公开(公告)号：EP2662281A2

公开(公告)日：2013-11-13

申请号：EP13156022.9

申请日：2013-02-20

申请人： The Boeing Company

发明人： Moselage III, John H.

IPC分类号： B64C1/06

CPC分类号： B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49908

摘要： A fuselage assembly is provided. The fuselage assembly includes a first barrel section (210) including a body that extends from a first end (211) to a second end (213) and a second barrel section (220) coupled to said first barrel section (210). The second barrel section (220) includes a body that extends from a first end (221) to a second end (223), and the second end (213) of the first barrel section (210) is coupled to the second end (223) of the second barrel section (220). At least one member (130, 132) induces a compressive force to at least one of the first barrel section (210) and the second barrel section (220).

摘要翻译： 提供机身组件。 机身组件包括第一筒部分（210），其包括从第一端（211）延伸到第二端（213）的本体和联接到所述第一筒部（210）的第二筒部（220）。 第二筒部（220）包括从第一端（221）延伸到第二端（223）的主体，并且第一筒部（210）的第二端（213）联接到第二端部（223） ）的第二筒部（220）。 至少一个构件（130,132）对第一筒部（210）和第二筒部（220）中的至少一个引导压缩力。

公开(公告)号：EP2307272B1

公开(公告)日：2013-01-09

申请号：EP09779891.2

申请日：2009-06-23

申请人： Airbus Operations GmbH

发明人： WEBER, Frank ,  SCHÖNFELDT, Olaf

IPC分类号： B64C1/06 ,  B21J15/14 ,  B64C1/10 ,  B64F5/00

CPC分类号： B64C1/10 ,  B21J15/14 ,  B23P2700/01 ,  B64C1/068 ,  B64C1/069 ,  B64C2001/0072 ,  B64F5/10 ,  Y02T50/43 ,  Y10T29/49826 ,  Y10T29/49895 ,  Y10T29/49966 ,  Y10T29/53417 ,  Y10T29/53913 ,  Y10T29/53961 ,  Y10T29/53974

摘要： The invention relates to a method for installing an especially dome-shaped pressure bulkhead on a one-piece, substantially conical rear section for an aircraft, wherein said rear section comprises a connection area and an end area, comprising the steps: a) horizontally accommodating a prefabricated rear section in a horizontal support, b) inserting the rear section into a pivoting frame, c) pivoting the rear section into a vertical position using the pivoting frame, wherein the connection area of the rear section points upward, d) horizontally placing and centering the pressure bulkhead on the connection area, and e) joining of the pressure bulkhead with the rear section in the area of the connection area. The invention further relates to an apparatus for carrying out the method using a pivoting frame for tilting the rear section into a vertical position for installing the pressure bulkhead.

公开(公告)号：EP2540615A1

公开(公告)日：2013-01-02

申请号：EP12173507.0

申请日：2012-06-26

申请人： Airbus Operations (Société par actions simplifiée)

发明人： Cacciaguerra, Bruno ,  Depeige, Alain ,  Lacombe, Jean-Claude ,  Cazeneuve, Hélène ,  Castanet, Marc-Antoine

IPC分类号： B64C1/06

CPC分类号： B64C1/069 ,  B64C1/068 ,  B64C2001/0081 ,  B64F5/10 ,  Y10T29/49622

摘要： Dispositif d'assemblage de deux tronçons de fuselage (14a, 14b) d'aéronef comprenant chacun une peau (18a, 18b) et des raidisseurs longitudinaux (20a, 20b), le dispositif comprenant des éclisses (46) reliant des couples de raidisseurs longitudinaux (20a, 20b) alignés mutuellement appartenant respectivement auxdits tronçons (14a, 14b), chaque éclisse (46) comprenant deux pièces d'éclisse (48a, 48b) comportant chacune au moins une semelle longitudinale (50) destinée à être fixée sur un raidisseur (20a, 20b) ainsi qu'une tête d'appui transversale (54), et au moins un organe de liaison démontable (58) apte à serrer mutuellement les têtes d'appui (54) desdites pièces d'éclisse (48a, 48b) pour permettre une transmission d'efforts longitudinaux entre ces pièces d'éclisse.
Ensemble de tronçons de fuselage assemblés au moyen d'un dispositif du type décrit ci-dessus.
Procédé d'assemblage de deux tronçons de fuselage au moyen d'un dispositif du type décrit ci-dessus.

