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1. 发明授权

US08444089B2 Pressure bulkhead and method for subdivision of an aircraft or spacecraft 有权
标题翻译：用于分舱飞机或航天器的压力舱壁和方法
公开(公告)号：US08444089B2
公开(公告)日：2013-05-21
申请号：US12678723
申请日：2008-06-18
申请人： Stephan Mischereit , Andreas Stephan
发明人： Stephan Mischereit , Andreas Stephan
IPC分类号： B64C1/10
CPC分类号： B64C1/10
摘要： The present invention provides a pressure bulkhead for subdivision of an aircraft or spacecraft into an internal and an external pressure region. The pressure bulkhead comprises a pressure plate having an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft, a supporting means which tiltably supports the edge on the inner contour, and a seal which seals the edge with the inner contour. A further aspect of the invention provides a method for subdivision of an aircraft or spacecraft into an internal and an external pressure region. Firstly, a pressure plate is provided that has an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft. In further steps, the edge is tiltably supported on the inner contour and sealed with the inner contour.
摘要翻译：本发明提供一种用于将飞行器或航天器分成内部和外部压力区域的压力舱壁。压力隔板包括压板，该压板具有与航空器或航天器的内轮廓相对应的边缘，可倾斜地支撑内轮廓上的边缘的支撑装置和将边缘与内轮廓密封的密封件。本发明的另一方面提供了一种用于将飞行器或航天器细分成内部和外部压力区域的方法。首先，提供压板，该压板的边缘成形为对应于飞行器或航天器的内轮廓。在另外的步骤中，边缘可倾斜地支撑在内轮廓上并用内轮廓密封。

2. 发明授权

US08408496B2 Fuselage cell structure of an airplane for the simplified installation and attachment of fasteners for fastening conduits 有权
标题翻译：飞机的机身单元结构，用于简化安装和连接用于紧固导管的紧固件
公开(公告)号：US08408496B2
公开(公告)日：2013-04-02
申请号：US12763796
申请日：2010-04-20
申请人： Andreas Stephan
发明人： Andreas Stephan
IPC分类号： F16B2/04
CPC分类号： B64C1/064 , B64C1/406 , F16L3/02 , F16L3/24 , H02G3/26 , H02G3/32
摘要： The invention relates to a fuselage cell structure of an aircraft for the simplified installation and attachment of at least one fastener for at least one conduit, the fuselage cell structure having a large number of reinforcing elements formed in particular using an aluminum alloy material. According to the invention, the reinforcing elements within the fuselage cell structure are provided with at least one groove in which the fasteners can be secured by producing a combined pressing and clamping fit creating a positive fit at least in certain regions. For this purpose, the fasteners can have at the lower face thereof, for example, two retaining feet which can be spread apart and attached by driving a fixing element into the groove. The reinforcing elements are continuous stringers preferably produced by extrusion and cross-bars, the required grooves being simultaneously extruded during the production process.
摘要翻译：本发明涉及飞行器的机身单元结构，用于简化安装和附接至少一个紧固件用于至少一个导管，该机身单元结构具有特别使用铝合金材料形成的大量增强元件。根据本发明，机身单元结构内的增强元件设置有至少一个凹槽，通过产生至少在某些区域中产生正配合的组合的压紧和夹紧配合，紧固件可以固定在该凹槽中。为此，紧固件在其下表面可以具有例如两个保持脚，其可以通过将固定元件驱动到槽中而分开并附接。增强元件是优选通过挤压和横杆制造的连续桁条，所需的凹槽在生产过程中同时挤出。

3. 发明授权

US08302312B2 Method for producing a fuselage airframe of an aircraft 有权
标题翻译：制造飞机机身机身的方法
公开(公告)号：US08302312B2
公开(公告)日：2012-11-06
申请号：US12721085
申请日：2010-03-10
申请人： Andreas Stephan
发明人： Andreas Stephan
IPC分类号： B21D53/88
CPC分类号： B64C1/068 , B64C2001/0072 , B64F5/10 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/49947 , Y10T29/49956
摘要： Disclosed is a method for producing a fuselage of an aircraft, wherein several fuselage sections that are arranged one behind another are joined together, comprises the following steps: a) production of an outer skin segment, the outer skin segment having on the underside a continuous longitudinal opening, b) widening the outer skin segment in order to introduce at least one floor frame, c) joining the outer skin segments to a rigid fuselage section which is already present, with the formation of a partial transverse seam, d) positioning a prefabricated lower shell in the longitudinal opening, in order to close the outer skin segment on the peripheral side, e) completing the partial transverse seam to form a transverse seam and joining the lower shell together with the outer skin segment with the formation of at least two longitudinal seams, and f) joining the floor frame together with the outer skin segment.
摘要翻译：本发明公开了一种飞机机身的制造方法，其特征在于，将一个彼此靠后配置的几个机身部分接合在一起，包括以下步骤：a）制造外皮段，所述外皮部分在下侧具有连续的纵向开口，b）加宽外皮段以便引入至少一个地板框架，c）将外皮段连接到已经存在的刚性机身部分，形成部分横向接缝，d）将在纵向开口中预制的下壳体，以便封闭外周侧的外皮段，e）完成部分横向接缝以形成横向接缝，并将下壳体与外皮段连接至少形成两个纵向接缝，以及f）将地板框架与外部皮肤部分连接。

