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1. 发明申请

US20150034782A1 Component arrangement on an aircraft structure, and a method for the installation of a component into an aircraft structure 有权
标题翻译：飞机结构上的部件布置，以及用于将部件安装到飞行器结构中的方法
公开(公告)号：US20150034782A1
公开(公告)日：2015-02-05
申请号：US14003004
申请日：2012-02-29
申请人： Volker Reye , Stefan Tacke , Cyrille Billard , Kai Streit
发明人： Volker Reye , Stefan Tacke , Cyrille Billard , Kai Streit
IPC分类号： B64D43/00
CPC分类号： B64D43/00 , B64D43/02 , Y10T29/49826
摘要： A component arrangement on an aircraft structure, in particular on a fuselage structure of an aircraft, with at least one mounting structure connected with the aircraft structure, and at least one component to be assigned to the aircraft structure, in particular a measuring device. At least one component carrier is provided to receive the component to be mounted, wherein the component carrier is connected with the mounting structure, and an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure. Also a method for the installation of a component into an aircraft structure with a mounting structure including the step of connecting the component with the mounting structure via a component carrier, so that an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure.
摘要翻译：飞机结构上的组件装置，特别是在具有与飞行器结构连接的至少一个安装结构的飞机的机身结构上的部件布置，以及要分配给飞行器结构的至少一个部件，特别是测量装置。提供至少一个分量载体以接收待安装的部件，其中部件载体与安装结构连接，并且部件载体的远离部件的外表面与该部件的外表面大致平齐飞机结构。还有一种用于将部件安装到具有安装结构的飞行器结构中的方法，其包括通过部件载体将部件与安装结构连接的步骤，使得部件载体的远离部件的外表面延伸大致与飞行器结构的外表面齐平。

2. 发明授权

US08444090B2 Transverse butt connection between two fuselage sections 失效
标题翻译：两个机身部分之间的横向对接
公开(公告)号：US08444090B2
公开(公告)日：2013-05-21
申请号：US12735799
申请日：2009-02-16
申请人： Volker Reye , Stefan Tacke , Stephan Mischereit
发明人： Volker Reye , Stefan Tacke , Stephan Mischereit
IPC分类号： 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，更特别地，用于创造用于飞行器的机身单元，可以具有多个在外皮上彼此均匀地平行间隔布置的桁条。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化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和两个端部区域由圆周横向对接带执行，该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，其中楔形物可以推入每个横向对接带楔形表面和用于公差的表面楔形表面之间机身部分之间的补偿。

3. 发明授权

US09493247B2 Component arrangement on an aircraft structure, and a method for the installation of a component into an aircraft structure 有权
公开(公告)号：US09493247B2
公开(公告)日：2016-11-15
申请号：US14003004
申请日：2012-02-29
申请人： Volker Reye , Stefan Tacke , Cyrille Billard , Kai Streit
发明人： Volker Reye , Stefan Tacke , Cyrille Billard , Kai Streit
IPC分类号： B64C1/14 , B64D43/00 , B64D43/02
CPC分类号： B64D43/00 , B64D43/02 , Y10T29/49826
摘要： A component arrangement on an aircraft structure, in particular on a fuselage structure of an aircraft, with at least one mounting structure connected with the aircraft structure, and at least one component to be assigned to the aircraft structure, in particular a measuring device. At least one component carrier is provided to receive the component to be mounted, wherein the component carrier is connected with the mounting structure, and an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure. Also a method for the installation of a component into an aircraft structure with a mounting structure including the step of connecting the component with the mounting structure via a component carrier, so that an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure.

