontrib>GREIDANUS; BUWE V. W</creatorcontrib><creatorcontrib>ROEBROEKS; GERANDUS H. J. J</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>GUNNINK; JAN W</au><au>OOST; ROB C. V</au><au>GARESCHE; CARL E</au><au>GREIDANUS; BUWE V. W</au><au>ROEBROEKS; GERANDUS H. J. J</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Spliced laminate for aircraft fuselage</title><date>1995-07-04</date><risdate>1995</risdate><abstract>A laminated body panel for aircraft applications comprises first and second metal layers and an adhesive layer. First and second sections in each metal layer are generally coplanar and separated by a splice line. A first splice line in a first metal layer is generally parallel to a second splice line in a second metal layer, and spaced laterally from the second splice line. An adhesive layer between the metal layers preferably contains reinforcing fibers bridging across the splice lines. An aircraft fuselage or wing or empennage made with spliced body panels of the invention has fewer joints and weighs less than one made with narrower body panels containing unspliced metal layers.</abstract><edition>6</edition><oa>free_for_read</oa></addata></record> |
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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 LAYERED PRODUCTS LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT ORNON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM PERFORMING OPERATIONS TRANSPORTING |
| title | Spliced laminate for aircraft fuselage |
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