4. 发明申请

US20110233334A1 STRUCTURE, ESPECIALLY A FUSELAGE STRUCTURE OF AN AIRCRAFT OR A SPACECRAFT 有权
标题翻译：结构，特别是飞机或空间的融合结构
公开(公告)号：US20110233334A1
公开(公告)日：2011-09-29
申请号：US12740880
申请日：2008-10-31
申请人： Andreas Stephan
发明人： Andreas Stephan
IPC分类号： B64C1/06
CPC分类号： B64C1/10
摘要： The present invention provides a fuselage structure (1; 1′) of an aircraft comprising an annular skin segment (2; 2′) which has a cross-sectional opening (3; 3′), a pressure cap (4; 4′) for a pressure-tight closure of the cross-sectional opening (3; 3′), and a plurality of tension struts (7, 8, 9; 7′, 8′, 9′) which in each case connect the pressure cap (4; 4′) to the annular skin segment (2; 2′) and absorb loads acting on the pressure cap (4; 4′), as tensile loads. This advantageously means that the tension struts (7, 8, 9; 7′, 8′, 9′) do not have to absorb substantially any bending moments. Consequently, the tension struts can be produced with a relatively small cross section, which entails a reduction in weight. Furthermore, it is possible to produce and mount tension struts (7, 8, 9; 7′, 8′, 9′) of this type in a simple manner.
摘要翻译：本发明提供一种飞行器的机身结构（1; 1'），其包括具有横截面开口（3; 3'），压力盖（4; 4'）的环形皮肤段（2; 2'），用于横截面开口（3; 3'）的压力密封，以及多个张力支柱（7,8,9; 7'，8'，9'），其在每种情况下连接压力盖（ 4; 4'）连接到环形皮肤部分（2; 2'）并吸收作用在压力帽（4; 4'）上的负载作为拉伸载荷。这有利地意味着张力支柱（7,8,9; 7'，8'，9'）不必基本上吸收任何弯曲力矩。因此，张力支柱可以以相对小的横截面产生，这需要减轻重量。此外，可以简单地制造和安装这种类型的张紧支柱（7,8,9，7'，8'，9'）。

5. 发明申请

US20100196733A1 Method for Producing a Composite Skin in the Field of Aeronautics and Astronautics 有权
标题翻译：在航空航天领域生产复合皮肤的方法
公开(公告)号：US20100196733A1
公开(公告)日：2010-08-05
申请号：US12602459
申请日：2008-05-15
申请人： Andreas Stephan
发明人： Andreas Stephan
IPC分类号： B32B15/01 , B23K31/02 , B23K20/12 , B23K15/00 , B23K26/20
CPC分类号： B23K26/24 , B21J15/00 , B21J15/142 , B23K15/0006 , B23K20/122 , B23K26/26 , B23K2101/18 , B23K2103/10 , B64C1/069 , B64C1/12 , Y02T50/43 , Y10T29/49966 , Y10T29/49968 , Y10T428/12
摘要： The present invention provides a composite skin for the aeronautics and astronautics industries, and also a method for producing a composite skin of this type. The method comprises the following method steps: removing excess material from a butt plate to form a butt strap at one end thereof, subsequently connecting the other end of the butt plate to a skin plate with a substance-to-substance bond, and then fastening a further skin plate to the butt strap to form the composite skin. The idea behind the invention involves replacing a rivet connection with a substance-to-substance bond. This provides the advantage that the weight of the composite skin and the production costs for the composite skin are reduced.
摘要翻译：本发明提供了一种用于航空和航天工业的复合皮肤，以及这种类型的复合皮肤的制造方法。该方法包括以下方法步骤：从对接板去除多余的材料以在其一端形成对接带，随后将对接板的另一端连接到具有物质 - 物质粘合的表皮板，然后紧固一个进一步的皮肤板到对接带形成复合皮肤。本发明的想法涉及用物质与物质之间的接合来更换铆钉连接。这提供了复合皮肤的重量和复合皮肤的生产成本降低的优点。