4. 发明授权

US08528865B2 Connecting arrangement for joining two stiffening elements having different cross-sectional profiles for an aircraft or spacecraft, and shell component 有权
标题翻译：用于连接用于飞行器或航天器和壳体部件的具有不同横截面轮廓的两个加强元件的连接装置
公开(公告)号：US08528865B2
公开(公告)日：2013-09-10
申请号：US12838950
申请日：2010-07-19
申请人： Stefan Tacke , Hauke Lengsfeld , Volker Reye
发明人： Stefan Tacke , Hauke Lengsfeld , Volker Reye
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C2001/0072 , Y02T50/43 , Y10T403/70
摘要： A connecting arrangement for connecting two reinforcing elements of an aircraft or spacecraft, wherein the reinforcing elements have different cross-sectional profiles with at least one foot portion and at least one comb portion, at least one foot portion connecting element which on one side can be adapted to the geometric shape of the foot portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the foot portion of the second reinforcing element and can be connected rigidly thereto; and at least one comb portion connecting element which on one side can be adapted to the geometric shape of the comb portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the comb portion of the second reinforcing element and can be connected rigidly thereto.
摘要翻译：一种用于连接飞行器或航天器的两个增强元件的连接装置，其中所述加强元件具有不同的横截面轮廓，其具有至少一个脚部和至少一个梳齿部分，至少一个脚部连接元件可以在一侧适合于第一增强元件的脚部的几何形状，并且在相对侧上可以适应于第二增强元件的脚部的几何形状，并且可以刚性连接到其上; 并且至少一个梳状部分连接元件，其一侧可以适应于第一增强元件的梳理部分的几何形状，并且在相对侧上适合于第二增强元件的梳齿部分的几何形状，以及可以与其刚性连接。

5. 发明申请

US20110011980A1 CONNECTING ARRANGEMENT FOR JOINING TWO STIFFENING ELEMENTS HAVING DIFFERENT CROSS-SECTIONAL PROFILES FOR AN AIRCRAFT OR SPACECRAFT, AND SHELL COMPONENT 有权
标题翻译：连接安装有两个具有不同的跨部门轮廓的飞机或飞机组件和两个组件的安装元件
公开(公告)号：US20110011980A1
公开(公告)日：2011-01-20
申请号：US12838950
申请日：2010-07-19
申请人： Stefan Tacke , Hauke Lengsfeld , Volker Reye
发明人： Stefan Tacke , Hauke Lengsfeld , Volker Reye
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C2001/0072 , Y02T50/43 , Y10T403/70
摘要： A connecting arrangement for connecting two reinforcing elements of an aircraft or spacecraft, wherein the reinforcing elements have different cross-sectional profiles with in each case at least one foot portion and at least one comb portion, at least one foot portion connecting element which on one side can be adapted to the geometric shape of the foot portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the foot portion of the second reinforcing element and can be connected rigidly thereto; and at least one comb portion connecting element which on one side can be adapted to the geometric shape of the comb portion of the first reinforcing element and on the opposite side can be adapted to the geometric shape of the comb portion of the second reinforcing element and can be connected rigidly thereto in each case.
摘要翻译：一种用于连接飞机或航天器的两个增强元件的连接装置，其中所述加强元件具有不同的横截面轮廓，在每种情况下具有至少一个脚部和至少一个梳状部分，至少一个脚部连接元件侧面可以适应于第一增强元件的脚部的几何形状，并且在相对侧可以适应于第二增强元件的脚部的几何形状并且可以刚性连接到其上; 并且至少一个梳状部分连接元件，其一侧可以适应于第一增强元件的梳理部分的几何形状，并且在相对侧上适合于第二增强元件的梳齿部分的几何形状，以及在每种情况下均可与其刚性连接。

