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81. 发明授权

EP2481667B1 Structure raidie intégrant un orifice 有权
标题翻译：强化结构，其包括一开口
公开(公告)号：EP2481667B1
公开(公告)日：2015-03-04
申请号：EP12305107.0
申请日：2012-01-27
申请人： Airbus Opérations SAS
发明人： Messina, Paolo , Coudouent, Gérard , Larroumets, Pierre , Tonnele, Arnaud
IPC分类号： B64C1/08 , B64C3/22
CPC分类号： B64C1/08 , B32B3/266 , B64C3/22 , Y10T428/24124 , Y10T428/24149 , Y10T428/24273

82. 发明公开

EP2630603A1 METHODS AND APPARATUS FOR DIGITAL COMPOSITES 审中-公开
标题翻译：方法和设备数码复合材料
公开(公告)号：EP2630603A1
公开(公告)日：2013-08-28
申请号：EP11846817.2
申请日：2011-10-19
申请人： Massachusetts Institute Of Technology
发明人： GERSHENFELD, Neil , CHEUNG, Kenneth
IPC分类号： G06F19/00
CPC分类号： B23P11/00 , B32B5/12 , B32B5/26 , B64C1/06 , B64C1/08 , B64C3/48 , Y10T29/49826 , Y10T29/49828 , Y10T428/24 , Y10T428/24008
摘要： In exemplary implementations of this invention, a digital material comprising many discrete units is used to fabricate a sparse structure. The units are reversibly joined by elastic connections. Each unit comprises fiber-reinforced composite material. Each unit is small compared to the sparse structure as a whole. Likewise, in a sparse structure made from this digital material, the number of types of units is small compared to the total number of units. The digital material is anisotropic. This anisotropy may be due to different fiber orientations within each unit. Furthermore, different units in a single sparse structure may be oriented in different directions and in different, non-parallel planes. In some cases, the digital material is reinforced with carbon fibers, and connections between units are stronger than the units themselves. The small discrete units may be assembled into a strong, lightweight sparse structure, such as an airframe.

83. 发明授权

EP2148812B1 WING-FUSELAGE SECTION OF AN AIRCRAFT 有权
标题翻译：飞机的翅膀，船体分段
公开(公告)号：EP2148812B1
公开(公告)日：2012-10-31
申请号：EP08736434.5
申请日：2008-04-21
申请人： Airbus Operations GmbH
发明人： PAHL, Günter
IPC分类号： B64C1/08 , B64C3/20 , B64C3/22 , B64C1/26
CPC分类号： B64C1/08 , B64C3/22

84. 发明公开

EP2148812A1 WING-FUSELAGE SECTION OF AN AIRCRAFT 有权
标题翻译：飞机的翅膀，船体分段
公开(公告)号：EP2148812A1
公开(公告)日：2010-02-03
申请号：EP08736434.5
申请日：2008-04-21
申请人： Airbus Operations GmbH
发明人： PAHL, Günter
IPC分类号： B64C1/26
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 (7, 8) at which the wing (1) of the aircraft is connected to the fuselage (2), a fuselage region (3) with fuselage frame elements (11-15, 21-25) that extent across the longitudinal direction of the aircraft, and a wing region (5, 6) with spars (16-19, 26-29) that extend in the direction of the wingspan. According to the invention, the spars (16- 19, 26-29) of the wing region (5, 6) and the fuselage frame elements (11-15, 21-25) of the fuselage region (3) form part of an integral assembly (40) that extends at least over a middle part of the wing (1) and the fuselage region (3), including the wing roots (7, 8).

85. 发明公开

EP0130583A3 Thick core sandwich structures and method of fabrication thereof 失效
标题翻译：厚芯三角结构及其制造方法
公开(公告)号：EP0130583A3
公开(公告)日：1987-08-05
申请号：EP84107509
申请日：1984-06-28
申请人： ROCKWELL INTERNATIONAL CORPORATION
发明人： Rainville, Gilles
IPC分类号： B21D47/00
CPC分类号： B64C1/08 , B21D47/00 , B23K20/18 , B64C2001/0081 , Y02T50/42
摘要： A thick metallic sandwich structure having improved strength properties is formed by superplastic forming and selective metallurgical bonding. The structure mormally includes at least five sheets (including two face sheets and at least three core sheets), wherein portions of the core sheets are bonded together to form a partially layered core.

86. 发明申请

US20180207726A1 STRUCTURAL COMPONENT, METHOD FOR PRODUCING A STRUCTURAL COMPONENT AND METHOD FOR DESIGNING A STRUCTURAL COMPONENT 审中-公开
公开(公告)号：US20180207726A1
公开(公告)日：2018-07-26
申请号：US15865888
申请日：2018-01-09
申请人： Airbus Operations GmbH
发明人： Volker Robrecht , Thomas Holder
IPC分类号： B22F5/10 , B29C64/153 , B22F3/105 , B33Y10/00 , B33Y80/00
CPC分类号： B22F5/10 , B22F3/1055 , B22F3/1115 , B29C64/153 , B29L2031/3082 , B33Y10/00 , B33Y80/00 , B64C1/08 , B64C1/12 , Y02P10/295
摘要： A structural component, in particular for an aircraft, has a grid structure which is constructed from rod elements, wherein the rod elements form basic units which are repeated within the grid structure and each have the same polyhedral outer shape. A first number of reinforcing elements are provided in a first region of the grid structure, and a second number of reinforcing elements are provided in a second region of the grid structure, wherein the second number of reinforcing elements is smaller than the first number of reinforcing elements.

