公开(公告)号：US20100230539A1

公开(公告)日：2010-09-16

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。

公开(公告)号：US20100320322A1

公开(公告)日：2010-12-23

申请号：US12735799

申请日：2009-02-16

申请人： Volker Reye ,  Stefan Tacke ,  Stephan Mischereit

发明人： Volker Reye ,  Stefan Tacke ,  Stephan Mischereit

IPC分类号： B64C1/00 ,  B23P11/00

CPC分类号： B64C1/069 ,  B64C1/06 ,  B64C2001/0072 ,  B64C2211/00 ,  Y02T50/43 ,  Y10T29/49826

摘要： 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).

摘要翻译： 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：US08444090B2

公开(公告)日：2013-05-21

申请号：US12735799

申请日：2009-02-16

申请人： Volker Reye ,  Stefan Tacke ,  Stephan Mischereit

发明人： Volker Reye ,  Stefan Tacke ,  Stephan Mischereit

IPC分类号： B64C1/06

CPC分类号： B64C1/069 ,  B64C1/06 ,  B64C2001/0072 ,  B64C2211/00 ,  Y02T50/43 ,  Y10T29/49826

摘要： 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.

摘要翻译： 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：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。