公开(公告)号：EP2730497A1

公开(公告)日：2014-05-14

申请号：EP12192367.6

申请日：2012-11-13

申请人： Airbus Operations GmbH

发明人： Boenning, Kenneth

IPC分类号： B64C1/14 ,  B64C1/06

CPC分类号： B64C1/1484 ,  B64C1/066 ,  B64C1/1492 ,  Y02T50/46 ,  Y10T29/49826

摘要： An aircraft window arrangement (10) comprises a sidewall lining panel (12) which is provided with a window opening (14), an inner window (22) attached to the sidewall lining panel (12) and extending across the window opening (14) formed in the sidewall lining panel (12) and an outer window (38) arranged at a distance from the inner window (22) and extending across a window opening (40) formed in an aircraft outer skin (42). The aircraft window arrangement (10) further comprises a window funnel (56) comprising an inner rim (58) facing the inner window (22) and extending along a circumference of the window opening (14) formed in the sidewall lining panel (12), and an outer rim (60) facing the outer window (38) and extending along a circumference of the window opening (40) formed in the aircraft outer skin (42). The window funnel (56) is formed separate from the sidewall lining panel (12). The window funnel (56) may be attached to a retainer (44) for retaining the outer window (38).

公开(公告)号：EP2683607A1

公开(公告)日：2014-01-15

申请号：EP12702735.7

申请日：2012-01-27

申请人： PPG Industries Ohio, Inc.

发明人： DEGANIS, Luis E. ,  SONG, Di ,  STEWART, Sherman D.

IPC分类号： B64C1/14

CPC分类号： B64C1/1492

摘要： An aircraft transparency includes a first ply having a first major surface and a second major surface. A second ply is spaced from the first ply and has a third major surface and a fourth major surface. A polymeric interlayer is located between the first and second plies. At least one bore extends through the first and second plies and the interlayer. A high strength bushing is located in the bore, with an outer sidewall of the bushing in direct contact with the material of the first and second plies. In one embodiment, the bore is a tapered bore and the bushing has a tapered outer sidewall. In another embodiment, the bore is a cylindrical bore and the bushing has a cylindrical outer sidewall.

公开(公告)号：EP1945500B1

公开(公告)日：2012-10-31

申请号：EP06791840.9

申请日：2006-09-05

申请人： Airbus Operations GmbH

发明人： BROWNJOHN, Nicholas ,  MÜHLTHALER, Georg ,  MÜLLER, Rainer

IPC分类号： B64C1/14

CPC分类号： B64C1/1484 ,  B64C1/1492

公开(公告)号：EP2094561B8

公开(公告)日：2012-04-11

申请号：EP07819831.4

申请日：2007-11-15

申请人： Airbus Operations GmbH

发明人： KRAHN, Stefan

IPC分类号： B64C1/14

CPC分类号： B64C1/1492

摘要： Window element (1, 23) with a covering tape (7, 36) and a covering means (8, 35) and comprising a window assembly (5, 25) which can be fixed in a hermetically sealed manner to the window frame (4, 24) by means of a retainer (15, 26), the window frame (4, 24) being enclosed by an encircling seal (11, 32) which has an encircling recess (12, 33).

公开(公告)号：EP2340201A1

公开(公告)日：2011-07-06

申请号：EP08877199.3

申请日：2008-09-30

申请人： Sikorsky Aircraft Corporation

发明人： AU-YEUNG, Honmartin, K. ,  GOLDSCHMIDT, David, J. ,  STOBIECKI, Anthony, Z.

IPC分类号： B64C1/14 ,  B64C1/32 ,  F42B1/00

CPC分类号： B64C1/1492 ,  B64C1/32 ,  F42B1/00 ,  F42D3/00

摘要： A pyrotechnic egress system includes an air encapsulation member which at least partially surrounds a charge holder which contains an explosive cord.