6. 发明申请

US20100320322A1 TRANSVERSE BUTT CONNECTION BETWEEN TWO FUSELAGE SECTIONS 失效
标题翻译：两个熔接部分之间的横向连接
公开(公告)号：US20100320322A1
公开(公告)日：2010-12-23
申请号：US12735799
申请日：2009-02-16
申请人： Volker Reye , Stefan Tacke , Stephan Mischereit
发明人： Volker Reye , Stefan Tacke , Stephan Mischereit
IPC分类号： B64C1/00 , B23P11/00
CPC分类号： B64C1/069 , B64C1/06 , B64C2001/0072 , B64C2211/00 , Y02T50/43 , Y10T29/49826
摘要： The invention relates to a transverse butt connection (1, 24) between two fuselage sections (2, 3, 25, 26), more particularly for creating a fuselage cell for an aircraft, with a number of stringers (41, 42) arranged spaced out uniformly parallel to one another inside on an outer skin (4, 5, 27, 28).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, it is proposed according to the invention that both end areas (6, 7, 29, 30) of the fuselage sections (2, 3, 25, 26) have on the inside oppositely inclined skin wedge faces (8, 9) and the connection of the two end areas (6, 7, 29, 30) is carried out by a circumferential transverse butt strap (10, 31) which is provided with two oppositely inclined transverse butt strap wedge faces (12, 13) in the underneath area (11) wherein a wedge (14, 15, 33, 34) can be pushed in between each one transverse butt strap wedge face (12, 130) and a skin wedge face (8, 9) for tolerance compensation between the fuselage sections (2, 3, 25, 26).
摘要翻译：本发明涉及两个机身部分（2,3,25,26）之间的横向对接连接（1,24），更特别地涉及用于产生用于飞行器的机身单元，其中多个桁条（41,42）间隔布置在外皮（4,5,27,28）上彼此均匀地平行地排列。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化补偿装置实现通用公差补偿，根据本发明提出了两个端部区域（6,7,29,30）机身部分（2,3,25,26）在内侧相对倾斜的皮肤楔形面（8,9）上，并且两个端部区域（6,7,29,30）的连接通过圆周横向对接带子（10,31），其在下部区域（11）中设置有两个相对倾斜的横向对接带楔面（12,13），其中楔形物（14,15,33,34）可以推入每个横向对接带楔面（12,130）和皮肤楔面（8,9），用于机身部分（2,3,25,26）之间的公差补偿。

7. 发明申请

US20100276069A1 METHOD AND DEVICE FOR THE PRODUCTION OF TUBULAR STRUCTURAL COMPONENTS 审中-公开
标题翻译：用于生产管状结构构件的方法和装置
公开(公告)号：US20100276069A1
公开(公告)日：2010-11-04
申请号：US12794487
申请日：2010-06-04
申请人： Hauke Lengsfeld , Volker Reye
发明人： Hauke Lengsfeld , Volker Reye
IPC分类号： B29C70/56 , B32B37/10
CPC分类号： B29C70/48 , B29C33/505 , B29C70/345 , B29C70/36 , B29C70/443 , B29C70/446 , B29C70/541 , B29D23/001 , B29K2105/089 , B29K2307/04 , B29L2023/22 , B29L2031/3082 , B30B5/02 , Y02T50/43
摘要： The present invention provides a method for the production of a tubular structural component. A tubular moulding tool having an inner mould surface which is shaped corresponding to an outer surface of the structural component is provided. A support surface of an expandable support which is formed such that in an unexpanded state, it fills the moulding tool, leaving an expansion spacing of the support surface to the mould surface, is covered with a tubular fibre-woven fabric. After the support has been arranged in the moulding tool, the fibre-woven fabric is pressed against the mould surface by expanding the support and is infiltrated by a curable matrix. From another point of view, a device is provided for the production of a tubular structural component.
摘要翻译：本发明提供一种生产管状结构部件的方法。提供一种具有对应于结构部件的外表面成形的内模表面的管状模制工具。可膨胀支撑件的支撑表面被形成为使得在未膨胀的状态下，其填充模制工具，留下支撑表面到模具表面的膨胀间隔被管状纤维织物覆盖。在支撑件已经被布置在模制工具中之后，通过膨胀支撑件将纤维织物压靠在模具表面上并被可固化基体渗入。另一方面，提供了一种用于生产管状结构部件的装置。

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