公开(公告)号：US08353479B2

公开(公告)日：2013-01-15

申请号：US12742206

申请日：2008-11-13

Applicant: Stefan Tacke ,  Thorsten Roming ,  Klaus Edelmann

Inventor： Stefan Tacke ,  Thorsten Roming ,  Klaus Edelmann

IPC: B64C1/00

CPC classification number: B64C1/061 ,  B64C1/069 ,  B64C2001/0081

Abstract: A coupling element for connecting stringers in the process of joining two fuselage sections by means of at least one transverse splicing plate, wherein in each case the fuselage sections on the inside comprise a multitude of stringers arranged on fuselage skins, as well as annular frame elements, wherein the coupling element comprises a base flange and a frame element flange, and by way of the coupling element in each case a connection between the opposing stringers, the annular frame element and the fuselage skins or the transverse splicing plate takes place so that the coupling element beyond a connection of the stringer base also supports the connection of stringers on the flank side.

Abstract translation: 一种用于在通过至少一个横向拼接板连接两个机身部分的过程中连接桁条的联接元件，其中在每种情况下，内侧的机身部分包括布置在机身外壳上的多个桁条以及环形框架元件 ，其中所述联接元件包括底部凸缘和框架元件凸缘，并且通过所述联接元件，在每种情况下，相对的纵梁之间的连接，所述环形框架元件和机身外壳或横向拼接板发生，使得 连接元件超过桁条基座的连接，也支撑在侧面上的桁条的连接。

公开(公告)号：US20110236622A1

公开(公告)日：2011-09-29

申请号：US13072229

申请日：2011-03-25

Applicant: Stefan Tacke ,  Thorsten Roming

Inventor： Stefan Tacke ,  Thorsten Roming

IPC: B32B5/12

CPC classification number: B64C1/062 ,  B32B1/00 ,  B32B3/266 ,  B32B15/08 ,  B32B2262/106 ,  B32B2307/558 ,  B32B2307/56 ,  B32B2307/714 ,  B32B2605/18 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T428/24132 ,  Y10T428/24331

Abstract: In the case of a fiber composite component for energy absorption in the event of a crash for an aircraft or spacecraft, the fiber composite component is formed as a laminate construction made of CFRP layers and at least one integrated metal foil portion which is corrosion-resistant with respect to the CFRP layers. A fuselage structure portion of an aircraft or spacecraft is formed using at least one fiber composite component of this type. An aircraft or spacecraft comprises a fuselage structure portion of this type.

Abstract translation: 在用于飞机或航天器碰撞的能量吸收的纤维复合材料部件的情况下，纤维复合材料部件形成为由CFRP层和至少一个耐腐蚀的集成金属箔部分制成的层叠结构 相对于CFRP层。 飞机或航天器的机身结构部分使用这种类型的至少一个纤维复合部件形成。 飞机或航天器包括这种类型的机身结构部分。

公开(公告)号：US20100044514A1

公开(公告)日：2010-02-25

申请号：US12418153

申请日：2009-04-03

Applicant: Stefan Tacke

Inventor： Stefan Tacke

IPC: B64C1/06

CPC classification number: B64C1/069 ,  B64C2001/0072 ,  Y02T50/43

Abstract: A connection arrangement for connecting a first and second reinforcing element of an aircraft or spacecraft, the reinforcing elements each have profiled cross-sections comprising at least one foot portion and at least one web portion. They are spaced from one another at their end connection faces by a strap element. The connection arrangement comprises at least one foot portion connection element, which can be adjusted and firmly joined on one side to the geometrical shape of the foot portion of the first reinforcing element, on the other side to the geometrical shape of the foot portion of the second reinforcing element and to the interposed strip element, and comprising at least one web coupling element, which can be adjusted and firmly joined on one side to the geometrical shape of the web portion of the first reinforcing element, and on the other side to the strap element. A shell component of an aircraft or spacecraft comprises at least two shell elements connected to a strap element at a transverse seam, which shell elements each comprise at least a first and second reinforcing element which, in turn, are connected to a connection arrangement.

Abstract translation: 用于连接飞行器或航天器的第一和第二加强元件的连接装置，所述加强元件各自具有包括至少一个脚部分和至少一个腹板部分的成型横截面。 它们在其端部连接面处由带元件彼此间隔开。 连接装置包括至少一个脚部连接元件，该连接元件可以在另一侧被调节并牢固地连接在第一加强元件的脚部的几何形状的一侧上，与第一加强元件的脚部的几何形状相一致 第二增强元件和插入的带状元件，并且包括至少一个腹板联接元件，其可以在一侧被调节并牢固地连接到第一增强元件的腹板部分的几何形状，并且在另一侧到 表带元素。 飞行器或航天器的壳体部件包括在横向接缝处连接到带元件的至少两个壳体元件，所述壳体元件各自包括至少第一和第二加强元件，所述第一和第二加强元件又连接到连接装置。

公开(公告)号：US09493247B2

公开(公告)日：2016-11-15

申请号：US14003004

申请日：2012-02-29

Applicant: Volker Reye ,  Stefan Tacke ,  Cyrille Billard ,  Kai Streit

Inventor： Volker Reye ,  Stefan Tacke ,  Cyrille Billard ,  Kai Streit

IPC: B64C1/14 ,  B64D43/00 ,  B64D43/02

CPC classification number: B64D43/00 ,  B64D43/02 ,  Y10T29/49826

Abstract: 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.