公开(公告)号：EP2252504A1

公开(公告)日：2010-11-24

申请号：EP09717217.5

申请日：2009-02-16

申请人： Airbus Operations GmbH

发明人： DITTMAR, Volker ,  ROHDE, Jens ,  BRUNKEN, Renke ,  LANGE, Matthias

IPC分类号： B64C1/14

CPC分类号： B64C1/1492 ,  B64C1/061

摘要： The invention relates to the fuselage structure of an airplane comprising an outer skin (1) that is stiffened through a plurality of vertical transverse ribs (7) and a plurality of horizontal longitudinal ribs (8), wherein the outer skin (1) comprises a plurality of windows (5), each of which comprises a window frame (6). To be able to freely and flexibly select both the size and the arrangement of viewing or penetration openings in the fuselage hull, it is provided according to the invention that at least one transverse rib (7) runs through the window frame (6) of a window (5) so that the transverse rib ends in an upper section (9) of the window frame (6) and in a lower section (10) of the window frame (6).

公开(公告)号：EP2094561A1

公开(公告)日：2009-09-02

申请号：EP07819831.4

申请日：2007-11-15

申请人： Airbus Deutschland GmbH

发明人： KRAHN, Stefan

IPC分类号： B64C1/14

CPC分类号： B64C1/1492

摘要： Window element (1, 23) with a covering tape (7, 36) and a covering means (8, 35) and comprising a window assembly (5, 25) which can be fixed in a hermetically sealed manner to the window frame (4, 24) by means of a retainer (15, 26), the window frame (4, 24) being enclosed by an encircling seal (11, 32) which has an encircling recess (12, 33).

公开(公告)号：EP1753655B1

公开(公告)日：2009-08-05

申请号：EP05742842.7

申请日：2005-05-24

申请人： Airbus Deutschland GmbH

发明人： BOLD, Jens

IPC分类号： B64C1/14

CPC分类号： B64C1/1492

摘要： A window frame (1) for installation in the exterior shell (5) of an aircraft, which comprises in each case at least one outer flange (2), one inner flange (3), and one vertical flange (4) arranged perpendicular and between these flanges, is manufactured from a fiber-reinforced thermoplastic material, by, first, manufacturing a semifinished part from webbing and thermoplastic material, which subsequently is deep-drawn in a molding tool. The window frame (1) comprises multiple substructures (16-19) welded to one another and has a core (17) comprising a unidirectional-running webbing.

公开(公告)号：EP1748926B1

公开(公告)日：2009-04-08

申请号：EP05777883.9

申请日：2005-05-24

申请人： Airbus Deutschland GmbH (HRB 43527)

发明人： BOLD, Jens

IPC分类号： B64C1/14

CPC分类号： B64C1/1492

摘要： With a window frame (1) for installation in the exterior shell (5) of an aircraft, which comprises at least one outer flange (2), an inner flange (3), and a vertical flange (4) arranged perpendicular to and between these flanges, a vertical flange is attached to a window element (7, 8) to be held. This is fixed in its position via a plurality of holder elements (10) distributed at equidistance over the periphery of the window frame (1), the holder elements (10) being connected with the outer flange (2) of the window frame. Each of the holder elements (10) comprises a base plate (11) with a pin (12) arranged perpendicular to the plate surface, as well as a downholder clip (13) that can be brought into force-fit engagement with the pin (12). The outer surfaces of the pin are provided with a sawtooth-like structure, which is brought into engagement with hook-shaped clamping elements (15) flexibly formed on the downholder clip (13) and over which a ring-shaped locking element (14) is displaced. The holder elements (10) comprise a thermoplastic material, which can be provided with reinforcement fibers and are made by die casting. Before installation of the window frame (1) in the aircraft, the base plates (11) of the holder elements (10) are adhered to the outer flange (2) of the window frame (1), and upon mounting, are riveted with these to the exterior shell (5) of the aircraft.

公开(公告)号：EP2024228A1

公开(公告)日：2009-02-18

申请号：EP07729698.6

申请日：2007-05-31

申请人： Airbus Deutschland GmbH (HRB 43527)

发明人： PAHL, Guenter

IPC分类号： B64C1/14

CPC分类号： B64C1/068 ,  B64C1/12 ,  B64C1/1492

摘要： The present invention provides a method for the production of a fuselage structure, and a fuselage structure, in particular of an aircraft or spacecraft, with an inner shell arrangement (20) which has an upper inner shell (21) and a lower inner shell (22), the upper inner shell (21) being spaced apart at least in some sections from the lower inner shell (22) by a first gap (23) in order to form a window region; and a window band (41) which is arranged at least in the window region and has a pane device which comprises a grid structure (10) which absorbs fuselage forces.