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1. 发明公开

EP1966046A1 MODULE FOR AN AIRCRAFT 审中-公开
标题翻译：飞机模块
公开(公告)号：EP1966046A1
公开(公告)日：2008-09-10
申请号：EP06841173.5
申请日：2006-12-27
申请人： Airbus Deutschland GmbH , Airbus SAS
发明人： SAINT-JALMES, Bruno , REZAG, André , ZANEBONI, Jason , SCHUMACHER, Markus , MUIN, Andrew , HAACK, Cord , CARR, Michael
IPC分类号： B64D11/06 , B64D11/00
CPC分类号： B64D11/003 , B64C1/18 , B64D11/00 , B64D11/0015 , B64D11/00154 , B64D11/06 , B64D11/0601 , B64D11/0604 , B64D11/0611 , B64D11/0626 , B64D11/0627 , B64D11/0631 , B64D11/0639 , B64D11/06395 , B64D11/0649 , B64D11/0696 , B64D2011/0046 , B64D2011/0053 , Y02T50/46 , Y10T29/49826
摘要： The present invention relates to a module for an aircraft. The aircraft having a fuselage structure (6) and a floor element (5).The floor element (5) defining a floor plane. The module comprises a frame device (2), wherein the frame device (2) is adapted for mounting a functional element (4) and wherein the frame device (2) is adapted for attachment to the floor element (5) of the aircraft at a first location in the floor plane (7). The frame device (2) is adapted for attachment to the fuselage structure (6) of the aircraft at a second location (7'), wherein the second location is not in the floor plane.
摘要翻译：飞机模块技术领域本发明涉及一种飞机模块。该飞机具有机身结构（6）和地板元件（5）。地板元件（5）限定了地板平面。该模块包括框架装置（2），其中框架装置（2）适于安装功能元件（4），并且其中框架装置（2）适于附接到飞机的地板元件（5）在地板平面（7）中的第一位置。框架装置（2）适于在第二位置（7'）附接到飞机的机身结构（6），其中第二位置不在地板平面中。

2. 发明授权

EP1966046B1 MODULE FOR AN AIRCRAFT 有权
公开(公告)号：EP1966046B1
公开(公告)日：2019-04-17
申请号：EP06841173.5
申请日：2006-12-27
申请人： Airbus Deutschland GmbH , Airbus SAS
发明人： SAINT-JALMES, Bruno , REZAG, André , ZANEBONI, Jason , SCHUMACHER, Markus , MUIN, Andrew , HAACK, Cord , CARR, Michael
IPC分类号： B64D11/06 , B64D11/00

3. 发明授权

EP2032430B1 AIRCRAFT FUSELAGE STRUCTURE AND METHOD FOR ITS PRODUCTION 有权
标题翻译：平面船体结构及其制造方法
公开(公告)号：EP2032430B1
公开(公告)日：2010-04-28
申请号：EP07729879.2
申请日：2007-06-05
申请人： Airbus Deutschland GmbH
发明人： HAACK, Cord
IPC分类号： B64C1/00 , B64C1/06 , B64C1/12
CPC分类号： B64C1/068 , B64C1/061 , B64C1/12 , B64C2001/0045 , B64C2001/0072 , B64C2001/0081 , Y02T50/43 , Y10T29/49947
摘要： An aircraft fuselage structure which is constructed from a plurality of shells which are joined together is disclosed. Each shell forms part of the aircraft fuselage and comprises a support structure and a skin which is arranged on the latter and outwardly seals the aircraft fuselage in a compression-proof manner. The aircraft fuselage structure comprises an upper and side shell and a lower shell, of which the lower shell has a radius which is essentially significantly larger than the radius of the upper and side shell. The upper and side shell and the lower shell are joined together at transition regions extending in the longitudinal direction of the aircraft. The support structure of the lower shell is designed in terms of its strength in such a manner that it is capable of absorbing the internal pressure loading of the lower shell without the use of a main crossmember.

4. 发明公开

EP2032430A2 AIRCRAFT FUSELAGE STRUCTURE AND METHOD FOR ITS PRODUCTION 有权
标题翻译：飞机机体结构及其生产方法
公开(公告)号：EP2032430A2
公开(公告)日：2009-03-11
申请号：EP07729879.2
申请日：2007-06-05
申请人： Airbus Deutschland GmbH
发明人： HAACK, Cord
IPC分类号： B64C1/00 , B64C1/06 , B64C1/12
CPC分类号： B64C1/068 , B64C1/061 , B64C1/12 , B64C2001/0045 , B64C2001/0072 , B64C2001/0081 , Y02T50/43 , Y10T29/49947
摘要： An aircraft fuselage structure which is constructed from a plurality of shells which are joined together is disclosed. Each shell forms part of the aircraft fuselage and comprises a support structure and a skin which is arranged on the latter and outwardly seals the aircraft fuselage in a compression-proof manner. The aircraft fuselage structure comprises an upper and side shell and a lower shell, of which the lower shell has a radius which is essentially significantly larger than the radius of the upper and side shell. The upper and side shell and the lower shell are joined together at transition regions extending in the longitudinal direction of the aircraft. The support structure of the lower shell is designed in terms of its strength in such a manner that it is capable of absorbing the internal pressure loading of the lower shell without the use of a main crossmember.
摘要翻译：描述了一种飞机机身结构，其由多个连接在一起的壳体（11,12）构成，每个壳体形成飞机机身（10）的一部分并且包括支撑结构（13,13a，14,14a）和（15,16），所述表皮（15,16）布置在所述表皮上并且以防压方式向外密封所述飞机机身（10）。根据本发明，飞机机身结构包括上壳体和侧壳体（11）和下壳体（12），其下壳体（12）具有半径（R2），该半径（R2）基本上明显大于半径），所述上壳体和所述侧壳体（11）以及所述下壳体（12）在沿所述飞机的纵向方向延伸的过渡区域（18,19）处连接在一起，并且所述支撑结构（12）的下部壳体（13,13a）在其强度方面设计成能够在不使用主横梁的情况下吸收下壳体（12）的内压负荷。

