公开(公告)号：US07875333B2

公开(公告)日：2011-01-25

申请号：US12126173

申请日：2008-05-23

Applicant: Andreas Stephan

Inventor： Andreas Stephan

IPC: B32B3/10

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：US20100237195A1

公开(公告)日：2010-09-23

申请号：US12678732

申请日：2008-06-10

Applicant: Andreas Stephan

Inventor： Andreas Stephan

IPC: B64C1/12 ,  B21D53/88

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：US20100237194A1

公开(公告)日：2010-09-23

申请号：US12740183

申请日：2008-10-30

Applicant: Andreas Stephan

Inventor： Andreas Stephan

IPC: B64C1/06 ,  B21D53/88

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行器的机身，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。