公开(公告)号：US09150299B2

公开(公告)日：2015-10-06

申请号：US13130257

申请日：2009-11-25

Applicant: Stefan Tacke

Inventor： Stefan Tacke

IPC: B64C1/06

CPC classification number: B64C1/061

Abstract: A shell component for an aircraft or spacecraft. The shell component includes a skin panel, a plurality of stringers which are arranged on the skin panel, a former which includes a fiber composite material and is arranged over the stringers so as to cross the stringers, and a former connection structure which includes 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: 飞机或航天器的外壳部件。 外壳部件包括皮肤面板，布置在皮肤面板上的多个桁条，前者，其包括纤维复合材料，并且布置在桁条上以跨过桁条，以及前连接结构，其包括延展性 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：US08371529B2

公开(公告)日：2013-02-12

申请号：US12868101

申请日：2010-08-25

Applicant: Stefan Tacke ,  Andre Stuebs

Inventor： Stefan Tacke ,  Andre Stuebs

IPC: B64C1/06

CPC classification number: B64C1/064 ,  B64C1/069 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/43

Abstract: The invention relates to an interconnection, including: a T-stringer which has a web portion and two foot portions; a Ω-stringer which has a comb portion and two foot portions; and a connection arrangement which joins together the foot portions of the T-stringer and of the Ω-stringer, wherein the connection arrangement joins together the T-stringer and the Ω-stringer, wherein the connection arrangement has a first and a second connection element, the connection elements connecting a first foot portion of the T-stringer to a first foot portion of the Ω-stringer, respectively, wherein the connection elements together have a substantially H-shaped outline, and wherein at least one angle bracket, in particular for connecting a former to the Ω-stringer and the T-stringer, is connected to the widening foot portions of the first and second connection elements.

Abstract translation: 本发明涉及一种互连，其包括：具有腹板部分和两个脚部的T形纵梁; 一个梳子部分和两个脚部分; 以及连接装置，所述连接装置将所述T形纵梁和所述“格栅”的所述脚部连接在一起，其中所述连接装置将所述T形纵梁和所述导轨连接在一起，其中所述连接装置具有第一和第二 连接元件，所述连接元件分别将所述T形纵梁的第一脚部分连接到所述连接元件的第一脚部分，其中所述连接元件在一起具有大致H形轮廓，并且其中至少一个尖括号 特别是用于将前者连接到＆OHgr--stringer和T型纵梁的连接件连接到第一和第二连接元件的加宽的脚部。

公开(公告)号：US20110001010A1

公开(公告)日：2011-01-06

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: B64C1/06

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：US20150034782A1

公开(公告)日：2015-02-05

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: B64D43/00

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.

Abstract translation: 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。

公开(公告)号：US08444090B2

公开(公告)日：2013-05-21

申请号：US12735799

申请日：2009-02-16

Applicant: Volker Reye ,  Stefan Tacke ,  Stephan Mischereit

Inventor： Volker Reye ,  Stefan Tacke ,  Stephan Mischereit

IPC: B64C1/06

CPC classification number: B64C1/069 ,  B64C1/06 ,  B64C2001/0072 ,  B64C2211/00 ,  Y02T50/43 ,  Y10T29/49826

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20100272954A1

公开(公告)日：2010-10-28

申请号：US12666605

申请日：2008-06-19

Applicant: Thorsten Roming ,  Thorsten Schroeer ,  Hauke Kirstein ,  Hinnik Gensch ,  Stefan Tacke

Inventor： Thorsten Roming ,  Thorsten Schroeer ,  Hauke Kirstein ,  Hinnik Gensch ,  Stefan Tacke

IPC: B32B3/10 ,  B64F5/00 ,  B23P11/00

CPC classification number: B64C1/12 ,  B64C1/064 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49826 ,  Y10T428/19 ,  Y10T428/192 ,  Y10T428/197 ,  Y10T428/24124 ,  Y10T428/24132 ,  Y10T428/24298 ,  Y10T428/24314 ,  Y10T428/24322 ,  Y10T428/24331 ,  Y10T428/24661 ,  Y10T428/24744 ,  Y10T428/24752 ,  Y10T428/24777 ,  Y10T428/2495 ,  Y10T428/249923

Abstract: This invention provides a coupling method for coupling a first and a second stiffening profile element for an outer skin of an aircraft or space craft. In a first step the stiffening profile elements are arranged on the outer skin in such a manner that the stiffening profile elements oppose each other with their respective front sides and enclose within themselves a cavity. Furthermore, a fixing hole is formed through a wall of at least one of the stiffening profile elements in the cavity inside a coupling zone of the stiffening profile element. An access opening is formed through the wall in the cavity along the coupling zone. A coupling strap, which couples the stiffening profile elements together, is fastened to the coupling zone by means of a fastening element guided through the fixing hole.

Abstract translation: 本发明提供了一种用于联接飞行器或航天飞机的外皮的第一和第二加强型材元件的联接方法。 在第一步骤中，加强型材元件以这样的方式布置在外皮上，使得加强型材元件以它们各自的前侧彼此相对并且在它们自身内包围空腔。 此外，在加强型材元件的连接区域内的空腔内的至少一个加强型材元件的壁上形成固定孔。 通过沿着耦合区域的空腔中的壁形成进入开口。 将加强型材元件连接在一起的联接带通过引导通过固定孔的紧固元件紧固到联接区域。

公开(公告)号：US20110042519A1

公开(公告)日：2011-02-24

申请号：US12868101

申请日：2010-08-25

Applicant: Stefan Tacke ,  Andre Stuebs

Inventor： Stefan Tacke ,  Andre Stuebs

IPC: B64C1/06 ,  B64C1/12

CPC classification number: B64C1/064 ,  B64C1/069 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/43

Abstract: The present invention provides an interconnection, in particular in the field of aerospace. The interconnection has a T-stringer, an Ω-stringer and a connecting arrangement. The connecting arrangement connects base sections of the T-stringer and of the Ω-stringer to one another. This provides a coupling of an Ω-stringer to a T-stringer which is comparatively insensitive with respect to tolerances relating to the orientation of the Ω-stringer in relation to the T-stringer.

Abstract translation: 本发明提供了一种互连，特别是在航天领域。 互连具有一个T形纵梁，一个“纵向”和“连接”。 连接装置将T型纵梁的基部和“OHgr”型的压头彼此连接起来。 这提供了一个与一个T-纵梁的耦合，该T型纵梁相对于相对于T型纵梁的方向的公差相对不敏感。

公开(公告)号：US20100320322A1

公开(公告)日：2010-12-23

申请号：US12735799

申请日：2009-02-16

Applicant: Volker Reye ,  Stefan Tacke ,  Stephan Mischereit

Inventor： Volker Reye ,  Stefan Tacke ,  Stephan Mischereit

IPC: B64C1/00 ,  B23P11/00

CPC classification number: B64C1/069 ,  B64C1/06 ,  B64C2001/0072 ,  B64C2211/00 ,  Y02T50/43 ,  Y10T29/49826

Abstract: 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).

Abstract translation: 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。

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。