公开(公告)号：EP2209711B1

公开(公告)日：2012-04-25

申请号：EP08839251.9

申请日：2008-09-12

申请人： AIRBUS OPERATIONS (S.A.S)

发明人： CAZENEUVE, Hélène ,  CACCIAGUERRA, Bruno ,  LACOMBE, Jean Claude ,  ANDISSAC, David

IPC分类号： B64C1/06 ,  B64C1/12

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

摘要： The invention relates to an aircraft structure (1) including stiffened panels (5) assembled at junctions, whereat the stiffeners (9) are interrupted. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. Said panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the invention includes a doubler (26) necessitating at most one additional part per panel junction zone for all of the interrupted stiffeners in said zone.

公开(公告)号：EP2257467B1

公开(公告)日：2011-11-23

申请号：EP09720770.8

申请日：2009-02-16

申请人： Airbus Operations GmbH

发明人： TACKE, Stefan ,  MISCHEREIT, Stephan ,  REYE, Volker

IPC分类号： B64C1/12 ,  B64C1/06

CPC分类号： B64C1/069 ,  B64C1/06 ,  B64C2001/0072 ,  B64C2211/00 ,  Y02T50/43 ,  Y10T29/49826

摘要： A transverse butt connection between two fuselage sections, more particularly for creating a fuselage cell for an aircraft, can have a number of stringers arranged spaced out uniformly parallel to one another inside on an outer skin. In order to enable a universal tolerance compensation with standardised compensating means within a predetermined tolerance band between two fuselage sections which are to be joined together, both end areas of the fuselage sections can have on the inside oppositely inclined skin wedge surfaces and the connection of the two end areas is carried out by a circumferential transverse butt strap which is provided with two oppositely inclined transverse butt strap wedge surfaces in the underneath area wherein a wedge can be pushed in between each one transverse butt strap wedge surface and a skin wedge surface for tolerance compensation between the fuselage sections.

摘要翻译： 两个机身部分之间的横向对接连接，特别是用于为飞行器创建机身单元的横向对接连接件可以具有多个在外皮上彼此均匀地间隔开的间隔开的桁条。 为了能够在要连接在一起的两个机身部分之间的预定公差带内的标准补偿装置实现通用公差补偿，机身部分的两个端部区域可以在内侧相对倾斜的皮肤楔形表面上，并且连接 两个端部区域由圆周横向对接带执行，该周向横向对接带在下部区域中设置有两个相对倾斜的横向对接带楔形表面，其中楔形件可以被推入每个横向对接带楔形表面和用于公差的皮肤楔形表面之间 机身部分之间的补偿。

公开(公告)号：EP2373539A1

公开(公告)日：2011-10-12

申请号：EP09805809.2

申请日：2009-12-31

申请人： Airbus Operations (S.A.S.)

发明人： BERNARD, Patrick ,  RIVA, Sébastien

IPC分类号： B64C1/06

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

摘要： The invention relates to an aircraft fuselage structure comprising at least first and second panels (1, 2) made of composite materials, placed side-by-side along a joint (6) and assembled together by means of at least one longitudinal joint (20), said longitudinal joint comprising a double Ω-shaped runner comprising: first and second Ω-shaped elements (21, 22), each including a head (21a, 22a) and two webs (21b, 21c, 22b, 22c); a first lateral flange (24) positioned as a continuation of the first web (21b) of the first Ω-shaped element; a second lateral flange (25) positioned as a continuation of the last web (22c) of the second Ω-shaped element; and a central flange (23) connecting the second web (21c) of the first Ω-shaped element with the first web (22b) of the second Ω-shaped element and covering the joint between the two panels.

公开(公告)号：EP2212191A1

公开(公告)日：2010-08-04

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：EP2209712A2

公开(公告)日：2010-07-28

申请号：EP08839369.9

申请日：2008-09-12

申请人： AIRBUS OPERATIONS (S.A.S)

发明人： GAUTHIE, Laurent ,  BERNADET, Philippe

IPC分类号： B64C1/06 ,  B64C1/12

CPC分类号： B64C1/064 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49826

摘要： The invention relates to a system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners (4) interrupted by reinforcing frames (5). At said interruptions, the stresses experienced by the stiffeners (4) must be transmitted despite the presence of the reinforcing frames (5). Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the invention includes the creation of battens (15) that cover the ends (16) of consecutive sections (6) of a stiffener (4) and the skin (7) of the fuselage (1), extending under the reinforcing frame (5) in order to join said two consecutive sections (6).

