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1. 发明授权

US08496207B2 Connection of cabin components, cabin component and method for connecting cabin components 有权
标题翻译：客舱部件连接，客舱部件和连接客舱部件的方法
公开(公告)号：US08496207B2
公开(公告)日：2013-07-30
申请号：US12836641
申请日：2010-07-15
申请人： Robert Alexander Goehlich , Daniel Wenninger
发明人： Robert Alexander Goehlich , Daniel Wenninger
IPC分类号： B64C1/22 , B64D11/00
CPC分类号： B64D11/003
摘要： A connection device for a plurality of cabin components of an aircraft includes a rail extending in a longitudinal direction of an aircraft structure, wherein the plurality of cabin components is disposed on the rail; and a plurality of adjustment devices configured to self-adjust each of the plurality of cabin components in the longitudinal direction.
摘要翻译：用于飞行器的多个舱室部件的连接装置包括沿飞行器结构的纵向方向延伸的轨道，其中多个舱室部件设置在轨道上; 以及多个调整装置，其被配置为在纵向方向上自适应地调节所述多个客舱部件中的每一个。

2. 发明授权

US08356772B2 Lightweight structure 有权
标题翻译：轻量结构
公开(公告)号：US08356772B2
公开(公告)日：2013-01-22
申请号：US12509008
申请日：2009-07-24
申请人： Rolf Bense , Steffen Biesek , Robert Alexander Goehlich , Karl-Hinrich Herbst , Michael Kreimeyer , Christian Kulik , Marco Pacchione
发明人： Rolf Bense , Steffen Biesek , Robert Alexander Goehlich , Karl-Hinrich Herbst , Michael Kreimeyer , Christian Kulik , Marco Pacchione
IPC分类号： B64C1/12
CPC分类号： B64C1/12 , B64C1/069 , B64C2001/0081 , Y02T50/42
摘要： A lightweight structure is disclosed, in particular a lightweight structure for an aircraft which is formed from a large number of components which can be joined together by weld joining processes. According to the invention, the lightweight structure has a component thickness which is increased corresponding to the loads in the joint region of the at least one welded joint compared to a thickness of the component outside the joint region.
摘要翻译：公开了一种轻质结构，特别是用于飞机的轻型结构，其由大量可通过焊接连接工艺连接在一起的部件形成。根据本发明，轻质结构具有相对于至少一个焊接接头的接合区域中的负载而增加的部件厚度，与组件外部的接合区域的厚度相比较。

3. 发明申请

US20120187248A1 METHOD AND DEVICE FOR THE INSTALLATION OF SYSTEMS, AND A FREIGHT LOADING SYSTEM 有权
标题翻译：用于系统安装的方法和装置以及货物装载系统
公开(公告)号：US20120187248A1
公开(公告)日：2012-07-26
申请号：US13386513
申请日：2010-07-22
申请人： Robert Alexander Goehlich , Cihangir Sayilgan
发明人： Robert Alexander Goehlich , Cihangir Sayilgan
IPC分类号： B64C1/22 , B64F5/00
CPC分类号： B64D9/00 , B64C1/20 , B64F5/50 , Y10T29/49826
摘要： Disclosed is a method for the installation of systems in an aeroplane fuselage 4, a device 2 with a rails system 14 for the execution of the method, and a freight loading system 50, which uses the rails system 14 as a guidance system for cargo 52, 54.
摘要翻译：公开了一种用于在飞机机身4中安装系统的方法，具有用于执行该方法的轨道系统14的装置2和使用轨道系统14作为货物52的引导系统的货物装载系统50 ，54。