公开(公告)号：US08528865B2

公开(公告)日：2013-09-10

申请号：US12838950

申请日：2010-07-19

Applicant: Stefan Tacke ,  Hauke Lengsfeld ,  Volker Reye

Inventor： Stefan Tacke ,  Hauke Lengsfeld ,  Volker Reye

IPC: B64C1/06

CPC classification number: B64C1/064 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T403/70

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US08220745B2

公开(公告)日：2012-07-17

申请号：US12418153

申请日：2009-04-03

Applicant: Stefan Tacke

Inventor： Stefan Tacke

IPC: B64C1/06

CPC classification number: B64C1/069 ,  B64C2001/0072 ,  Y02T50/43

Abstract: A connection arrangement for connecting a first and second reinforcing element of an aircraft or spacecraft, the reinforcing elements each have profiled cross-sections comprising at least one foot portion and at least one web portion. They are spaced from one another at their end connection faces by a strap element. The connection arrangement comprises at least one foot portion connection element, which can be adjusted and firmly joined on one side to the geometrical shape of the foot portion of the first reinforcing element, on the other side to the geometrical shape of the foot portion of the second reinforcing element and to the interposed strip element, and comprising at least one web coupling element, which can be adjusted and firmly joined on one side to the geometrical shape of the web portion of the first reinforcing element, and on the other side to the strap element. A shell component of an aircraft or spacecraft comprises at least two shell elements connected to a strap element at a transverse seam, which shell elements each comprise at least a first and second reinforcing element which, in turn, are connected to a connection arrangement.

Abstract translation: 用于连接飞行器或航天器的第一和第二加强元件的连接装置，所述加强元件各自具有包括至少一个脚部分和至少一个腹板部分的成型横截面。 它们在其端部连接面处由带元件彼此间隔开。 连接装置包括至少一个脚部连接元件，该连接元件可以在另一侧被调节并牢固地连接在第一加强元件的脚部的几何形状的一侧上，与第一加强元件的脚部的几何形状相一致 第二增强元件和插入的带状元件，并且包括至少一个腹板联接元件，其可以在一侧被调节并牢固地连接到第一增强元件的腹板部分的几何形状，并且在另一侧到 表带元素。 飞行器或航天器的壳体部件包括在横向接缝处连接到带元件的至少两个壳体元件，所述壳体元件各自包括至少第一和第二加强元件，所述第一和第二加强元件又连接到连接装置。

公开(公告)号：US20110297788A1

公开(公告)日：2011-12-08

申请号：US13130257

申请日：2009-11-25

Applicant: Stefan Tacke

Inventor： Stefan Tacke

IPC: B64C1/12

CPC classification number: B64C1/061

Abstract: The present invention provides a shell component for an aircraft or spacecraft. The shell component comprises a skin panel, a plurality of stringers which are arranged on the skin panel, a former which comprises a fibre composite material and is arranged over the stringers so as to cross said stringers, and a former connection structure which comprises a ductile material and a plurality of foot portions fixed to the skin panel. The foot portions each transition integrally into a shoulder portion fixed to the former over an associated fixing span, the fixing spans associated with the foot portions extending along the former substantially continuously over the stringers.

Abstract translation: 本发明提供一种用于飞行器或航天器的壳体部件。 外壳部件包括皮肤面板，多个string条，其布置在皮肤面板上，前者包括纤维复合材料，并且布置在桁条上以便穿过桁条;以及前连接结构，其包括延性 材料和固定到皮肤面板的多个脚部。 所述脚部分每个过渡成一体地形成在相关联的固定跨度上固定到前者的肩部中，所述固定跨度与沿所述前部延伸的所述脚部基本上连续地延伸到所述桁条上。

公开(公告)号：US20110011980A1

公开(公告)日：2011-01-20

申请号：US12838950

申请日：2010-07-19

Applicant: Stefan Tacke ,  Hauke Lengsfeld ,  Volker Reye

Inventor： Stefan Tacke ,  Hauke Lengsfeld ,  Volker Reye

IPC: B64C1/06

CPC classification number: B64C1/064 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T403/70

Abstract: 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.

Abstract translation: 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。