87. 发明申请

US20180170533A1 UNMANNED AERIAL VEHICLE 审中-公开
公开(公告)号：US20180170533A1
公开(公告)日：2018-06-21
申请号：US15849254
申请日：2017-12-20
申请人： Samsung Electronics Co., Ltd
发明人： Wu Seong LEE , Bae Seok LIM , Youn Hyung CHOI , Seung Nyun KIM , Yong Sang YUN
IPC分类号： B64C27/00 , B64D47/08 , B64C39/02
CPC分类号： B64C27/006 , B64C1/08 , B64C39/024 , B64C2201/027 , B64C2201/108 , B64C2201/127 , B64C2201/141 , B64D47/08
摘要： An unmanned aerial vehicle (UAV) is provided. The UAV includes a first guard grill, a second guard grill configured to be removably combined with the first guard grill and form an external structure and an inner space of the UAV with the first guard grill, a housing configured to include a central portion located in the center of the inner space and embed a processor and a navigation system, one or more propelling elements configured to be located the inner space and be disposed around the central portion, and a plurality of motor assemblies configured to be located in the inner space and drive the propelling elements while being electrically connected with the processor. When viewed from the outside of the external structure, the propelling elements are partially covered by at least one of the first guard grill or the second guard grill.

88. 发明授权

US09725158B2 Self-righting frame and aeronautical vehicle and method of use 有权
公开(公告)号：US09725158B2
公开(公告)日：2017-08-08
申请号：US15257904
申请日：2016-09-06
申请人： Gaofei Yan , James Dees
发明人： Gaofei Yan , James Dees
IPC分类号： B64C27/08 , B64C17/02 , B64C39/02 , B64D47/08 , B64C1/08 , B64C27/10 , G05D1/00 , A63H27/00 , A63H30/04 , A63H33/00 , A63H15/06 , B64C1/00 , B64C1/06 , B64C17/00
CPC分类号： B64C17/02 , A63H15/06 , A63H27/12 , A63H30/04 , A63H33/005 , B64C1/00 , B64C1/061 , B64C1/08 , B64C17/00 , B64C27/10 , B64C39/024 , B64C2201/027 , B64C2201/108 , B64C2201/12 , B64C2201/146 , B64D47/08 , G05D1/0011 , G05D1/0094
摘要： A self-righting aeronautical vehicle comprising a hollowed frame and a lift mechanism. The exterior of the frame and center of gravity are adapted to self-right the vehicle. The frame can include sealed, hollowed sections for use in bodies of water. The frame can be spherical in shape enabling inspection of internal surface of partially or fully enclosed structures. Inspection equipment can be integrated into the vehicle and acquired data can be stored or wirelessly communicated to a server. A controlled or other mass can be pivotally assembled to a pivot axle spanning across the interior of the frame. The pivot axis can rotate about a vertical axis (an axis perpendicular to the elongated axis). The propulsion mechanisms can be adapted for use as a terrestrial vehicle when enclosed in a sealed spherical shell.

89. 发明授权

US09657489B2 Fractal stiffening 有权
公开(公告)号：US09657489B2
公开(公告)日：2017-05-23
申请号：US14739539
申请日：2015-06-15
申请人： THE BOEING COMPANY
发明人： David William Harper
IPC分类号： E04H7/00 , B64C1/08 , B64C1/12 , E04C2/08 , E04C2/32 , E04C2/38 , E04C2/42
CPC分类号： E04H7/00 , B64C1/08 , B64C1/12 , E04C2/08 , E04C2/32 , E04C2/384 , E04C2/427
摘要： A structural support having fractal-stiffening and method of fabricating the support is presented where an optimized location of at least three nodes is predetermined prior to fabricating the structural support where a first set of webs is formed on one side of the support and joined to the nodes to form a first pocket region. A second set of webs is formed within the first pocket region forming a second pocket region where the height of the first set of webs extending orthogonally from the side of the support is greater than the second set of webs extending orthogonally from the support.

90. 发明授权

US09592898B1 Airframe 有权
标题翻译：机体
公开(公告)号：US09592898B1
公开(公告)日：2017-03-14
申请号：US14880966
申请日：2015-10-12
申请人： Allen L. Davies, Jr.
发明人： Allen L. Davies, Jr.
IPC分类号： B64C1/00 , B64C1/06 , B64C1/12
CPC分类号： B64C1/061 , B64C1/08 , B64C1/12
摘要： An aircraft fuselage panel system for an aircraft of the type having a tubular fuselage frame includes a plurality of generally U-shaped frame members are each adapted to receive a portion of the tubular fuselage frame therein. Each frame member includes a plurality of apertures therethrough. A plurality of metal tabs are fixed to the tubular fuselage frame and include at least one aperture therethrough axially aligned with one of the apertures of one of the frame members. A rigid panel is adapted for fixing between each metal tab and the frame members. Each panel has a plurality of apertures therethrough each axially aligned with one of the apertures of the metal tabs and the frame members. A plurality of mechanical fasteners are adapted for fixing the panel between each metal tab and one of the frame members. The panel and frame member are fixed to the fuselage frame thereby.
摘要翻译：用于具有管状机身框架的类型的飞行器的飞行器机身面板系统包括多个大致U形的框架构件，每个框架构件适于容纳其中的管状机身框架的一部分。每个框架构件包括穿过其中的多个孔。多个金属片固定到管状机身框架，并且包括穿过其中一个框架构件的一个孔的轴向对准的至少一个孔。刚性面板适于在每个金属薄片和框架构件之间固定。每个面板具有穿过其中的多个孔，其与金属接片和框架构件的孔中的一个轴向对齐。多个机械紧固件适于将面板固定在每个金属凸片和框架构件中的一个之间。面板和框架件由此固定在机身框架上。

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