4. 发明申请

US20100038489A1 LIGHTWEIGHT STRUCTURE 有权
标题翻译：轻型结构
公开(公告)号：US20100038489A1
公开(公告)日：2010-02-18
申请号：US12509008
申请日：2009-07-24
申请人： Rolf Bense , Steffen Biesek , Robert Alexander Goehlich , Karl-Hinrich Herbst , Michael Kreimeyer , Chiristian Kulik , Marco Pacchione
发明人： Rolf Bense , Steffen Biesek , Robert Alexander Goehlich , Karl-Hinrich Herbst , Michael Kreimeyer , Chiristian Kulik , Marco Pacchione
IPC分类号： B64C1/06
CPC分类号： B64C1/12 , B64C1/069 , B64C2001/0081 , Y02T50/42
摘要： A lightweight structure is disclosed, in particular a lightweight structure for an aircraft which is formed from a large number of components which can be joined together by weld joining processes. According to the invention, the lightweight structure has a component thickness which is increased corresponding to the loads in the joint region of the at least one welded joint compared to a thickness of the component outside the joint region.
摘要翻译：公开了一种轻质结构，特别是用于飞机的轻型结构，其由大量可通过焊接连接工艺连接在一起的部件形成。根据本发明，轻质结构具有相对于至少一个焊接接头的接合区域中的负载而增加的部件厚度，与组件外部的接合区域的厚度相比较。

5. 发明授权

US08740144B2 Passenger supply arrangement for an aeroplane 失效
标题翻译：飞机的乘客供应安排
公开(公告)号：US08740144B2
公开(公告)日：2014-06-03
申请号：US13097262
申请日：2011-04-29
申请人： Robert Alexander Goehlich , Holger Frauen , Cihangir Sayilgan
发明人： Robert Alexander Goehlich , Holger Frauen , Cihangir Sayilgan
IPC分类号： B64D11/00
CPC分类号： B64D11/00151 , B64D11/0015 , B64D11/00155 , B64D11/003 , B64D11/0624 , B64D11/0649 , B64D13/00 , Y02T50/44 , Y02T50/46
摘要： A passenger supply arrangement provides a communications system and comfort system for a passenger of an aeroplane. The passenger supply arrangement includes a presentation surface configured to be integrated into a backrest of a passenger seat of an aeroplane and a passenger supply module configured to be disposed above the passengers seats of the aeroplane. The passenger supply module includes at least one projector configured to project an image onto the presentation surface. The image includes a monitoring area for playback of video and an operating area for displaying and for actuation of operating elements of the passenger supply module.
摘要翻译：乘客供应安排为飞机乘客提供通信系统和舒适系统。乘客供应装置包括配置成集成到飞机的乘客座椅的靠背中的演示表面和被配置为设置在飞机的乘客座位上方的乘客供应模块。乘客供应模块包括至少一个投影仪，其配置成将图像投影到呈现表面上。图像包括用于播放视频的监视区域和用于显示和用于驾驶乘客供应模块的操作元件的操作区域。

6. 发明授权

US08087621B2 Holder for fixing components, in particular lines, inside an aircraft without using holes 有权
标题翻译：用于固定组件，特别是线路内的飞机内，不使用孔
公开(公告)号：US08087621B2
公开(公告)日：2012-01-03
申请号：US12273075
申请日：2008-11-18
申请人： Cihangir Sayilgan , Holger Frauen , Frank Neuhaus , Robert Alexander Goehlich , Rainer Schildt
发明人： Cihangir Sayilgan , Holger Frauen , Frank Neuhaus , Robert Alexander Goehlich , Rainer Schildt
IPC分类号： F16L3/08
CPC分类号： B64C1/406 , B64D11/0015 , B64D11/00155 , B64D11/02 , B64D11/04 , B64D13/00 , H02G3/0456
摘要： Disclosed is a holder for fixing all types of component, in particular lines, without using holes and largely without using tools inside a conventional fuselage structure of an aircraft with stringers and annular formers, the formers each being provided with an angle bracket at crossing points between a stringer and an annular former. The holder is configured so as to be split in two with a lower part and an upper part which can be connected thereto, the lower part being slidable onto an angle bracket. By attaching the upper part to the lower part, the holder is positionally fixed at the crossing point in the top region of an annular former. It is fixed in its final position by connecting the holder to a transverse line holder as a function element by means of an expansion pin or other connection elements. Other alternative function elements for fixing the components, such as a longitudinal line holder, a transverse batten or a longitudinal batten for specific installation requirements, may, if necessary, be combined with at least one holder so as to form holder arrangement with any desired degree of complexity.
摘要翻译：公开了一种用于固定所有类型的部件，特别是线，而不使用孔并且在具有桁条和环形成形器的飞行器的常规机身结构内部大部分不使用工具的情况下，各个部件都设置有尖角支架，桁条和环形成形机。保持器构造成可以分为两部分，下部和上部可以连接到其上，下部可滑动到角度支架上。通过将上部附接到下部，保持器被定位在环形成形器的顶部区域中的交叉点处。通过借助于膨胀销或其他连接元件将支架连接到作为功能元件的横线支架固定在其最终位置。用于固定组件的其他替代功能元件，例如用于特定安装要求的纵向线支架，横向板条或纵向板条，如果需要，可以与至少一个支架组合，以便形成具有任何所需程度的支架装置的复杂性。

