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111. 发明申请

US20160375978A1 Stiffened fuselage component as well as method and apparatus for manufacturing a stiffened fuselage component 审中-公开
标题翻译：加强的机身部件以及用于制造加强的机身部件的方法和装置
公开(公告)号：US20160375978A1
公开(公告)日：2016-12-29
申请号：US15190982
申请日：2016-06-23
申请人： Airbus Operations GmbH
发明人： Paul Joern
IPC分类号： B64C1/06 , B29D99/00 , B29C65/60 , B64C1/12 , B29B11/06
CPC分类号： B64C1/068 , B29B11/06 , B29C65/601 , B29D99/0014 , B29D99/0021 , B29K2307/04 , B29K2663/00 , B29K2671/00 , B29L2031/3082 , B64C1/08 , B64C1/12 , B64C2001/0045 , B64C2001/0072 , Y02T50/43
摘要： A stiffened fuselage component made of a fiber reinforced composite material, in particular for use in an aircraft, comprises a skin element and a plurality of elongated stiffening elements forming a stiffening element pattern comprising a plurality of node points and being attached to an inner surface of the skin element. At least some of the node points are defined by an intersection of at least two stiffening elements at an acute angle or an obtuse angle. At least some of the elongated stiffening elements are shaped so as to define an internal cavity delimited by an inner surface of the stiffening elements and covered by the skin element.
摘要翻译：由特别用于飞行器的纤维增强复合材料制成的加强的机身部件包括皮肤元件和多个细长加强元件，所述多个细长加强元件形成包括多个节点的加强元件图案，并且附接到皮肤元素。至少一些节点由锐角或钝角的至少两个加强元件的交点限定。细长的加强元件中的至少一些被成形为限定由加强元件的内表面限定并被皮肤元件覆盖的内腔。

112. 发明申请

US20160347438A1 SINGLE-PIECE STRINGER FOR AERONAUTIC STRUCTURE 审中-公开
标题翻译：用于航空结构的单颗圆柱
公开(公告)号：US20160347438A1
公开(公告)日：2016-12-01
申请号：US15166763
申请日：2016-05-27
申请人： STELIA AEROSPACE
发明人： Nicolas Kawski , Olivier Vincent
IPC分类号： B64C1/06 , B64C3/18
CPC分类号： B64C1/064 , B64C1/08 , B64C3/182 , B64C2001/0081
摘要： The invention relates to a single-piece stringer for an aeronautic structure, the stringer comprising a single-piece body including at least one hollow longitudinal portion so as to define an outer enclosure, said outer enclosure including a plurality of openings.
摘要翻译：本发明涉及一种用于航空结构的单件纵梁，所述纵梁包括单件本体，所述单件本体包括至少一个中空纵向部分以便限定外壳，所述外壳包括多个开口。

113. 发明授权

US09415871B1 Aircraft adapted for transporting cargo 有权
标题翻译：适用于运输货物的飞机
公开(公告)号：US09415871B1
公开(公告)日：2016-08-16
申请号：US14629162
申请日：2015-02-23
申请人： SQUARE PEG ROUND HOLE LLC
发明人： John-Curtiss Paul , James D. Raeder
IPC分类号： B64C1/22 , B64D9/00 , B64C1/14 , B64D11/06
CPC分类号： B64C1/22 , B64C1/064 , B64C1/068 , B64C1/08 , B64C1/1415 , B64C1/1461 , B64C1/20 , B64D9/00 , B64D11/06 , B64D11/0689
摘要： The fuselage of an aircraft comprises a floor structure, a roof structure, a first lateral side structure, a second lateral side structure, and a middle structure. The floor structure, the roof structure, the first lateral side structure, and the second lateral side structure define a fuselage space between them. The middle structure spans at least part way between the floor structure and the roof structure, and runs between the first lateral side structure and the second lateral side structure such that the middle structure partitions the fuselage space into an occupant space and a cargo space. A seat for a pilot is disposed in the occupant space lateral to a portion of the middle structure and a portion of the cargo space.
摘要翻译：飞机的机身包括地板结构，屋顶结构，第一侧面结构，第二侧面结构和中间结构。地板结构，屋顶结构，第一侧面结构和第二侧面结构在它们之间限定了机身空间。中间结构至少部分地跨越地板结构和屋顶结构之间，并且在第一侧面结构和第二侧面结构之间延伸，使得中间结构将机身空间分成乘员空间和货物空间。驾驶员的座椅被设置在占用空间中间结构的一部分和货物空间的一部分的侧面。

