EP 2408665 A2 20120125 - FUSELAGE CELL STRUCTURE FOR AN AIRCRAFT IN HYBRID DESIGN
Title (en)
FUSELAGE CELL STRUCTURE FOR AN AIRCRAFT IN HYBRID DESIGN
Title (de)
RUMPFZELLENSTRUKTUR FÜR EIN FLUGZEUG IN HYBRIDBAUWEISE
Title (fr)
STRUCTURE CELLULAIRE DE FUSELAGE DE CONSTRUCTION HYBRIDE POUR UN AVION
Publication
Application
Priority
- EP 2010053331 W 20100316
- DE 102009013585 A 20090317
- US 16087209 P 20090317
Abstract (en)
[origin: CA2755840A1] The invention relates to a fuselage cell structure in hybrid design for an aircraft, wherein the fuselage cell structure is formed having a plurality of skin fields (2, 3, 30-32, 42, 43, 70, 71), longitudinal struts (53, 88, 89) and cross struts, in particular ribs (18, 59), creating a plurality of longitudinal and/or cross seams (1, 29, 41, 77, 83). At least one skin field (2, 31, 32, 71) is double-shelled and at least one skin field (3, 30, 43, 70) is designed monolithically. According to the invention, there is at least one longitudinal bracket (10, 81, 82) having a first and a second longitudinal flange (11, 12) in the region of the at least one longitudinal seam (1, 83) between a monolithic and a double-shelled skin field (2, 3, 70, 71), wherein the longitudinal flanges (11, 12) are connected to each other offset by means of an inclined bridge (13). In the region of the at least one cross seam (29, 41, 77), between a monolithic and a double-shelled skin field (30, 31, 42, 43, 70, 71), there is at least one load transition (34, 56, 90, 91) for linking at least one longitudinal strut (53, 88, 89) located on the monolithic skin field (43, 70) to the at least one double-shelled skin field (42, 71). A load flow compatible connection is created between a monolithic and a double-shelled skin field (2, 3, 70, 71) by the longitudinal brackets, wherein at the same time the core structure (4, 74) of the double-shelled skin field (2, 71) is laterally sealed. The load transitions (29, 41, 90, 91) in the region of the cross seams (29, 41, 77) ensure an effective load distribution of the loads originating from the longitudinal struts (53, 88, 89) to the double-shelled skin fields (31, 32, 42, 71), wherein an additional stiffening and sealing of the otherwise open core structure (44, 74) can be simultaneously achieved by means of an optional cross bracket (37, 49, 84).
IPC 8 full level
CPC (source: EP US)
B64C 1/064 (2013.01 - EP US); B64C 1/065 (2013.01 - EP US); B64C 1/12 (2013.01 - EP US); B64C 2001/0072 (2013.01 - EP US); Y02T 50/40 (2013.01 - EP US)
Citation (examination)
- WO 8200974 A1 19820401 - BOEING CO [US]
- EP 0935235 A2 19990811 - EUROCOPTER DEUTSCHLAND [DE]
- DE 102007003275 A1 20080724 - AIRBUS GMBH [DE]
- DE 102007029500 A1 20090102 - AIRBUS GMBH [DE]
Designated contracting state (EPC)
AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR
DOCDB simple family (publication)
DE 102009013585 A1 20100923; DE 102009013585 B4 20120126; BR PI1009128 A2 20170530; CA 2755840 A1 20100923; CN 102427998 A 20120425; CN 102427998 B 20141015; EP 2408665 A2 20120125; JP 2012520787 A 20120910; RU 2011141820 A 20130427; RU 2482995 C1 20130527; US 2012056037 A1 20120308; US 9586668 B2 20170307; WO 2010106040 A2 20100923; WO 2010106040 A3 20110331
DOCDB simple family (application)
DE 102009013585 A 20090317; BR PI1009128 A 20100316; CA 2755840 A 20100316; CN 201080021424 A 20100316; EP 10713432 A 20100316; EP 2010053331 W 20100316; JP 2012500215 A 20100316; RU 2011141820 A 20100316; US 201013257367 A 20100316