5. 发明授权

EP2027012B1 TAIL STRUCTURE FOR AN AIRCRAFT OR SPACECRAFT 有权
标题翻译：航空器或航天器的尾部结构
公开(公告)号：EP2027012B1
公开(公告)日：2015-10-07
申请号：EP07730127.3
申请日：2007-06-13
申请人： Airbus Deutschland GmbH
发明人： HAACK, Cord
IPC分类号： B64C1/06
CPC分类号： B64C1/068 , B64C1/061 , B64C1/10 , B64C1/26 , B64D2027/264 , B64G1/00

6. 发明授权

EP2021762B1 TEST DEVICE 有权
标题翻译：测试设备
公开(公告)号：EP2021762B1
公开(公告)日：2015-03-18
申请号：EP07725624.6
申请日：2007-05-29
申请人： Airbus Deutschland GmbH
发明人： JOHANNSEN, Uwe , SCHOPENHAUER, Wolfram , PEITZ, Hilmar , HAACK, Cord
IPC分类号： G01N3/02 , B60N2/44 , G01M7/08 , G01M17/007 , B64D11/06
CPC分类号： G01N3/02 , B60N2/90 , G01M99/001 , G01N2203/0246
摘要： U-profiles (3a-b) are arranged on a load cell (2) so that limbs (4a-b) of the profiles are contacted to the surface of the load cell and are fixed to the load cell using fixing elements (5a-b). Floor plates (13a-b) are fixed to the upper chord (11) of a seat rail (8) and to the connecting elements (16a-b) using fixing elements (14a-b,15a-b). The connecting elements are fixed to the limbs of the U-profiles using fixing elements (19a-b). The seat rail has a crown (12) that is arranged in the middle of the upper chord symmetrical to a bar (7) to accommodate the components of a passenger seat.

7. 发明公开

EP2027012A1 TAIL STRUCTURE FOR AN AIRCRAFT OR SPACECRAFT 有权
标题翻译：后部结构用于飞机或航天器
公开(公告)号：EP2027012A1
公开(公告)日：2009-02-25
申请号：EP07730127.3
申请日：2007-06-13
申请人： Airbus Deutschland GmbH
发明人： HAACK, Cord
IPC分类号： B64C1/10 , B64C1/26
CPC分类号： B64C1/068 , B64C1/061 , B64C1/10 , B64C1/26 , B64D2027/264 , B64G1/00
摘要： The present invention provides a tail structure (1) for an aircraft or spacecraft, which adjoins a fuselage section (2) of the aircraft or spacecraft, and comprises a support construction (3) for supporting at least one craft component {40, 41) , and a bulkhead unit (5) intended for the pressure-tight sealing of the fuselage section (2) and able to be coupled both to the support construction (3) and to the fuselage section (2) so as to form a force flow path between the at least one craft component (40, 41) and the fuselage section (2) .

8. 发明公开

EP2024227A1 AIRCRAFT FUSELAGE STRUCTURE AND METHOD FOR PRODUCING IT 有权
标题翻译：飞机船体结构及其制造方法
公开(公告)号：EP2024227A1
公开(公告)日：2009-02-18
申请号：EP07729899.0
申请日：2007-06-05
申请人： Airbus Deutschland GmbH
发明人： HAACK, Cord
IPC分类号： B64C1/06
CPC分类号： B64C1/068 , Y10T29/49826
摘要： An aircraft fuselage structure is described with frames running in the circumferential direction, stringers running in the longitudinal direction and a skin which is arranged thereon and outwardly seals the aircraft fuselage in a compression-proof manner. According to the invention, it is provided that the aircraft fuselage structure contains prefabricated integral units (10) which each run in the circumferential direction of a fuselage segment and in which the frame (11) of a fuselage segment and connecting elements (17, 18) for connection to skin elements (20) comprising stringers (22) and skin (21) are formed.

9. 发明公开

EP2021762A1 TEST DEVICE 有权
标题翻译：测试设备
公开(公告)号：EP2021762A1
公开(公告)日：2009-02-11
申请号：EP07725624.6
申请日：2007-05-29
申请人： Airbus Deutschland GmbH (HRB 43527)
发明人： JOHANNSEN, Uwe , SCHOPENHAUER, Wolfram , PEITZ, Hilmar , HAACK, Cord
IPC分类号： G01N3/02 , B60N2/44 , G01M7/08 , G01M17/007 , B64D11/06
CPC分类号： G01N3/02 , B60N2/90 , G01M99/001 , G01N2203/0246
摘要： U-profiles (3a-b) are arranged on a load cell (2) so that limbs (4a-b) of the profiles are contacted to the surface of the load cell and are fixed to the load cell using fixing elements (5a-b). Floor plates (13a-b) are fixed to the upper chord (11) of a seat rail (8) and to the connecting elements (16a-b) using fixing elements (14a-b,15a-b). The connecting elements are fixed to the limbs of the U-profiles using fixing elements (19a-b). The seat rail has a crown (12) that is arranged in the middle of the upper chord symmetrical to a bar (7) to accommodate the components of a passenger seat.

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