114. 发明申请

US20160176494A1 SELF-RIGHTING FRAME AND AERONAUTICAL VEHICLE 审中-公开
标题翻译：自拍框和航空汽车
公开(公告)号：US20160176494A1
公开(公告)日：2016-06-23
申请号：US14977546
申请日：2015-12-21
申请人： Gaofei YAN , James DEES
发明人： Gaofei YAN , James DEES
IPC分类号： B64C1/06 , B64C1/08 , A63H15/06 , A63H27/00 , A63H30/04 , B64C27/10 , B64C17/00
CPC分类号： B64C1/061 , A63H15/06 , A63H27/12 , A63H30/04 , A63H33/005 , B64C1/00 , B64C1/08 , B64C17/00 , B64C27/10
摘要： An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting dome shaped vehicle body has an apex/protrusion preferably at a top of a central vertical axis. The apex/protrusion provides initial instability to begin a self-righting process when the vehicle is inverted on a surface. A lift and stabilization panel extends across an upper portion of said frame to provide lift, drag and/or stability. A propulsion system can be located within a central void of the frame assembly and oriented to provide a lifting force. An electronics assembly is also carried by the self-righting body for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a supporting surface. The body provides self-righting functionality and protection of elements carried therein.
摘要翻译：将自身从颠倒状态维持到直立状态的航空车辆具有优选地在中心垂直轴的顶部的顶角/突出部。当车辆在表面上倒置时，顶点/突起提供初始的不稳定性，以开始自我矫正过程。电梯和稳定板横跨所述框架的上部延伸以提供升力，阻力和/或稳定性。推进系统可以位于框架组件的中心空隙内并且被定向成提供提升力。电子组件也由自动矫正机构承载，用于接收遥控命令，并且通信地互连到电源，用于远程控制航空车辆起飞，飞行和着陆在支撑表面上。身体提供自我矫正的功能和保护其中所携带的元素。

115. 发明授权

US08387917B1 Support structure for a cargo aircraft 有权
标题翻译：货机支撑结构
公开(公告)号：US08387917B1
公开(公告)日：2013-03-05
申请号：US12731261
申请日：2010-03-25
申请人： Robert Erik Grip , Blaine Knight Rawdon
发明人： Robert Erik Grip , Blaine Knight Rawdon
IPC分类号： B64C1/00
CPC分类号： B64C1/08 , B64C1/22
摘要： A method and apparatus for transporting containers in an aircraft. A number of containers is loaded into the aircraft. The aircraft is comprised of first and second outer planar structures, a number of planar structures located between the first outer planar structure and the second outer planar structure, a wing, and a support structure. The first outer planar structure, the second outer planar structure, and the number of planar structures are substantially parallel to each other, are coupled to each other to form a fuselage structure, and are configured to receive the number of containers. The support structure connects the wing to a first bottom end of the first outer planar structure, a second bottom end of the second outer planar structure, and a number of bottom ends of the number of planar structures. The aircraft is operated to transport the number of containers to a destination.
摘要翻译：一种用于在飞机上运输集装箱的方法和装置。飞机上装有许多集装箱。飞行器由第一和第二外部平面结构构成，位于第一外部平面结构和第二外部平面结构之间的多个平面结构，翼和支撑结构。第一外平面结构，第二外平面结构和平面结构的数量基本上彼此平行，彼此耦合以形成机身结构，并且被配置为接收多个容器。支撑结构将翼连接到第一外平面结构的第一底端，第二外平面结构的第二底端和多个平面结构的多个底端。该飞机经营运送集装箱到目的地的数量。

116. 发明授权

US08322656B2 Wing-fuselage section of an aircraft 有权
标题翻译：飞机机翼部分
公开(公告)号：US08322656B2
公开(公告)日：2012-12-04
申请号：US12597250
申请日：2008-04-21
申请人： Günter Pahl
发明人： Günter Pahl
IPC分类号： B64C1/00
CPC分类号： B64C1/08 , B64C3/22
摘要： A wing-fuselage section of an aircraft, which wing-fuselage section comprises a wing root at which the wing of the aircraft is connected to the fuselage, a fuselage region with fuselage frame elements that extent across the longitudinal direction of the aircraft, and a wing region with spars that extend in the direction of the wingspan. According to the invention, the spars of the wing region and the fuselage frame elements of the fuselage region form part of an integral assembly that extends at least over a middle part of the wing and the fuselage region, including the wing roots.
摘要翻译：飞机的机翼部分，机翼部分包括机翼，飞机的机翼与机身相连，机身区域具有横跨飞行器的纵向延伸的机身框架元件，以及翼展区域与翼展的方向延伸。根据本发明，机翼区域的翼梁和机身区域的机身框架元件形成整体组件的一部分，其至少在机翼和机身区域的中间部分延伸，包括机翼根部。