公开(公告)号：EP2200899B1

公开(公告)日：2012-08-01

申请号：EP08842153.2

申请日：2008-10-15

申请人： AIRBUS OPERATIONS (SAS)

发明人： CAZENEUVE, Hélène ,  CACCIAGUERRA, Bruno

IPC分类号： B64C1/06 ,  B64C1/12

CPC分类号： B64C1/06 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43

摘要： The invention relates to an aircraft fuselage (1) produced by assembling, at a circumferential joint (5), at least two sections (11a, 11b), each section comprising a coating (12a, 12b) and at least one element of at least one stiffener, the said two elements having a closed cross section and being assembled by a splicing piece (3)(30)(300). The elements (2a, 2b) of the stiffener and the splicing piece (3)(30)(300) are made of composite. Said splicing piece, which has two flanges (34, 35)(102, 112)(303)is fixed to the coatings (12a, 12b) and to the stiffener elements (2a, 2b) by working fastenings (7) positioned only on the flanges (34, 35)(102, 112)(303) of the said splicing piece.

公开(公告)号：EP2429894A2

公开(公告)日：2012-03-21

申请号：EP10719336.9

申请日：2010-05-10

申请人： Airbus Operations GmbH

发明人： GORR, Eugen ,  BENSE, Rolf

IPC分类号： B64C1/06

CPC分类号： B64F5/0009 ,  B64C1/061 ,  B64C1/069 ,  B64C2001/0081 ,  B64F5/10 ,  Y10T29/49622

摘要： The invention relates to a method for producing an aircraft fuselage (2) comprising at least two fuselage tubes (8, 10, 12). According to the invention, the connecting sections (20, 22) used for forming a transversal joining region (18) are initially prepared for a different transversal join and then the fuselage tubes (8, 10) are mounted about the connecting sections (20, 22). The invention also relates to an aircraft fuselage (2) comprising annular connecting sections (20, 22) used for forming said type of transversal join.

摘要翻译： 公开了一种用于制造具有至少两个机身壳体的飞行器机身的方法，其中连接段首先被准备用于形成用于稍后的横向接头的横向接合区域，并且机身套筒然后围绕连接段构造; 还公开了具有用于形成这种横向接头的环形连接段的飞行器机身。

公开(公告)号：EP2212191B1

公开(公告)日：2011-11-02

申请号：EP08849841.5

申请日：2008-11-13

申请人： Airbus Operations GmbH

发明人： TACKE, Stefan ,  ROMING, Thorsten ,  EDELMANN, Klaus

IPC分类号： B64C1/06 ,  B64C1/12 ,  F16B5/06

CPC分类号： B64C1/061 ,  B64C1/069 ,  B64C2001/0081

摘要： The invention relates to a coupling element (1, 15, 47) for interconnecting stringers (38, 39) when joining two fuselage sections (32, 33) by means of at least one cross butt bracket (37), the fuselage sections comprising on their interior respective pluralities of stringers (38, 39) arranged on fuselage skins (35, 36) and frames (41), the coupling element having a root flange (2, 16, 46) and a frame flange (3, 17, 48). The coupling element establishes a connection between the opposite stringers (38, 39), the frame (41) and the fuselage skins (35, 36) or the cross butt bracket (37) so that the coupling element (1, 15, 47) allowing not only a connection of the stringer root but also a flank connection of the stringers.

公开(公告)号：EP2310186A2

公开(公告)日：2011-04-20

申请号：EP09769478.0

申请日：2009-05-26

申请人： AIRBUS OPERATIONS (S.A.S)

发明人： GALLANT, Guillaume ,  LACOMBE, Jean-Claude

IPC分类号： B29C65/00 ,  F16L47/00

CPC分类号： B64C1/069 ,  B29C65/56 ,  B29C66/5229 ,  B29C66/71 ,  B29C66/721 ,  B29C2793/0036 ,  B29K2023/06 ,  B29K2067/00 ,  B29K2105/06 ,  B29L2031/3082 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/4932 ,  Y10T29/49622 ,  Y10T29/49826 ,  B29K2023/04

摘要： The invention relates to a method for assembling two structural elements, at least one of the two being tube-shaped and including a skin made of a fiber-reinforced composite material. The ability of said element to adapt to the shape and perimeter of the junction interface is improved by providing longitudinal grooves (5) distributed on the circumference of the junction interface. The grooves (5) are of a sufficient length to provide the junction interface with the flexibility to accommodate, through the relative radial movement of each portion located between two grooves, the differences in shape and perimeter among the junction interfaces of the two structural elements.