6. 发明申请

US20100192377A1 METHOD FOR PRODUCING A FUSELAGE AIRFRAME OF AN AIRCRAFT 有权
标题翻译：制造飞机的空调机的方法
公开(公告)号：US20100192377A1
公开(公告)日：2010-08-05
申请号：US12721085
申请日：2010-03-10
申请人： Andreas Stephan
发明人： Andreas Stephan
IPC分类号： B21D53/88
CPC分类号： B64C1/068 , B64C2001/0072 , B64F5/10 , Y02T50/43 , Y10T29/49616 , Y10T29/49622 , Y10T29/49947 , Y10T29/49956
摘要： Disclosed is a method for producing a fuselage of an aircraft, wherein several fuselage sections that are arranged one behind another are joined together, comprises the following steps: a) production of an outer skin segment, the outer skin segment having on the underside a continuous longitudinal opening, b) widening the outer skin segment in order to introduce at least one floor frame, c) joining the outer skin segments to a rigid fuselage section which is already present, with the formation of a partial transverse seam, d) positioning a prefabricated lower shell in the longitudinal opening, in order to close the outer skin segment on the peripheral side, e) completing the partial transverse seam to form a transverse seam and joining the lower shell together with the outer skin segment with the formation of at least two longitudinal seams, and f) joining the floor frame together with the outer skin segment.
摘要翻译：本发明公开了一种飞机机身的制造方法，其特征在于，将一个彼此靠后配置的几个机身部分接合在一起，包括以下步骤：a）制造外皮段，所述外皮部分在下侧具有连续的纵向开口，b）加宽外皮段以便引入至少一个地板框架，c）将外皮段连接到已经存在的刚性机身部分，形成部分横向接缝，d）将在纵向开口中预制的下壳体，以便封闭外周侧的外皮段，e）完成部分横向接缝以形成横向接缝，并将下壳体与外皮段连接至少形成两个纵向接缝，以及f）将地板框架与外部皮肤部分连接在一起。

7. 发明申请

US20080250772A1 Multi-stage apparatus for separating liquid droplets from gases 有权
标题翻译：用于从气体中分离液滴的多级装置
公开(公告)号：US20080250772A1
公开(公告)日：2008-10-16
申请号：US11783593
申请日：2007-04-10
申请人： Stefan Becker , Carsten Schippers , Wolfgang Heikamp , Tobias Neumann , Andreas Stephan , Jens Gutekunst , Peter Biebricher
发明人： Stefan Becker , Carsten Schippers , Wolfgang Heikamp , Tobias Neumann , Andreas Stephan , Jens Gutekunst , Peter Biebricher
IPC分类号： B01D46/00
CPC分类号： B01D50/002 , B01D45/06 , B01D45/16 , B01D46/003 , B01D46/0031 , B01D2267/40 , F04C29/026
摘要： Disclosed is a device for separating liquids from gases comprising a preseparator that separates an untreated gas region from a preseparator gas region, a main separator comprising a coalescing element for increasing the size of liquid droplets and a post-separator.
摘要翻译：公开了一种用于从气体中分离液体的装置，包括将未处理气体区域与预分离器气体区域分离的预分离器，包括用于增加液滴尺寸的聚结元件的主分离器和后分离器。

8. 发明授权

US08783610B2 Transverse splicing plate for creating a fuselage, and a method for connecting two, in particular wound, CFP fuselage sections 有权
标题翻译：用于创建机身的横向拼接板，以及用于连接两个特别是伤口的CFP机身部分的方法
公开(公告)号：US08783610B2
公开(公告)日：2014-07-22
申请号：US12740183
申请日：2008-10-30
申请人： Andreas Stephan
发明人： Andreas Stephan
IPC分类号： B64C1/06
CPC分类号： B64C1/069 , B64C2001/0072 , Y02T50/43 , Y10T29/49346 , Y10T29/49622
摘要： A transverse splicing plate for producing a fuselage of an aircraft by connecting several CFP fuselage sections that have in particular been produced in the winding method, in each case by forming a transverse seam, wherein the flexible transverse splicing plate is of a multilayer construction, in other words it comprises a multitude of plate segments arranged one above the other, wherein each of the plate segments comprises a multitude of longitudinal slits, each being able independently of each other to make small radial bending movements in order to cause tolerance compensation in radial direction between the fuselage sections to be joined, in which tolerance compensation a sliding movement between the sub-plates of the plate segments arranged one above the other takes place in axial direction of the barrel-shaped fuselage sections, and wherein on the inside the ends of the fuselage sections comprise chamfers; as well as a method for producing a connection between two CFP fuselage sections, which have preferably been produced in the winding method, by means of a transverse splicing plate according to the invention.
摘要翻译：一种横向拼接板，用于通过连接几个特别是以卷绕方式生产的CFP机身部分，在每种情况下通过形成横向接缝来生产飞机的机身，其中柔性横向拼接板是多层结构，换句话说，它包括一个彼此上下布置的多个板段，其中每个板段包括多个纵向狭缝，每个纵向狭缝彼此独立地进行小径向弯曲运动，以便在径向上进行公差补偿在要连接的机身部分之间，其中公差补偿在一个彼此上下布置的板段的子板之间的滑动运动沿着筒形机身部分的轴向方向发生，并且其中在内侧的机身部分包括倒角; 以及用于通过根据本发明的横向拼接板来生产优选以卷绕方法制造的两个CFP机身部分之间的连接的方法。