117. 发明申请

US20120009372A1 STRUCTURAL PANEL WITH INTEGRATED STIFFENING 有权
标题翻译：具有整体结构的结构面板
公开(公告)号：US20120009372A1
公开(公告)日：2012-01-12
申请号：US13162920
申请日：2011-06-17
申请人： Cedric MEYER , Jocelyn GAUDIN
发明人： Cedric MEYER , Jocelyn GAUDIN
IPC分类号： B32B3/06
CPC分类号： B64C1/08 , B29D99/0014 , B29L2031/3082 , Y10T428/195
摘要： The invention relates to the field of structural panels, more specifically, but not exclusively, to the field of aircraft fuselage panels.The invention concerns a stiffened panel (10) comprising at least one stiffener (4), known as a longitudinal stiffener, extending substantially from one extremity of the panel to the other and whose trace on the surface of said panel's skin (1) follows a path having non-zero geodesic curvature between the two extremities of said stiffener.This configuration makes it possible to optimize both the panel's stiffness and its resistance to the force flow to which it is subjected in operation by minimizing its mass through an optimum definition of the orientation of the stiffeners relative to said force flow.
摘要翻译：本发明涉及结构面板领域，更具体但非唯一地涉及飞机机身面板领域。本发明涉及一种加强板（10），其包括至少一个称为纵向加强件的加强件（4），该加强件（4）基本上从板的一个端部延伸到另一个，并且其在所述面板的皮肤（1）的表面上的痕迹遵循路径在所述加强件的两个末端之间具有非零的测地曲率。这种构造使得可以通过对加强件相对于所述力流的取向的最佳定义来最小化其质量来优化面板刚度及其在操作中所受到的力流的阻力。

118. 发明申请

US20100133382A1 WING-FUSELAGE SECTION OF AN AIRCRAFT 有权
标题翻译：飞机的WF-FUSELAGE部分
公开(公告)号：US20100133382A1
公开(公告)日：2010-06-03
申请号：US12597250
申请日：2008-04-21
申请人： Günter Pahl
发明人： Günter Pahl
IPC分类号： B64C1/26 , B64C1/18 , B64C1/06 , B64C1/08
CPC分类号： B64C1/08 , B64C3/22
摘要： A wing-fuselage section of an aircraft, which wing-fuselage section comprises a wing root at which the wing of the aircraft is connected to the fuselage, a fuselage region with fuselage frame elements that extent across the longitudinal direction of the aircraft, and a wing region with spars that extend in the direction of the wingspan. According to the invention, the spars of the wing region and the fuselage frame elements of the fuselage region form part of an integral assembly that extends at least over a middle part of the wing and the fuselage region, including the wing roots.
摘要翻译：飞机的机翼部分，机翼部分包括机翼，飞机的机翼与机身相连，机身区域具有横跨飞行器的纵向延伸的机身框架元件，以及翼展区域与翼展的方向延伸。根据本发明，机翼区域的翼梁和机身区域的机身框架元件形成整体组件的一部分，其至少在机翼和机身区域的中间部分延伸，包括机翼根部。

119. 发明授权

US06343452B1 Tubular frame 失效
标题翻译：管状框架
公开(公告)号：US06343452B1
公开(公告)日：2002-02-05
申请号：US09137451
申请日：1998-08-14
申请人： Laurence Holden
发明人： Laurence Holden
IPC分类号： E04C208
CPC分类号： B64C1/08 , E04B1/3205 , E04B2001/3288
摘要： A tubular main frame (2) for an aeroplane, bridge, or pressure vessel, for example, comprises a honeycomb structure with cells (4) thereof distributed round the periphery of the frame and along the frame, the cells each being at least pentagonal, preferably largely hexagonal.
摘要翻译：例如，用于飞机，桥梁或压力容器的管状主框架（2）包括蜂窝结构，其蜂窝结构具有围绕框架的周边并且沿框架分布的单元（4），每个单元至少为五边形，优选大部分是六边形。

120. 发明授权

US6010182A Vehicle chassis and body construction 失效
标题翻译：车辆底盘和车身结构
公开(公告)号：US6010182A
公开(公告)日：2000-01-04
申请号：US58514
申请日：1998-04-10
申请人： John A. Townsend
发明人： John A. Townsend
IPC分类号： B62D25/00 , B62D21/12 , B62D23/00 , B62D27/06 , B62D29/04 , B62D33/04 , B64C1/08 , B64C1/12 , F16B5/00 , F16B7/22 , B62D27/00
CPC分类号： B62D21/12 , B62D23/005 , B62D27/06 , B62D29/048 , B62D33/044 , B64C1/08 , B64C1/12 , F16B5/00 , F16B7/22
摘要： This invention relates to chassis and body panel structural systems for a wide variety of vehicles, including automotive, water vessels, aircraft and human powered vehicles, principally comprising a node and interlocking spaceframe system that can be hand assembled in the field. The invention also comprises a key and lock system for wedgingly interlocking body panels to the spaceframe. Together these systems comprise novel Frame Integration Technology (FIT) of the invention. Examples of vehicles include autos, utility vehicles (trucks), public transport vehicles, light boats, human powered vehicles such as bicycles, pedicabs and the like, and light aircraft.
摘要翻译：本发明涉及用于各种车辆的底盘和车身面板结构系统，包括汽车，水船，飞机和人力车辆，主要包括可在现场手动组装的节点和互锁空间框架系统。本发明还包括用于将楔形互锁的车身面板锁定到空间框架上的钥匙和锁定系统。这些系统一起包括本发明的新颖的帧集成技术（FIT）。车辆的实例包括汽车，多用途车（卡车），公共交通工具，轻型船，诸如自行车，脚踏车等人力车辆和轻型飞机。

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