公开(公告)号：EP2155470B1

公开(公告)日：2011-01-12

申请号：EP08759619.3

申请日：2008-05-15

申请人： Airbus Operations GmbH

发明人： STEPHAN, Andreas

IPC分类号： B29C65/06 ,  B29C65/16 ,  B29C65/60 ,  B29C65/74 ,  B29C70/54

CPC分类号： B23K26/24 ,  B21J15/00 ,  B21J15/142 ,  B23K15/0006 ,  B23K20/122 ,  B23K26/26 ,  B23K2201/18 ,  B23K2203/10 ,  B64C1/069 ,  B64C1/12 ,  Y02T50/43 ,  Y10T29/49966 ,  Y10T29/49968 ,  Y10T428/12

摘要： A composite skin for the aeronautics and astronautics industries, and also a method for producing a composite skin of this type is provided. The method comprises the following method steps: removing excess material from a butt plate to form a butt strap at one end thereof, subsequently connecting the other end of the butt plate to a skin plate with a substance-to-substance bond, and then fastening a further skin plate to the butt strap to form the composite skin. The idea behind the invention involves replacing a rivet connection with a substance-to-substance bond. This provides the advantage that the weight of the composite skin and the production costs for the composite skin are reduced.

公开(公告)号：EP2247496A1

公开(公告)日：2010-11-10

申请号：EP09716463.6

申请日：2009-02-03

申请人： Airbus Operations GmbH

发明人： TACKE, Stefan ,  STUEBS, Andre

IPC分类号： B64C1/06 ,  B64C1/12

CPC分类号： B64C1/064 ,  B64C1/069 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/43

摘要： The present invention provides an interconnection (1), in particular in the field of aerospace. The interconnection (1) has a T stringer (9), an Ω stringer (10) and a connecting arrangement (2). The connecting arrangement connects base sections (12, 13, 15, 16) of the T stringer (9) and of the Ω stringer (10) to one another. This provides a coupling of an Ω stringer to a T stringer which is comparatively insensitive with respect to tolerances relating to the orientation of the Ω stringer (10) in relation to the T stringer (9).

公开(公告)号：EP2242682A1

公开(公告)日：2010-10-27

申请号：EP09712562.9

申请日：2009-02-11

申请人： Airbus Operations GmbH

发明人： SAUERMANN, Axel

IPC分类号： B64C1/06 ,  B29C65/00

CPC分类号： B64C1/069 ,  B29B13/025 ,  B29C65/02 ,  B29C65/20 ,  B29C65/4815 ,  B29C65/483 ,  B29C65/5042 ,  B29C66/1122 ,  B29C66/1142 ,  B29C66/43 ,  B29C66/43441 ,  B29C66/5221 ,  B29C66/54 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/73715 ,  B29C66/73921 ,  B29C66/73941 ,  B29K2071/00 ,  B29K2101/12 ,  B29K2105/06 ,  B29K2307/00 ,  B29L2031/3082 ,  B64C2001/0072 ,  Y02T50/43 ,  B29C65/00 ,  B29K2063/00 ,  B29K2307/04

摘要： The invention relates to a method of connecting two fuselage sections (1, 2, 21, 22) formed by a fibre-reinforced plastics material, in particular wound fuselage sections (1, 2, 21, 22) for aircraft fuselage cells, having a multiplicity of stringers (10, 11, 35, 36) arranged with a uniform distribution at a distance from and parallel to one another on the inner side of an outer skin (3, 4, 25, 26), with the formation of a transverse joint (5, 30). In order to be able in particular to join together wound CFRP fuselage sections so that simple tolerance compensation is made possible in a continuous, industrial production process, the method according to the invention comprises the following steps: aligning a first and a second fuselage section (1, 2, 21, 22) with respect to one another, heating and adapting at least one transverse butt strap (9, 23), formed by a fibre-reinforced thermoplastic material, in such a way that tolerance compensation between differing cross-sectional geometries of the first and second fuselage sections (1, 2, 21, 22) is made possible, or heating at least one end region (27) of a second fuselage section (2, 22) formed by a fibre-reinforced thermoplastic material, and joining together the two fuselage sections (1, 2, 21, 22).