9. 发明授权

US08480030B2 Structural component and method for stiffening an external skin 有权
标题翻译：用于加固外部皮肤的结构部件和方法
公开(公告)号：US08480030B2
公开(公告)日：2013-07-09
申请号：US12678732
申请日：2008-06-10
申请人： Andreas Stephan
发明人： Andreas Stephan
IPC分类号： B64C1/00
CPC分类号： B64C1/12 , Y10T29/49622
摘要： The present invention provides a structural component for an aircraft or a space craft having an outer skin and a first reinforcing element which runs on the outer skin along a first spatial direction. A second reinforcing element runs over the first reinforcing element in a second spatial direction. A foot element supports the second reinforcing element on the outer skin, the foot element having a feed-through opening in which the first reinforcing element is held in a positive manner. From another point of view, a method is provided for reinforcing an outer skin of an aircraft or space craft, in which a first reinforcing element is attached to the outer skin along a first spatial direction. A foot element having a feed-through opening is attached over the first reinforcing element such that the first reinforcing element is held positively in the feed-through opening. A second reinforcing element is attached to the foot element in a second spatial direction over the first reinforcing element.
摘要翻译：本发明提供一种用于飞机或航天飞机的结构部件，其具有外皮和沿着第一空间方向在外皮上延伸的第一加强元件。第二增强元件在第二空间方向上延伸超过第一加强元件。脚部元件支撑外皮上的第二加强元件，脚元件具有馈通开口，第一加强元件以正向方式保持在该通孔中。从另一观点出发，提供了一种用于加强飞行器或太空飞船的外皮的方法，其中第一加强元件沿着第一空间方向附接到外皮。具有馈通开口的脚元件附接在第一加强元件上，使得第一加强元件被正确地保持在馈通开口中。第二增强元件在第一增强元件上的第二空间方向上附接到脚元件。

10. 发明申请

US20100252684A1 FUSELAGE CELL STRUCTURE OF AN AIRPLANE FOR THE SIMPLIFIED INSTALLATION AND ATTACHMENT OF FASTENERS FOR FASTENING CONDUITS 有权
标题翻译：用于简化安装和紧固紧固件的空气调节装置的空调机构结构
公开(公告)号：US20100252684A1
公开(公告)日：2010-10-07
申请号：US12763796
申请日：2010-04-20
申请人： Andreas Stephan
发明人： Andreas Stephan
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C1/406 , F16L3/02 , F16L3/24 , H02G3/26 , H02G3/32
摘要： The invention relates to a fuselage cell structure of an aircraft for the simplified installation and attachment of at least one fastener for at least one conduit, the fuselage cell structure having a large number of reinforcing elements formed in particular using an aluminium alloy material. According to the invention, the reinforcing elements within the fuselage cell structure are provided with at least one groove in which the fasteners can be secured by producing a combined pressing and clamping fit creating a positive fit at least in certain regions. For this purpose, the fasteners can have at the lower face thereof, for example, two retaining feet which can be spread apart and attached by driving a fixing element into the groove. The reinforcing elements are continuous stringers preferably produced by extrusion and cross-bars, the required grooves being simultaneously extruded during the production process.
摘要翻译：本发明涉及飞行器的机身单元结构，用于简化安装和附接至少一个紧固件用于至少一个导管，该机身单元结构具有特别使用铝合金材料形成的大量增强元件。根据本发明，机身单元结构内的增强元件设置有至少一个凹槽，通过产生至少在某些区域中产生正配合的组合的压紧和夹紧配合，紧固件可以固定在该凹槽中。为此，紧固件在其下表面可以具有例如两个保持脚，其可以通过将固定元件驱动到槽中而分开并附接。增强元件是优选通过挤压和横杆制造的连续桁条，所需的凹槽在生产过程中同时挤出。

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