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1. 发明授权

US11377189B2 Aircraft fuselage structure having a grid-stiffened panel 有权
公开(公告)号：US11377189B2
公开(公告)日：2022-07-05
申请号：US16715391
申请日：2019-12-16
申请人： Airbus Operations SAS , Airbus Operations GmbH
发明人： Christophe Mialhe , Andreas Dresel
IPC分类号： B64C1/06 , B64F5/10 , B21D53/92 , B64C1/12
摘要： A structure for an aircraft fuselage, the structure comprising a skin having an outer face and an inner face machined as a grid-stiffened panel, a plurality of frames, each frame shaped as the cross section of the fuselage and the frames being arranged one after the other along a longitudinal direction of the fuselage. The outer perimeter of each frame is secured to the inner face, a plurality of stringers extend parallel to the longitudinal direction, each stringer extending across multiple frames, passing through these at an opening provided to that end in each frame, and each stringer is pressed against the inner face and secured thereto. In the upper part and in the lower part of the fuselage, a torsion box is provided extending parallel to the longitudinal direction, each torsion box comprising a horizontal plate and tabs which secure the plate to the inner face.

2. 发明授权

US09213097B2 Aircraft comprising an onboard weather radar antenna provided with inclined panels 有权
标题翻译：飞机包括一个装有倾斜面板的车载天气雷达天线
公开(公告)号：US09213097B2
公开(公告)日：2015-12-15
申请号：US14099531
申请日：2013-12-06
申请人： Airbus Operations (SAS)
发明人： Christophe Mialhe
IPC分类号： G01S13/95 , H01Q1/42 , B64C1/36 , H01Q1/28 , H01Q21/20 , G01S13/42
CPC分类号： G01S13/953 , B64C1/36 , G01S13/426 , G01S13/95 , H01Q1/28 , H01Q1/281 , H01Q1/42 , H01Q21/20 , Y02A90/18
摘要： An aircraft comprising a fuselage and a radome fixed to the fuselage. The radome defines a housing and the fuselage comprises a sealed bulkhead closing the housing. A weather radar antenna comprises a main panel. A plurality of peripheral panels are arranged around the main panel, inclined from a planar surface of the main panel and located on the same side of the planar surface. The housing contains the antenna which is mounted on the fuselage through a mechanical support fixed to the fuselage and to the weather radar antenna on the same side of the planar surface as the peripheral panels. A bird strike shield is located between the antenna and the sealed bulkhead. The shield comprises a dome with a top and a base, the base being fixed to the aircraft fuselage. An opening is formed at the top of the dome through which the mechanical support passes.
摘要翻译：飞机包括机身和固定在机身上的天线罩。天线罩限定一个外壳，机身包括一个封闭外壳的密封隔板。天气雷达天线包括主面板。多个外围板围绕主面板设置，从主面板的平面倾斜并且位于平面的同一侧。外壳包含通过机械支撑件安装在机身上的天线，机械支撑件固定在机身上，天线雷达天线与外围面板在平面表面的同一侧。天线和密封舱壁之间设有一个鸟击屏蔽。屏蔽包括具有顶部和底部的圆顶，该基座固定在飞行器机身上。开口形成在穹顶的顶部，机械支撑穿过该顶部。

