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公开(公告)号：WO2014113464A1
公开(公告)日：2014-07-24
申请号：PCT/US2014/011670
申请日：2014-01-15
Applicant: OTTO, William M.
Inventor： OTTO, William M.
IPC: B64C1/00
CPC classification number: B64C25/20 , B64C1/00 , B64C1/065 , B64C1/069 , B64C1/10 , B64C3/185 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/02 , B64C25/10 , B64C25/12 , B64C25/14 , B64C25/18 , B64C25/22 , B64C2025/125 , B64D33/10 , B64D37/04 , F02B37/001 , Y02T50/32 , Y02T50/44
Abstract: A fuselage for an airplane including a frame comprising an upper truss and a lower truss extending from a front end of the fuselage towards the rear end of the fuselage, wherein the lower truss comprises one or more forward box beams, a plurality of support rings attached to the upper truss and lower truss, a front bulkhead connected to a first end of the upper truss and lower truss, a main bulkhead connected to the upper truss and lower truss, a pressure vessel adapted to fit within the frame between the front bulkhead and main bulkhead, and a skin adapted to fit over the frame.
Abstract translation: 一种用于飞机的机身，包括框架，该框架包括从机身的前端朝向机身的后端延伸的上桁架和下桁架，其中下桁架包括一个或多个前箱梁，多个支撑环连接 连接到上桁架和下桁架的前隔板，连接到上桁架和下桁架的第一端的前隔板，连接到上桁架和下桁架的主隔板，适于装配在前隔板和前隔板之间的框架内的压力容器 主要隔板和适于装配在框架上的皮肤。
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公开(公告)号：WO2014113426A1
公开(公告)日：2014-07-24
申请号：PCT/US2014/011602
申请日：2014-01-15
Applicant: OTTO, William M.
Inventor： OTTO, William M.
IPC: B64C25/34
CPC classification number: B64C25/20 , B64C1/00 , B64C1/065 , B64C1/069 , B64C1/10 , B64C3/185 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/02 , B64C25/10 , B64C25/12 , B64C25/14 , B64C25/18 , B64C25/22 , B64C2025/125 , B64D33/10 , B64D37/04 , F02B37/001 , Y02T50/32 , Y02T50/44
Abstract: A main landing gear system for an aircraft including a truss element including a front portion joined to a rear portion, a first support unit and second support unit affixed to the truss at the junction of the first portion and the second portion on opposing sides of the truss, a first actuator and a second actuator rotatively affixed to respective first support unit and second support unit and to a respective first wheel and second wheel, a first trailing link and second trailing link each coupled to the respective first wheel and second wheel.
Abstract translation: 一种用于飞行器的主起落架系统，其包括桁架元件，该桁架元件包括接合到后部的前部，第一支撑单元和第二支撑单元，该第一支撑单元和第二支撑单元在第一部分和第二部分的接合处固定到桁架 桁架，第一致动器和第二致动器，其旋转地固定到相应的第一支撑单元和第二支撑单元以及相应的第一轮和第二轮，第一牵引杆和第二牵引杆，每个联接到相应的第一轮和第二轮。
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公开(公告)号：WO2009067319A2
公开(公告)日：2009-05-28
申请号：PCT/US2008081472
申请日：2008-10-28
Applicant: BOEING CO , LEE ROBERT MICHAEL , EVANS BRIAN G
Inventor： LEE ROBERT MICHAEL , EVANS BRIAN G
Abstract: A multi-segment flap fence is incorporated into the wing such that a lower fence structure is attached to the underside of the fixed wing, an upper fence structure is attached to the main flap (e.g., at the outboard end). The two flap segments are configured to slideably articulate with respect to each other when the flap is extended to form a composite flap fence having an area that is substantially equal to the sum of the surface areas of the upper and lower flap fence structures. In one embodiment, the area of the upper fence is less than that of the lower fence.
Abstract translation: 多翼片挡板结合到机翼中，使得下固定翼结构附接到固定翼的下侧，上挡板结构附接到主翼片（例如，在外侧端）。 两个翼片段构造成当翼片延伸时相对于彼此可滑动地铰接以形成具有基本上等于上部和下部翼片挡板结构的表面积的总和的面积的复合翼片挡板。 在一个实施例中，上围栏的面积小于下围栏的面积。
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公开(公告)号：WO00063071A1
公开(公告)日：2000-10-26
申请号：PCT/FR2000/000864
申请日：2000-04-06
CPC classification number: B64C3/14 , B64C3/58 , B64C2003/145 , Y02T50/12
Abstract: The present invention relates to an aerodynamic surface (1) such as a wing, empennage, angle of drift, nacelle pylon etc. for an aircraft. According to the invention, said aerodynamic surface (1) comprises at least one lightening hole (7) pertaining to the trailing edge of the underwing; at least one hinged baffle (8) that can be mounted in the lightening hole (7) of the underwing, whereby the chord thereof is equal to a several hundredths of the chord (C) of the aerodynamic surface (1); and means for actuating the moveable baffle (8) so that it can rotate around the hinge line (9).
