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1. 发明授权

US09371126B2 Aircraft fuselage 有权
标题翻译：飞机机身
公开(公告)号：US09371126B2
公开(公告)日：2016-06-21
申请号：US14095040
申请日：2013-12-03
申请人： Airbus Operations GmbH , EADS Deutschland GmbH
发明人： Markus Siemetzki , Brian Bautz , Lars Margull , Matthias Waimer , Tim Bergmann , Sebastian Heimbs , Paul Schatrow
IPC分类号： B64C1/06
CPC分类号： B64C1/062
摘要： An aircraft fuselage including an outer skin that is stiffened by way of a backing structure and that delimits at least one passenger cabin and one cargo hold. In the vertical direction of the fuselage, the cargo hold is arranged below the passenger cabin. The backing structure in the cargo hold above a cargo-hold floor framework comprises at least two lateral quasi-joints, and below the cargo-hold floor framework comprises at least one further quasi-joint. In the cargo hold, in the longitudinal direction of the fuselage, a multitude of energy absorption devices, arranged one behind the other and acting in the transverse direction of the fuselage, are arranged for absorbing tensile loads.
摘要翻译：飞机机身包括通过背衬结构加固的外皮，并限定至少一个客舱和一个货舱。在机身的垂直方向上，货舱位于客舱的下方。在货舱底板框架上方的货舱中的支撑结构包括至少两个横向准接头，并且在货舱底板框架下方包括至少一个另外的准关节。在货舱中，沿着机身的纵向方向，布置有大量能量吸收装置，其排列成彼此并且沿机身的横向方向作用，以吸收拉伸载荷。

2. 发明申请

US20150151828A1 Aircraft Fuselage 有权
标题翻译：飞机机身
公开(公告)号：US20150151828A1
公开(公告)日：2015-06-04
申请号：US14095040
申请日：2013-12-03
申请人： EADS Deutschland GmbH , Airbus Operations GmbH
发明人： Markus Siemetzki , Brian Bautz , Lars Margull , Matthias Waimer , Tim Bergmann , Sebastian Heimbs , Paul Schatrow
IPC分类号： B64C1/06
CPC分类号： B64C1/062
摘要： An aircraft fuselage including an outer skin that is stiffened by way of a backing structure and that delimits at least one passenger cabin and one cargo hold. In the vertical direction of the fuselage, the cargo hold is arranged below the passenger cabin. The backing structure in the cargo hold above a cargo-hold floor framework comprises at least two lateral quasi-joints, and below the cargo-hold floor framework comprises at least one further quasi-joint. In the cargo hold, in the longitudinal direction of the fuselage, a multitude of energy absorption devices, arranged one behind the other and acting in the transverse direction of the fuselage, are arranged for absorbing tensile loads.
摘要翻译：飞机机身包括通过背衬结构加固的外皮，并限定至少一个客舱和一个货舱。在机身的垂直方向上，货舱位于客舱的下方。在货舱底板框架上方的货舱中的支撑结构包括至少两个横向准接头，并且在货舱底板框架下方包括至少一个另外的准关节。在货舱中，沿着机身的纵向方向，布置有大量能量吸收装置，其排列成彼此并且沿机身的横向方向作用，以吸收拉伸载荷。

3. 发明授权

US09493224B2 Connection arrangement and structure 有权
标题翻译：连接布置和结构
公开(公告)号：US09493224B2
公开(公告)日：2016-11-15
申请号：US14555618
申请日：2014-11-27
申请人： Airbus Operations GmbH
发明人： Dieter Hachenberg , Lars Margull , Dieter Kohlgrueber , Matthias Waimer , Harald Kraft
IPC分类号： B64C1/06 , B64C1/18 , F16F7/08 , F16F7/12
CPC分类号： B64C1/062 , B64C1/18 , F16F7/08 , F16F7/124 , F16F7/127
摘要： An energy-absorbing connection arrangement with a multitude of connectors for joining two components, such as a transverse member and a circular frame element, of an aircraft fuselage. Each connector comprises a headed shaft and the shafts reach through component boreholes. On the shaft ends facing away from the heads, counter-bearings are provided. At least one of the components comprises a fiber-reinforced plastic material. A head and/or counter-bearing of at least one connector rests against at least one underlay device. The underlay device is received in a guide groove in the first component, with the guide groove commencing in the region of the boreholes. The underlay device, upon exceeding a mechanical threshold load, is slidable away from the boreholes. Energy absorption takes place along a longitudinal center axis of the guide groove as a result of hole-bearing-stress failure and/or the shearing of the fiber-reinforced plastic material component.
摘要翻译：一种能量吸收连接装置，其具有用于连接飞行器机身的两个部件（例如横向部件和圆形框架部件）的多个连接器。每个连接器包括头轴，并且轴穿过部件钻孔。在远离头部的轴端上，设有反作用轴承。至少一个部件包括纤维增强塑料材料。至少一个连接器的头部和/或反向轴承抵靠至少一个底垫装置。底垫装置被容纳在第一部件中的引导槽中，导向槽从钻孔区域开始。超过机械阈值负载时，底垫装置可以从钻孔中滑动。由于孔承载应力破坏和/或纤维增强塑料材料部件的剪切，能量吸收沿引导槽的纵向中心轴线发生。

4. 发明申请

US20150151829A1 CONNECTION ARRANGEMENT AND STRUCTURE 有权
标题翻译：连接安排和结构
公开(公告)号：US20150151829A1
公开(公告)日：2015-06-04
申请号：US14555618
申请日：2014-11-27
申请人： Airbus Operations GmbH
发明人： Dieter Hachenberg , Lars Margull , Dieter Kohlgrueber , Matthias Waimer , Harald Kraft
IPC分类号： B64C1/06
CPC分类号： B64C1/062 , B64C1/18 , F16F7/08 , F16F7/124 , F16F7/127
摘要： An energy-absorbing connection arrangement with a multitude of connectors for joining two components, such as a transverse member and a circular frame element, of an aircraft fuselage. Each connector comprises a headed shaft and the shafts reach through component boreholes. On the shaft ends facing away from the heads, counter-bearings are provided. At least one of the components comprises a fiber-reinforced plastic material. A head and/or counter-bearing of at least one connector rests against at least one underlay device. The underlay device is received in a guide groove in the first component, with the guide groove commencing in the region of the boreholes. The underlay device, upon exceeding a mechanical threshold load, is slidable away from the boreholes. Energy absorption takes place along a longitudinal center axis of the guide groove as a result of hole-bearing-stress failure and/or the shearing of the fiber-reinforced plastic material component.
摘要翻译：一种能量吸收连接装置，其具有用于连接飞行器机身的两个部件（例如横向部件和圆形框架部件）的多个连接器。每个连接器包括头轴，并且轴穿过部件钻孔。在远离头部的轴端上，设有反作用轴承。至少一个部件包括纤维增强塑料材料。至少一个连接器的头部和/或反向轴承抵靠至少一个底垫装置。底垫装置被容纳在第一部件中的引导槽中，导向槽从钻孔区域开始。超过机械阈值负载时，底垫装置可以从钻孔中滑动。由于孔承载应力破坏和/或纤维增强塑料材料部件的剪切，能量吸收沿引导槽的纵向中心轴线发生。

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