3. 发明申请

US20150321742A1 STIFFENER FOR AN AIRCRAFT FUSELAGE, METHOD FOR MANUFACTURING SAME, AND AIRCRAFT FUSELAGE EQUIPPED WITH SUCH A STIFFENER 有权
标题翻译：用于制造飞机的冲击器，其制造方法和装备有这种加速器的飞机配件
公开(公告)号：US20150321742A1
公开(公告)日：2015-11-12
申请号：US14652118
申请日：2013-12-20
申请人： AIRBUS OPERATIONS (SAS)
发明人： Christophe Mialhe , Romain Delahaye , Philipe Rodrigo
IPC分类号： B64C1/06 , B21D53/92 , B21D5/16
CPC分类号： B64C1/06 , B21D5/16 , B21D53/92 , B64C1/061 , B64C1/12
摘要： This stiffener is intended for a fuselage. It comprises a hollow section that can be trapezoidal, with a base attached to the fuselage or to the floor, high enough rising sides and a top side contributing to the rigidity and cohesion of the stiffener. A direct assembly with the fuselage is possible. The base is made of two edges provided one on the other or in front of the other. This rigid stiffener, in spite of its discontinuous section, can be manufactured by simple foldings of a planar metal sheet at the beginning.
摘要翻译：这种加强筋适用于机身。它包括可以是梯形的中空部分，其底部附接到机身或地板，足够高的上升侧和顶侧有助于加强件的刚性和内聚力。与机身直接组装是可能的。基座由另一个或另一个前面提供的两个边缘组成。该刚性加强件尽管具有不连续的截面，但可以通过平面金属板在开始时的简单折叠来制造。

4. 发明申请

US20140159949A1 AIRCRAFT COMPRISING AN ONBOARD WEATHER RADAR ANTENNA PROVIDED WITH INCLINED PANELS 有权
标题翻译：包含天花板天线的航空器提供有内置的面板
公开(公告)号：US20140159949A1
公开(公告)日：2014-06-12
申请号：US14099531
申请日：2013-12-06
申请人： Airbus Operations (SAS)
发明人： Christophe Mialhe
IPC分类号： G01S13/95
CPC分类号： G01S13/953 , B64C1/36 , G01S13/426 , G01S13/95 , H01Q1/28 , H01Q1/281 , H01Q1/42 , H01Q21/20 , Y02A90/18
摘要： An aircraft comprising a fuselage and a radome fixed to the fuselage. The radome defines a housing and the fuselage comprises a sealed bulkhead closing the housing. A weather radar antenna comprises a main panel. A plurality of peripheral panels are arranged around the main panel, inclined from a planar surface of the main panel and located on the same side of the planar surface. The housing contains the antenna which is mounted on the fuselage through a mechanical support fixed to the fuselage and to the weather radar antenna on the same side of the planar surface as the peripheral panels. A bird strike shield is located between the antenna and the sealed bulkhead. The shield comprises a dome with a top and a base, the base being fixed to the aircraft fuselage. An opening is formed at the top of the dome through which the mechanical support passes.
摘要翻译：飞机包括机身和固定在机身上的天线罩。天线罩限定一个外壳，机身包括一个封闭外壳的密封隔板。天气雷达天线包括主面板。多个外围板围绕主面板设置，从主面板的平面倾斜并且位于平面的同一侧。外壳包含通过机械支撑件安装在机身上的天线，机械支撑件固定在机身上，天线雷达天线与外围面板在平面表面的同一侧。天线和密封舱壁之间设有一个鸟击屏蔽。屏蔽包括具有顶部和底部的圆顶，该基座固定在飞行器机身上。开口形成在穹顶的顶部，机械支撑穿过该顶部。

5. 发明授权

US11407487B2 Unitary aircraft windshield with conical single curvature 有权
公开(公告)号：US11407487B2
公开(公告)日：2022-08-09
申请号：US16953832
申请日：2020-11-20
申请人： Airbus Operations SAS
发明人： Patrick Lieven , Christophe Mialhe , Jérôme Phalippou
IPC分类号： B64C1/14 , B64C1/00
摘要： A windshield for an aircraft cockpit is provided which includes a glazed windshield part which has a single curvature corresponding to a portion of the envelope of a cone extending between a lower plane and an upper plane which intersect an axis of the cone. The single curvature of the glazed part of the windshield enables the glazed part to be produced more easily, for example by rolling or by hydroforming. It also makes it possible to create configurations for a cockpit for two pilots, a single pilot or even no pilot, on the basis of a single aerodynamic shape of the fuselage of the aircraft by only adapting the structure of the windshield. Also provided are a windshield frame for such a windshield, a windshield assembly including such a windshield frame and such a windshield, and an aircraft equipped with such a windshield.