7. 发明申请

US20110303791A1 Fuselage Section of an Aircraft and Method for the Production of the Fuselage Section 有权
标题翻译：飞机机身部分和生产机身部分的方法
公开(公告)号：US20110303791A1
公开(公告)日：2011-12-15
申请号：US13154899
申请日：2011-06-07
申请人： Holger Frauen , Robert Alexander Goehlich
发明人： Holger Frauen , Robert Alexander Goehlich
IPC分类号： B64C1/00 , B64C1/06
CPC分类号： B29C70/202 , B29D99/001 , B29L2031/3082 , B64C1/068 , B64C2001/0072 , Y02T50/43
摘要： In accordance with the method, an inside layer of a fuselage section skin made from first fibers is placed on a manufacturing surface, the first fibers being placed in one or more first fiber directions. On the inside layer, a stiffening structure is formed from stiffening fibers, the stiffening fibers being placed in one or more stiffening fiber directions. An outside layer of the fuselage section skin, comprising fourth fibers, is placed on the stiffening structure formed from stiffening fibers, the fourth fibers being placed in one or more fourth fiber directions. The stiffening structure is designed and developed in such a way that the fuselage section does not require an additional stiffening structure, is connected with the fuselage section skin, and comprises the inside layer, the stiffening structure, and the outside layer; in particular, an additional stiffening structure in the form of stringers and frames is not required.
摘要翻译：根据该方法，将由第一纤维制成的机身部分皮肤的内层放置在制造表面上，将第一纤维放置在一个或多个第一纤维方向上。在内层中，加强结构由加强纤维形成，加强纤维被放置在一个或多个加强纤维方向上。包括第四纤维的机身部分皮肤的外层被放置在由加强纤维形成的加强结构上，第四纤维被放置在一个或多个第四纤维方向上。加固结构的设计和开发方式使得机身部分不需要额外的加强结构，与机身部分皮肤相连，并且包括内层，加强结构和外层; 特别地，不需要桁条和框架形式的附加加强结构。

8. 发明申请

US20090159750A1 HOLDER FOR FIXING COMPONENTS, IN PARTICULAR LINES, INSIDE AN AIRCRAFT WITHOUT USING HOLES 有权
标题翻译：固定组件，特殊线路，不使用孔的飞机内部
公开(公告)号：US20090159750A1
公开(公告)日：2009-06-25
申请号：US12273075
申请日：2008-11-18
申请人： Cihangir Sayilgan , Holger Frauen , Frank Neuhaus , Robert Alexander Goehlich , Rainer Schildt
发明人： Cihangir Sayilgan , Holger Frauen , Frank Neuhaus , Robert Alexander Goehlich , Rainer Schildt
IPC分类号： B64C1/00
CPC分类号： B64C1/406 , B64D11/0015 , B64D11/00155 , B64D11/02 , B64D11/04 , B64D13/00 , H02G3/0456
摘要： Disclosed is a holder for fixing all types of component, in particular lines, without using holes and largely without using tools inside a conventional fuselage structure of an aircraft with stringers and annular formers, the formers each being provided with an angle bracket at crossing points between a stringer and an annular former. The holder is configured so as to be split in two with a lower part and an upper part which can be connected thereto, the lower part being slidable onto an angle bracket. By attaching the upper part to the lower part, the holder is positionally fixed at the crossing point in the top region of an annular former. It is fixed in its final position by connecting the holder to a transverse line holder as a function element by means of an expansion pin or other connection elements. Other alternative function elements for fixing the components, such as a longitudinal line holder, a transverse batten or a longitudinal batten for specific installation requirements, may, if necessary, be combined with at least one holder so as to form holder arrangement with any desired degree of complexity.
摘要翻译：公开了一种用于固定所有类型的部件，特别是线，而不使用孔并且在具有桁条和环形成形器的飞行器的常规机身结构内部大部分不使用工具的情况下固定所有类型的部件，所述成形器各自在桁条和环形成形机。保持器构造成可以分为两部分，下部和上部可以连接到其上，下部可滑动到角度支架上。通过将上部附接到下部，保持器被定位在环形成形器的顶部区域中的交叉点处。通过借助于膨胀销或其他连接元件将支架连接到作为功能元件的横线支架固定在其最终位置。用于固定组件的其他替代功能元件，例如用于特定安装要求的纵向线支架，横向板条或纵向板条，如果需要，可以与至少一个支架组合，以便形成具有任何所需程度的支架装置的复杂性。

