STRUCTURE OF A FUSELAGE OF AN AIRCRAFT WITH A MESH-REINFORCED PANEL
The invention provides a structure (156) for an aircraft fuselage (150), the structure (156) comprising a skin (158) having an outer face (160) and an inner face (162) machined as a grid-stiffened panel, a plurality of frames (164), each frame shaped as the cross section of the fuselage and the fram...
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| creator | MIALHE CHRISTOPHE DRESEL ANDREAS |
| description | The invention provides a structure (156) for an aircraft fuselage (150), the structure (156) comprising a skin (158) having an outer face (160) and an inner face (162) machined as a grid-stiffened panel, a plurality of frames (164), each frame shaped as the cross section of the fuselage and the frames being arranged one after the other along a longitudinal direction of the fuselage. The outer perimeter of each frame is secured to the inner face (162), a plurality of stringers (1666a-e) extend parallel to the longitudinal direction, each stringer extending across multiple frames (164), passingthrough these at an opening provided to that end (168) in each frame, and each stringer (166a-e) is pressed against the inner face (162) and secured thereto. In the upper part and in the lower part ofthe fuselage, a torsion box (302) is provided extending parallel to the longitudinal direction, each torsion box comprising a horizontal plate and tabs which secure the plate to the inner face (162).The specific combination o |
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The outer perimeter of each frame is secured to the inner face (162), a plurality of stringers (1666a-e) extend parallel to the longitudinal direction, each stringer extending across multiple frames (164), passingthrough these at an opening provided to that end (168) in each frame, and each stringer (166a-e) is pressed against the inner face (162) and secured thereto. In the upper part and in the lower part ofthe fuselage, a torsion box (302) is provided extending parallel to the longitudinal direction, each torsion box comprising a horizontal plate and tabs which secure the plate to the inner face (162).The specific combination o</description><language>chi ; eng</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; COSMONAUTICS ; HELICOPTERS ; PERFORMING OPERATIONS ; TRANSPORTING</subject><creationdate>2020</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=20200626&DB=EPODOC&CC=CN&NR=111332453A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,778,883,25547,76298</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20200626&DB=EPODOC&CC=CN&NR=111332453A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MIALHE CHRISTOPHE</creatorcontrib><creatorcontrib>DRESEL ANDREAS</creatorcontrib><title>STRUCTURE OF A FUSELAGE OF AN AIRCRAFT WITH A MESH-REINFORCED PANEL</title><description>The invention provides a structure (156) for an aircraft fuselage (150), the structure (156) comprising a skin (158) having an outer face (160) and an inner face (162) machined as a grid-stiffened panel, a plurality of frames (164), each frame shaped as the cross section of the fuselage and the frames being arranged one after the other along a longitudinal direction of the fuselage. The outer perimeter of each frame is secured to the inner face (162), a plurality of stringers (1666a-e) extend parallel to the longitudinal direction, each stringer extending across multiple frames (164), passingthrough these at an opening provided to that end (168) in each frame, and each stringer (166a-e) is pressed against the inner face (162) and secured thereto. 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The outer perimeter of each frame is secured to the inner face (162), a plurality of stringers (1666a-e) extend parallel to the longitudinal direction, each stringer extending across multiple frames (164), passingthrough these at an opening provided to that end (168) in each frame, and each stringer (166a-e) is pressed against the inner face (162) and secured thereto. In the upper part and in the lower part ofthe fuselage, a torsion box (302) is provided extending parallel to the longitudinal direction, each torsion box comprising a horizontal plate and tabs which secure the plate to the inner face (162).The specific combination o</abstract><oa>free_for_read</oa></addata></record> |
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| language | chi ; eng |
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| subjects | AEROPLANES AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS TRANSPORTING |
| title | STRUCTURE OF A FUSELAGE OF AN AIRCRAFT WITH A MESH-REINFORCED PANEL |
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