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1. 发明申请

US20120104170A1 FUSELAGE ELEMENT COMPRISING A FUSELAGE SEGMENT AND JOINING MEANS 有权
标题翻译：包含熔接部分和接合装置的熔接元件
公开(公告)号：US20120104170A1
公开(公告)日：2012-05-03
申请号：US13381673
申请日：2010-07-02
申请人： Guillaume Gallant , Romain Delahaye , Marc Dugerie , Marc-Antoine Castanet
发明人： Guillaume Gallant , Romain Delahaye , Marc Dugerie , Marc-Antoine Castanet
IPC分类号： B64C1/12 , B64C1/06
CPC分类号： B64C1/061 , B64C1/064 , B64C1/068 , B64C1/12
摘要： The invention relates to a fuselage element comprising a fuselage segment (1a) comprising a skin (3a), and junction means (6) for connecting the skin of said segment (1a) to an adjacent segment (1b). The segment (1a) extends along the longitudinal axis (X) of the fuselage, and the skin (3) includes at least one first section (10) at least one end of said segment (1a). The fuselage segment (1a) comprises at least one longitudinal stiffening element (5a) for the fuselage. The junction means (60) are arranged so as to contact an outer surface (30) of said first section (10) of the skin (3a), and the stiffening element (5a) partially extends at the junction means (6) along the longitudinal axis (X).
摘要翻译：本发明涉及一种机身元件，它包括一个包括皮肤（3a）的机身段（1a）和用于将所述段（1a）的皮肤连接到相邻区段（1b）的接合装置（6）。所述片段（1a）沿着所述机身的纵向轴线（X）延伸，并且所述皮肤（3）包括所述片段（1a）的至少一个端部中的至少一个第一部分（10）。机体段（1a）包括用于机身的至少一个纵向加强元件（5a）。接合装置（60）布置成接触皮肤（3a）的所述第一部分（10）的外表面（30），并且加强元件（5a）沿着连接装置（6）部分地延伸纵轴（X）。

2. 发明授权

US09371125B2 Fuselage element comprising a fuselage segment and joining means 有权
标题翻译：机身元件包括机身段和接合装置
公开(公告)号：US09371125B2
公开(公告)日：2016-06-21
申请号：US13381673
申请日：2010-07-02
申请人： Guillaume Gallant , Romain Delahaye , Marc Dugerie , Marc-Antoine Castanet
发明人： Guillaume Gallant , Romain Delahaye , Marc Dugerie , Marc-Antoine Castanet
IPC分类号： B64C1/12 , B64C1/06
CPC分类号： B64C1/061 , B64C1/064 , B64C1/068 , B64C1/12
摘要： A fuselage element including a fuselage segment including a skin and a junction means for connecting the skin to an adjacent fuselage segment. The fuselage segment extends along a longitudinal axis of the fuselage, and the skin includes a first section at at least one end of the fuselage segment. The fuselage segment includes at least one longitudinal stiffening element for the fuselage. A junction member is arranged so as to contact an outer surface of the first section of the skin, and the stiffening element partially extends to the junction member along the longitudinal axis.
摘要翻译：一种机身元件，包括包括皮肤的机身段和用于将皮肤连接到相邻的机身段的接合装置。机身段沿着机身的纵向轴线延伸，并且皮肤包括在机身段的至少一端的第一部分。机身部分包括用于机身的至少一个纵向加强元件。接合构件布置成接触皮肤的第一部分的外表面，并且加强元件沿着纵向轴线部分地延伸到接合构件。

3. 发明授权

US09067670B2 Frame for an opening provided in an aircraft fuselage 有权
标题翻译：在飞机机身上提供的开口的框架
公开(公告)号：US09067670B2
公开(公告)日：2015-06-30
申请号：US13380704
申请日：2010-06-25
申请人： Marc Dugerie , Guillaume Gallant , Romain Delahaye
发明人： Marc Dugerie , Guillaume Gallant , Romain Delahaye
IPC分类号： B64C1/00 , B64C1/14
CPC分类号： B64C1/1461
摘要： A door frame is provided at an opening made in a fuselage of an aircraft that is delimited by a skin. The frame includes an upper longitudinal stiffener and a lower longitudinal stiffener and two vertical substructures, each arranged on one side of the opening, connected by the upper and lower longitudinal stiffeners. The frame also comprises at least one stop provided at the level of the opening that uptakes radial forces exerted by the door. Each vertical substructure comprises at least three walls made of composite material that are connected to one another to form a box substructure having a closed and hollow cross-section in a sectional plane perpendicular to an axis of the length of the vertical substructure.
摘要翻译：在由皮肤划分的飞机的机体中形成的开口处设置有门框。框架包括上部纵向加强件和下部纵向加强件以及两个垂直子结构，每个垂直子结构均布置在开口的一侧，并由上部和下部纵向加强件连接。框架还包括设置在开口水平面上的至少一个止挡件，其吸收由门施加的径向力。每个垂直子结构包括由复合材料制成的至少三个壁，它们彼此连接以形成在垂直于垂直子结构的长度的轴线的截面中具有闭合且中空横截面的箱子结构。

4. 发明申请

US20120211602A1 FRAME FOR AN OPENING PROVIDED IN AN AIRCRAFT FUSELAGE 有权
标题翻译：在航空器熔接中提供的开放的框架
公开(公告)号：US20120211602A1
公开(公告)日：2012-08-23
申请号：US13380704
申请日：2010-06-25
申请人： Marc Dugerie , Guillaume Gallant , Romain Delahaye
发明人： Marc Dugerie , Guillaume Gallant , Romain Delahaye
IPC分类号： B64C1/14
CPC分类号： B64C1/1461
摘要： A frame of a door that is provided at an opening made in a fuselage of an aircraft that is delimited by a skin, whereby the frame that includes an upper longitudinal stiffener and a lower longitudinal stiffener provides the connection between two vertical substructures (62) that are arranged on both sides of the opening, at the level of which (5) there is provided at least one stop (56) that provides the uptake of radial forces exerted by the door, characterized in that each vertical substructure (62) includes at least three walls made of composite material that are connected to one another to form a closed and hollow profile in such a way as to obtain a box structure.
摘要翻译：设置在由皮肤划分的飞机的机身的开口处的门的框架，由此包括上纵向加强件和下纵向加强件的框架提供两个垂直子结构（62）之间的连接，布置在开口的两侧，在其水平处（5）设置有提供由门施加的径向力的吸收的至少一个止挡（56），其特征在于，每个垂直子结构（62）包括在由复合材料制成的至少三个壁，其彼此连接以形成封闭且中空的轮廓，以获得盒结构。

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