9. 发明授权

US09333703B2 Method and device for bonding parts to be joined, as well as component 有权
标题翻译：用于粘合要接合的部件以及部件的方法和装置
公开(公告)号：US09333703B2
公开(公告)日：2016-05-10
申请号：US13534110
申请日：2012-06-27
申请人： Robert Alexander Goehlich , Malte Sander
发明人： Robert Alexander Goehlich , Malte Sander
IPC分类号： B29C65/06 , B23K20/12 , B29C65/02 , B29C65/08 , B29C35/02 , B29C65/00 , B29L31/30
CPC分类号： B29C65/0681 , B23K20/122 , B23K20/1255 , B23K20/128 , B23K2101/08 , B23K2101/18 , B23K2103/16 , B29C35/02 , B29C65/028 , B29C65/06 , B29C65/0672 , B29C65/086 , B29C65/4815 , B29C65/488 , B29C65/72 , B29C66/0242 , B29C66/0382 , B29C66/1142 , B29C66/30341 , B29C66/43 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/72143 , B29C66/73921 , B29C66/7394 , B29C66/836 , B29C66/9261 , B29K2101/12 , B29K2105/08 , B29K2105/256 , B29L2031/3082 , Y10T428/24479 , B29K2307/04 , B29K2309/08 , B29K2277/10
摘要： A method is provided for producing a bonded joint between fiber-reinforced thermoplastic parts to be joined, in which fiber-containing plastic material is mixed into the joining zone while friction stir welding the parts to be joined in the form of a butt joint. A device for carrying out such a method for a joined component is also provided.
摘要翻译：提供一种用于在要接合的纤维增强热塑性部件之间生产接合接头的方法，其中将含纤维的塑料材料混合到接合区域中，同时以对接形式的接合部件进行摩擦搅拌焊接。还提供了一种用于实现这种接合部件的方法的装置。

10. 发明授权

US08844870B2 Fuselage segment, and method for the production of a fuselage segment 有权
标题翻译：机身段，以及生产机身段的方法
公开(公告)号：US08844870B2
公开(公告)日：2014-09-30
申请号：US13262246
申请日：2010-03-30
申请人： Robert Alexander Goehlich
发明人： Robert Alexander Goehlich
IPC分类号： B64C1/00 , B64C1/12 , B32B5/32 , B64D11/00 , B32B27/04 , B64C1/40 , B64D13/00 , B32B27/02
CPC分类号： B64C1/12 , B32B1/00 , B32B3/12 , B32B3/266 , B32B5/02 , B32B5/18 , B32B5/22 , B32B5/245 , B32B5/32 , B32B7/02 , B32B15/046 , B32B27/02 , B32B27/04 , B32B2260/021 , B32B2260/046 , B32B2262/101 , B32B2262/106 , B32B2266/02 , B32B2266/0214 , B32B2266/045 , B32B2307/536 , B32B2307/718 , B32B2605/18 , B64C1/40 , B64C2001/0072 , B64C2211/00 , B64D11/00 , B64D13/00 , Y02T50/43 , Y02T50/44 , Y02T50/46 , Y10T29/49
摘要： A fuselage segment of an aircraft fuselage is provided with an outer skin and an inner skin that are spaced apart from one another by a core, wherein conduits for system installations are integrated into the core, as well as a method for manufacturing such a fuselage segment.
摘要翻译：飞机机身的机身部分设置有通过芯彼此间隔开的外皮和内皮，其中用于系统装置的导管被集成到芯中，以及用于制造这样的机身部分的方法。

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