Abstract translation: 本发明涉及一种用于飞机的空气动力学表面（1），例如翼，尾翼，漂移角，机舱塔等。 根据本发明，所述空气动力学表面（1）包括至少一个与所述底翼的后缘相关的减重孔（7）; 至少一个铰链挡板（8），其可以安装在所述下摆的减光孔（7）中，由此所述弦线等于所述空气动力学表面（1）的弦（C）的几百分之一。 以及用于致动可移动挡板（8）使得其能够围绕铰链线（9）旋转的装置。
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公开(公告)号：WO99050141A1
公开(公告)日：1999-10-07
申请号：PCT/US1999/006753
申请日：1999-03-29
CPC classification number: B64C3/58 , B64C23/06 , Y02T50/162
Abstract: A deployable flow control device for a flow surface (10) over which fluid having a fluid boundary layer flows which fluid boundary layer exhibits certain dynamics is disclosed. The deployable flow control device comprises a flow effector (20) which is movably attached to a housing (12) which is attachable, either initially or retrofitably, to a flow surface (10). The flow effector (20) is deployed into and retracted out of the boundary layer on the flow surface (10) and thereby controls the boundary dynamics. Devices (including devices utilizing a sealable, flexible element (60)) operably connect to the flow effector (20) and deploy and retract it. The sealable, flexible element (60) has two elastic states defined as quiescent and deformed such that, when the sealable, flexible element (60) is utilized, the flow effector (20) is deployed into and retracted out of the fluid boundary layer based upon the elastic state of the sealable, flexible element (60).
Abstract translation: 公开了一种用于流动表面（10）的可展开的流量控制装置，流体边界层流过具有流体边界层的流体，流体边界层表现出某种动态。 可展开的流量控制装置包括流动执行器（20），其可移动地附接到壳体（12），壳体（12）可初始地或可更新地附接到流动表面（10）。 流动执行器（20）展开到流动表面（10）上的边界层中并从中缩出，从而控制边界动力学。 装置（包括利用可密封的柔性元件（60）的装置）可操作地连接到流动执行器（20）并且展开和缩回它。 可密封的柔性元件（60）具有定义为静止和变形的两个弹性状态，使得当使用可密封的柔性元件（60）时，流动执行器（20）基于流体边界层展开和退出 在可密封的柔性元件（60）的弹性状态下。
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Patent Agency Ranking
公开(公告)号：WO2014168661A3
公开(公告)日：2014-11-27
申请号：PCT/US2014011641
申请日：2014-01-15
Applicant: OTTO WILLIAM M
Inventor： OTTO WILLIAM M
CPC classification number: B64C25/20 , B64C1/00 , B64C1/065 , B64C1/069 , B64C1/10 , B64C3/185 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/02 , B64C25/10 , B64C25/12 , B64C25/14 , B64C25/18 , B64C25/22 , B64C2025/125 , B64D33/10 , B64D37/04 , F02B37/001 , Y02T50/32 , Y02T50/44
Abstract: A wing flap control system on a wing comprising at least two control plates having an opening sized to accommodate a drive shaft, a drive shaft that engages each of the openings in each of the plurality of plates, a sprocket rotatively affixed the drive shaft with the drive shaft penetrating the other control plate, at least two idler sprockets between the control plates, a chain wrapped around the sprocket and idler sprockets, a support arm rotatively coupled to the chain by a chain shoe and to a foreflap, a link arm rotatively coupled to the support arm and to a flap, where movement of the drive shaft causes the foreflap and flap to extend and retract to increase or decrease the surface area of the wing.
Abstract translation: 一种机翼上的机翼翼片控制系统，包括至少两个控制板，该控制板的开口尺寸适于容纳驱动轴;驱动轴，其接合多个板中的每一个中的每个开口;链轮，其将驱动轴与 驱动轴穿过另一个控制板，控制板之间至少有两个空转链轮，围绕链轮和惰轮链轮缠绕的链条，支撑臂通过链条可转动地联接到链条和前翼，连杆臂可旋转地联接 到支撑臂和翼片，其中驱动轴的运动导致前翼和翼片延伸和缩回以增加或减小机翼的表面积。
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公开(公告)号：WO2014155107A1
公开(公告)日：2014-10-02
申请号：PCT/GB2014/050958
申请日：2014-03-26
Applicant: EADS UK LIMITED
Inventor： ROLSTON, Stephen
Abstract: Modern aircraft wings generally have a lower surface the rear part of which is concave over at least some of its length, for additional lift. Sometimes it is desirable to reduce the wing lift, for instance during turbulence. To this end the wing 1 has, located at least partly in or forward of this concave part and forward of the trailing edge, a spoiler device such as a deployable spoiler 20 operable to change between a configuration in which the surface is uninterrupted and one in which the device separates flow, so as to reduce local lift over the concave portion. An actuator 26 can be provided for deploying the spoiler, and an upper spoiler 40 can also be present, operated by the same or a separate actuator. Alternatively the spoiler device can include a flexible or deforming material 120 operable to protrude from the wing surface.