公开(公告)号：EP2155470A1

公开(公告)日：2010-02-24

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 ,  B29D31/00 ,  B29L7/00

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：EP4406828A1

公开(公告)日：2024-07-31

申请号：EP23215218.1

申请日：2023-12-08

申请人： Airbus Operations GmbH

发明人： PAUL, Carsten ,  HAACK, Cord ,  KAUFMANN, Sergej

IPC分类号： B64C1/06 ,  B64D37/30

CPC分类号： B64D37/30 ,  B64C2211/0020130101 ,  B64C1/069 ,  B64C1/068

摘要： Die vorliegende Erfindung bezieht sich auf Flugzeugsektionen für Flugzeuge. Um ein Flugzeug zur Verfügung zu stellen, das in der Zeit am Boden zwischen zwei Flugmissionen eine verbesserte Effizienz für die Vielzahl der erforderlichen Tätigkeiten zur Verfügung stellt, ist eine Flugzeugsektion (10) für ein Flugzeug vorgesehen. Die Flugzeugsektion weist wenigstens ein Flugwerkteil (12) aus der Gruppe aufweisend Tragwerk und Leitwerk und ein erstes Rumpfwerkteil (14) auf. Das wenigstens eine Flugwerkteil ist an dem Rumpfwerkteil montiert. Das erste Rumpfwerkteil weist eine erste Kopplungsstelle (16) auf, die zur lösbaren Verbindung mit einer zweiten Kopplungsstelle an einem zweiten Rumpfwerkteil ausgebildet ist, um in gekoppeltem Zustand ein integres Rumpfwerk eines Flugzeugs zu bilden. Die erste Kopplungsstelle stellt eine mechanische Kopplung (18) mit einer zweiten Kopplungsstelle zur Verfügung, bildet eine Systeminfrastrukturschnittstelle (20) und stellt eine Datenübertragungsvorrichtung (22) für eine Integritätsprüfung zur Verfügung, wenn die Flugzeugsektion mit einer anderen Flugzeugsektion gekoppelt ist. Die erste Kopplungsstelle stellt ebenfalls eine Positioniersensorik (24) für ein geführtes Andocken der Flugzeugsektion mit einer anderen Flugzeugsektion in einer Zielposition (25) zur Verfügung.

公开(公告)号：EP3213995A4

公开(公告)日：2018-07-25

申请号：EP15855700

申请日：2015-10-12

申请人： GUANGZHOU XAIRCRAFT TECH CO LTD

发明人： PENG BIN ,  XIAO DINGFENG

IPC分类号： H02K9/06 ,  B64C39/02 ,  B64D33/08

CPC分类号： B64C25/08 ,  B64C1/069 ,  B64C25/52 ,  B64C25/58 ,  B64C27/08 ,  B64C39/024 ,  B64C2025/325 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64D27/26 ,  B64D33/08 ,  H02K9/06

摘要： A rotorcraft together with a heat dissipation structure for a motor, a connecting structure for an arm and an airframe and an assembly and disassembly structure for a foot stand are provided. The rotorcraft includes: the airframe, the arm having a first end connected to the airframe, a propeller connected to the second end of the arm and driven by a motor, and the heat dissipation structure for the motor. The heat dissipation structure for the motor includes: a casing being a hollow structure having a top opening and an air inlet in a bottom portion, in which a motor body is disposed inside of the casing, and an air channel is formed between a circumferential edge of the motor body and an inner wall of the casing; a head cover connected to a revolving shaft of the motor synchronously and provided with a plurality of air flow picks on the lower surface thereof; and a mounting stand fixed to an upper surface of the head cover and configured to be connected with the propeller.

公开(公告)号：EP2487106B1

公开(公告)日：2018-07-25

申请号：EP10822016.1

申请日：2010-10-05

申请人： Mitsubishi Heavy Industries, Ltd.

发明人： YOSHIDA, Shinichi ,  TANAKA, Hideaki ,  TANAKA, Yuya

IPC分类号： B64C1/00 ,  B64C1/14 ,  B64C3/24 ,  B64C1/06 ,  B32B7/00 ,  B32B7/08 ,  B32B3/08 ,  B32B3/14 ,  B32B7/02 ,  B32B3/26 ,  B64C3/18 ,  B64C3/26

CPC分类号： B64C3/187 ,  B32B3/08 ,  B32B3/14 ,  B32B3/263 ,  B32B3/266 ,  B32B7/005 ,  B32B7/02 ,  B32B7/08 ,  B64C1/061 ,  B64C1/064 ,  B64C1/068 ,  B64C1/069 ,  B64C1/1446 ,  B64C1/1492 ,  B64C3/182 ,  B64C3/26 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T428/24322

摘要： Provided is a wing the weight of which can be reduced, with consideration given to stress concentrations in areas around access holes. A wing (1) on which a tensile load is imposed in the longitudinal direction is provided with a center section (3b), a forward section (3a), and an aft section (3c). The center section (3b) is a holed structural member that is a fiber reinforced plastic composite material article which extends in the longitudinal direction and in which access holes (5) are formed. The forward section (3a) and the aft section (3c) are reinforced plastic composite material articles that extend in the longitudinal direction of the wing (1) and are connected to the sides of the center section (3b). The tensile stiffness of the center section (3b) in the longitudinal direction is lower than the tensile stiffness of the forward section (3a) and the aft section (3c) in the longitudinal direction.

公开(公告)号：EP3335980A1

公开(公告)日：2018-06-20

申请号：EP16382611.8

申请日：2016-12-16

申请人： Airbus Operations S.L.

发明人： ARANA HIDALGO, Alberto ,  VÁZQUEZ CASTRO, Jesús Javier

IPC分类号： B64C1/06 ,  B64C1/12 ,  F16B5/00

CPC分类号： B64C1/069 ,  B64C1/12 ,  F16B5/0028 ,  F16B5/0072

摘要： System for attaching a first shell (1) with a first protrusion (1.2) and a second shell (2) with a second protrusion (2.3), comprising a butt joint (3) configured to attach the first and second shell (1,2) in an attaching interface, the butt joint (3) comprising an external strap (4) faced outward of the aircraft (10) comprising an external hole (4.1) and an external surface (4.2), an internal strap (5) faced inward of the aircraft (10), comprising an internal hole (5.1), a bolt (6), configured to pass through the external hole (4.1) and the internal hole (5.1), a nut (7) configured to fix the bolt (6) to the external (4) and internal (5) straps, the first protrusion (1.3) and second protrusion (2.3) of each structural shell (1, 2) remaining fixed between said external (4) and internal (5) strap, and a void area (8) arranged around the bolt (6), the void area (8) being an area formed by the external (4) and internal (5) strap. The first (1) and second (2) shell comprise respectively a first recess (1.4) and a second recess (2.4) over the protrusions (1.3, 2.3), and the first and second protrusions (1.3, 2.3) being located between external (4) and internal (5) strap of the butt joint (3), said first and second protrusions (1.3, 2.3) also partially occupying the void area (8).