6. 发明授权

US09708050B2 Stiffener for an aircraft fuselage, method for manufacturing same, and aircraft fuselage equipped with such a stiffener 有权
公开(公告)号：US09708050B2
公开(公告)日：2017-07-18
申请号：US14652118
申请日：2013-12-20
申请人： Airbus Operations (SAS)
发明人： Christophe Mialhe , Romain Delahaye , Philipe Rodrigo
IPC分类号： B64C1/06 , B21D5/16 , B21D53/92 , B64C1/12
CPC分类号： B64C1/06 , B21D5/16 , B21D53/92 , B64C1/061 , B64C1/12
摘要： This stiffener is intended for a fuselage. It comprises a hollow section that can be trapezoidal, with a base attached to the fuselage or to the floor, high enough rising sides and a top side contributing to the rigidity and cohesion of the stiffener. A direct assembly with the fuselage is possible. The base is made of two edges provided one on the other or in front of the other. This rigid stiffener, in spite of its discontinuous section, can be manufactured by simple foldings of a planar metal sheet at the beginning.

7. 发明授权

US09856015B2 Rudder bar for an aircraft 有权
公开(公告)号：US09856015B2
公开(公告)日：2018-01-02
申请号：US14961349
申请日：2015-12-07
申请人： Airbus Operations (SAS)
发明人： Laurent Saint-Marc , Christophe Mialhe , Patrick Lieven , Romain Delahaye , Marc Audibert , Nicolas Chatrenet
IPC分类号： B64C19/02 , B64C13/04 , B64C13/06 , G05G1/30
CPC分类号： B64C13/04 , B64C13/06 , G05G1/30
摘要： A rudder bar for an aircraft comprising a floor, a steering connecting rod and a braking connecting rod. The rudder bar comprises a base fixed above the floor, a pedal arm mounted rotatably on the base about a first axis of rotation and having a lower end and an upper end, a pedal mounted rotatably on the lower end about a second axis of rotation, a first transmission assembly configured to transmit a movement to the steering connecting rod when the pedal arm pivots about the first axis of rotation, and a second transmission assembly configured to transmit a movement to the braking connecting rod when the pedal pivots about the second axis of rotation.

8. 发明申请

US20160159457A1 RUDDER BAR FOR AN AIRCRAFT 有权
公开(公告)号：US20160159457A1
公开(公告)日：2016-06-09
申请号：US14961349
申请日：2015-12-07
申请人： Airbus Operations (SAS)
发明人： Laurent Saint-Marc , Christophe Mialhe , Patrick Lieven , Romain Delahaye , Marc Audibert , Nicolas Chatrenet
IPC分类号： B64C9/02
CPC分类号： B64C13/04 , B64C13/06 , G05G1/30
摘要： A rudder bar for an aircraft comprising a floor, a steering connecting rod and a braking connecting rod. The rudder bar comprises a base fixed above the floor, a pedal arm mounted rotatably on the base about a first axis of rotation and having a lower end and an upper end, a pedal mounted rotatably on the lower end about a second axis of rotation, a first transmission assembly configured to transmit a movement to the steering connecting rod when the pedal arm pivots about the first axis of rotation, and a second transmission assembly configured to transmit a movement to the braking connecting rod when the pedal pivots about the second axis of rotation.
摘要翻译：用于飞机的舵杆，包括地板，转向连杆和制动连杆。方向舵杆包括固定在地板上方的底座，踏板臂，其围绕第一旋转轴线可旋转地安装在基座上，并具有下端和上端，踏板围绕第二旋转轴线可旋转地安装在下端上，第一传动组件，其构造成当踏板臂围绕第一旋转轴线枢转时将运动传递到转向连杆;以及第二传动组件，其构造成当踏板围绕第二轴线枢转时将运动传递到制动连杆回转。

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