Abstract translation: 现代飞机机翼通常具有下表面，其后部的至少一部分在其长度上是凹的，用于额外的升力。 有时需要减少机翼升力，例如在湍流期间。 为此，机翼1至少部分地位于该凹部的前方或后方，并且位于后缘的前方，具有可展开扰流板20的扰流装置，其可操作以在表面不间断的结构和 该装置分离流动，以便减少凹部上的局部升力。 可以设置致动器26用于展开扰流器，并且上扰流器40也可以由相同或单独的致动器操作。 或者，扰流装置可以包括可操作以从机翼表面突出的柔性或变形材料120。
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公开(公告)号：WO2014129761A1
公开(公告)日：2014-08-28
申请号：PCT/KR2014/001001
申请日：2014-02-06
Applicant: 주식회사 네스앤텍
Inventor： 이기성
CPC classification number: B64C27/28 , B64C3/38 , B64C3/58 , B64C9/323 , B64C39/024 , B64C2201/088 , B64C2201/108 , B64C2201/185 , B64C2201/187
Abstract: 착륙이 용이한 무인비행체가 제공되며, 무인비행체는 방향을 전환하는 프로펠러, 상기 프로펠러를 지지하는 프로펠러 타워, 상기 프로펠러 타워에 연결되어 있는 동체, 상기 동체의 수평축을 기준으로 좌우가 대칭이며, 상기 동체의 무게중심부에 한 쌍의 통공을 포함하는 주날개, 상기 한 쌍의 통공 내부에 각각 위치하는 한 쌍의 보조날개, 그리고 상기 한 쌍의 보조날개를 관통하며 상기 주날개에 고정되어 있는 기준축에 연결되어 있으며, 상기 한 쌍의 보조날개의 경사각도를 제어하는 액츄에이터(actuator)를 포함한다.
Abstract translation: 披露了一个简单的降落无人机，包括：改变方向的螺旋桨; 用于支撑螺旋桨的螺旋桨塔; 连接到螺旋桨塔的主体; 相对于主体的水平轴线对称地设置有两侧的主翼，在主体的主体的重心处形成有一对开口部， 一对辅助翼分别布置在该对开口中; 以及通过所述一对辅助翼连接到固定到主翼的基准轴的致动器，用于控制所述一对辅助翼的倾斜角。
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公开(公告)号：WO2014113435A1
公开(公告)日：2014-07-24
申请号：PCT/US2014/011622
申请日：2014-01-15
Applicant: OTTO, William M.
Inventor： OTTO, William M.
IPC: B64C25/10
CPC classification number: B64C25/20 , B64C1/00 , B64C1/065 , B64C1/069 , B64C1/10 , B64C3/185 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/02 , B64C25/10 , B64C25/12 , B64C25/14 , B64C25/18 , B64C25/22 , B64C2025/125 , B64D33/10 , B64D37/04 , F02B37/001 , Y02T50/32 , Y02T50/44
Abstract: A front landing gear system for an aircraft including a swing arm rotatively coupled to a wheel, a forward link arm rotatively coupled to the swing arm, a oleopneumatic cylinder rotatively coupled to the swing arm, second extension arm and a bulkhead, a plate rotatively coupled to the bulkhead, an actuation device rotatively coupled to the bulkhead and to the plate, where retraction of the linear actuation device causes the plate and extension arms to move upward towards the bulkhead.
Abstract translation: 一种用于飞行器的前起落架系统，包括可旋转地联接到车轮的摆臂，可旋转地联接到摆臂的前连杆臂，可旋转地联接到摇臂，第二延伸臂和隔板的油气缸，板旋转耦合 驱动装置旋转地联接到隔板和板上，其中线性致动装置的缩回导致板和延伸臂朝向舱壁向上移动。
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公开(公告)号：WO2011127938A1
公开(公告)日：2011-10-20
申请号：PCT/EP2010/002250
申请日：2010-04-12
Applicant: AIRBUS OPERATIONS GMBH , AIRBUS OPERATIONS LTD. , HELLER, Gerd , BUESCHER, Alexander , THEURICH, Frank , GIBSON, Tom , KARWIN, Michael , POWELL, Stephen
Inventor： HELLER, Gerd , BUESCHER, Alexander , THEURICH, Frank , GIBSON, Tom , KARWIN, Michael , POWELL, Stephen
IPC: B64C23/06
CPC classification number: B64C3/58 , B64C23/069 , Y02T50/164
Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box comprised of spars extending along the spanwise direction of the main wing, a plurality of ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box is comprised of a wing box base section (K10) and a wing box adapter section (20), that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device (W). In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib (R3) of the wing box base section (K10) up to the outermost rib (R5) of the wing box adapter section.
Abstract translation: 一种飞机的固定翼，具有在半跨上延伸的主翼，翼翼由沿着主翼的翼展方向延伸的翼梁组成，沿翼展方向观察的多个肋布置在另一个后面 ，和外皮。 翼箱由翼箱基部（K10）和翼盒适配器部分（20）组成，从机翼根部观察时，形成翼盒的外端区域，并被设计成固定翼尖 设备（W）。 在其标称建造状态下，翼箱适配器部分参考相应的局部翼展方向的二面角从翼箱基部（K10）的外肋（R3）连续增加至多60度，直到最外侧 机翼盒适配器部分的肋（R5）。
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