公开(公告)号：US07846242B2

公开(公告)日：2010-12-07

申请号：US10554922

申请日：2004-05-19

Applicant: Mark Paling ,  Andrew G. L. Blackwood ,  Ignitius Milomo ,  Stephan Niemeyer ,  Christian Fischer ,  Andreas Stephan

Inventor： Mark Paling ,  Andrew G. L. Blackwood ,  Ignitius Milomo ,  Stephan Niemeyer ,  Christian Fischer ,  Andreas Stephan

IPC: B01D53/02

CPC classification number: B01D53/261 ,  B01D2201/291 ,  B60T17/004 ,  Y10S55/17

Abstract: An air dryer desiccant cartridge, the cartridge comprising a base having an inlet and an outlet, and a casing connected to the base to define a cavity there between, wherein the cavity contains a filter and a desiccant, the filter being arranged upstream of the desiccant such that during normal operation fluid flow entering the cartridge through the inlet passes through the filter and then on to the desiccant before reaching the outlet, and during purging of the cartridge purge flow entering the outlet passes through the desiccant before reaching the filter, wherein further the cartridge includes a valve operable to permit a portion of the purge flow to bypass the filter.

Abstract translation: 一种空气干燥剂干燥剂盒，所述盒包括具有入口和出口的底座，以及连接到所述基座以在其间限定空腔的壳体，其中所述空腔包含过滤器和干燥剂，所述过滤器布置在所述干燥剂的上游 使得在正常操作期间，通过入口进入料筒的流体流动通过过滤器，然后在到达出口之前进入干燥剂，并且在吹扫进入出口的料筒清洗流程在到达过滤器之前通过干燥剂，其中进一步 该墨盒包括可操作以允许清洗流的一部分绕过过滤器的阀。

公开(公告)号：US20080292849A1

公开(公告)日：2008-11-27

申请号：US12126173

申请日：2008-05-23

Applicant: Andreas Stephan

Inventor： Andreas Stephan

IPC: B32B15/00

CPC classification number: B64C1/12 ,  B29C70/86 ,  B29K2705/00 ,  B29K2705/02 ,  B29L2031/3002 ,  B32B3/02 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T428/195 ,  Y10T428/24752 ,  Y10T428/24777

Abstract: A laminate sheet, in particular for use as a fuselage skin includes thin aluminium alloy sheets layered on top of one another with each two aluminium alloy sheets being adhesively bonded to one another at least in regions by an adhesive layer which includes at least one unidirectional fibreglass insert impregnated with a curable synthetic resin.

Abstract translation: 特别是用作机身皮肤的层压片包括层压在彼此之上的薄铝合金薄片，每个两个铝合金薄片至少在区域中通过粘合剂层粘合地粘合在一起，所述粘合剂层包括至少一个单向玻璃纤维 插入物用可固化合成树脂浸渍。

公开(公告)号：US08783610B2

公开(公告)日：2014-07-22

申请号：US12740183

申请日：2008-10-30

Applicant: Andreas Stephan

Inventor： Andreas Stephan

IPC: B64C1/06

CPC classification number: B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49346 ,  Y10T29/49622

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US08480030B2

公开(公告)日：2013-07-09

申请号：US12678732

申请日：2008-06-10

Applicant: Andreas Stephan

Inventor： Andreas Stephan

IPC: B64C1/00

CPC classification number: B64C1/12 ,  Y10T29/49622

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20100252684A1

公开(公告)日：2010-10-07

申请号：US12763796

申请日：2010-04-20

Applicant: Andreas Stephan

Inventor： Andreas Stephan

IPC: B64C1/06

CPC classification number: B64C1/064 ,  B64C1/406 ,  F16L3/02 ,  F16L3/24 ,  H02G3/26 ,  H02G3/32

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US07531018B2

公开(公告)日：2009-05-12

申请号：US11783592

申请日：2007-04-10

Applicant: Stefan Becker ,  Carsten Schippers ,  Wolfgang Heikamp ,  Tobias Neumann ,  Andreas Stephan

Inventor： Stefan Becker ,  Carsten Schippers ,  Wolfgang Heikamp ,  Tobias Neumann ,  Andreas Stephan

IPC: B01D46/00

CPC classification number: B01D46/2411 ,  B01D45/08 ,  B01D45/16 ,  B01D46/0031 ,  Y10S55/17

Abstract: An air deoiling element with a drainage line for discharging the separated liquids, in which the drainage line is integrally mounted to a support member.

Abstract translation: 具有用于排出分离液体的排水管的排气元件，其中排放管线一体地安装到支撑构件上。

公开(公告)号：US07183043B2

公开(公告)日：2007-02-27

申请号：US10344710

申请日：2001-08-14

Applicant: Jan Meijer ,  Andreas Stephan ,  Ulf Weidenmuller ,  Ivo Rangelow

Inventor： Jan Meijer ,  Andreas Stephan ,  Ulf Weidenmuller ,  Ivo Rangelow

IPC: G03F1/00 ,  G03C5/00

CPC classification number: G03F1/20

Abstract: The disclosed device is directed towards a shadow mask for ion beams comprising a silicon wafer with a hole pattern arranged therein, wherein the silicon wafer is provided at a side confronting the incident ion beams with a metallic coating which stops the ion beams and dissipates heat, wherein an apertured region of the silicon wafer has a thickness from about 20 μm to about 200 μm and apertures in the shadow mask have lateral dimensions from about 0.5 μm to about 3 μm.

Abstract translation: 所公开的装置指向用于离子束的阴影掩模，所述阴影掩模包含布置在其中的孔图案的硅晶片，其中所述硅晶片设置在与入射离子束相对的一侧，金属涂层停止所述离子束并散发热量， 其中硅晶片的有孔区域具有约20μm至约200μm的厚度，并且荫罩中的孔径具有约0.5μm至约3μm的横向尺寸。

公开(公告)号：US08408496B2

公开(公告)日：2013-04-02

申请号：US12763796

申请日：2010-04-20

Applicant: Andreas Stephan

Inventor： Andreas Stephan

IPC: F16B2/04

CPC classification number: B64C1/064 ,  B64C1/406 ,  F16L3/02 ,  F16L3/24 ,  H02G3/26 ,  H02G3/32

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US08302312B2

公开(公告)日：2012-11-06

申请号：US12721085

申请日：2010-03-10

Applicant: Andreas Stephan

Inventor： Andreas Stephan

IPC: B21D53/88

CPC classification number: B64C1/068 ,  B64C2001/0072 ,  B64F5/10 ,  Y02T50/43 ,  Y10T29/49616 ,  Y10T29/49622 ,  Y10T29/49947 ,  Y10T29/49956

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20110233334A1

公开(公告)日：2011-09-29

申请号：US12740880

申请日：2008-10-31

Applicant: Andreas Stephan

Inventor： Andreas Stephan

IPC: B64C1/06

CPC classification number: B64C1/10

Abstract: 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.

Abstract translation: 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'）。