中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

164 records (took 0.022 seconds)

    MODULAR AIRCRAFT SYSTEM
    81.
    发明申请
    MODULAR AIRCRAFT SYSTEM 审中-公开
    模块化飞机系统

    公开(公告)号：WO2017180392A1

    公开(公告)日：2017-10-19

    申请号：PCT/US2017/026146

    申请日：2017-04-05

    Applicant: AL-SABAH, Nasser M. ,  33100.81 PATENT TRUST

    Inventor： AL-SABAH, Nasser M.

    IPC: B64C3/38 ,  B64C3/34 ,  B64C9/00 ,  B64C9/32 ,  B64C13/00 ,  B64C13/20 ,  B64C39/02 ,  B64D15/00 ,  B64D27/02 ,  B64D27/14

    CPC classification number: B64C3/38 ,  B64C1/26 ,  B64C3/34 ,  B64C5/06 ,  B64C9/00 ,  B64C9/326 ,  B64C13/00 ,  B64C13/20 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/063 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/16 ,  B64C2201/165 ,  B64C2211/00 ,  B64D15/00 ,  B64D27/02 ,  B64D27/14 ,  B64D27/20 ,  B64D37/00 ,  B64D39/00 ,  B64D47/08 ,  Y02T50/32

    Abstract: The modular aircraft system includes a single fuselage (10) having a permanently installed empennage (12) and plural sets of wing modules (46a, 46b, 66a, 66b, 68a, 68b) and engine modules (56, 60, 64), with each wing and engine module optimized for different flight conditions and missions. The fuselage (10) and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings (46a, 46b) having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings (68a, 68b) having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module (66a, 66b) is also provided. Turboprop (56), single turbojet (60), and dual turbojet (64) engine modules are provided for installation depending upon mission requirements.

    Abstract translation: 模块化飞行器系统包括具有永久安装的尾翼（12）和多组翼模块（46a，46b，66a，66b，68a，68b）的单个机身（10）和发动机模块 56,60,64），每个机翼和发动机模块针对不同的飞行条件和任务进行了优化。 机身（10）和每个模块被配置为用于模块的快速移除和安装以最小化飞行器的停机时间。 当高度耐力和/或重量承载能力不受重视时，提供具有相对低纵横比的短翼（46a，46b）用于相对高速飞行。 提供具有高纵横比的长翼（68a，68b）用于速度不是绝对重要的较长距离和耐力飞行。 还提供了中跨翼模块（66a，66b）。 根据任务要求，提供涡轮螺旋桨发动机（56），单涡轮喷气发动机（60）和双涡轮喷气发动机（64）发动机模块用于安装。

    SPLIT WINGLET LATERAL CONTROL
    82.
    发明申请
    SPLIT WINGLET LATERAL CONTROL 审中-公开
    分离式金属边界控制

    公开(公告)号：WO2017151225A1

    公开(公告)日：2017-09-08

    申请号：PCT/US2017/013396

    申请日：2017-01-13

    Applicant: GOOGLE INC.

    Inventor： KREBS, Mark

    IPC: B64C9/00 ,  B64C9/34 ,  B64C23/06

    CPC classification number: B64C23/065 ,  B64C9/34 ,  B64C23/076 ,  B64C39/04 ,  Y02T50/164 ,  Y02T50/32 ,  Y02T50/44

    Abstract: A winglet (200) includes a winglet body (210) and a control body (220). The winglet body includes a first winglet surface (202) arranged opposite a second winglet surface (204). The second winglet surface is joined to the first winglet surface to form front and trailing edges (206, 208, 226, 228) of the winglet body. The second winglet surface defines a control body seat (270). The control body is coupled to the winglet body to move between a stowed position seated in the control body seat and a deployed position rotated out of the control body seat. The control body includes a first control surface (222) arranged to face toward the winglet body, a second control surface (224) arranged opposite the first control surface to face away from the winglet body.

    Abstract translation: 小翼（200）包括小翼主体（210）和控制主体（220）。 小翼主体包括与第二小翼表面（204）相对布置的第一小翼表面（202）。 第二小翼表面连接到第一小翼表面以形成小翼主体的前缘和后缘（206,208,226,228）。 第二小翼表面限定控制本体座（270）。 控制本体联接到小翼本体以在坐在控制本体座中的收起位置和旋转出控制本体座的展开位置之间移动。 控制体包括布置成面向小翼本体的第一控制表面（222），布置成与第一控制表面背离小翼本体的第二控制表面（224）。

    AIRCRAFT WING SYSTEM
    83.
    发明申请
    AIRCRAFT WING SYSTEM 审中-公开
    飞机制造系统

    公开(公告)号：WO2016203256A1

    公开(公告)日：2016-12-22

    申请号：PCT/GB2016/051816

    申请日：2016-06-17

    Applicant: BAE SYSTEMS PLC

    Inventor： BROWN, Robert

    IPC: B64C9/24

    CPC classification number: B64C9/24 ,  F16H49/001 ,  Y02T50/32

    Abstract: An aircraft wing system and method comprising: an aircraft wing (102) including upper and lower surfaces, and a leading edge between the upper and lower surfaces; a fairing (200) coupled to the leading edge; and actuation means configured to move the fairing (200) relative to the aircraft wing (102) between a stowed position, a first deployed position, and a second deployed position. The stowed position is when the fairing (200) is in contact with the aircraft wing (102) and serves as a continuation of the aircraft wing (102). The first deployed position is when the fairing (200) is in contact with the aircraft wing (102) and located below the stowed position. The second deployed position is when the fairing (200) is spaced apart from the leading edge to create a gap (402, 500) between the fairing (200) and the leading edge.

    Abstract translation: 一种飞机机翼系统和方法，包括：包括上表面和下表面的飞机机翼（102）和上表面和下表面之间的前缘; 整流罩（200）连接到前沿; 以及致动装置，其构造成在收起位置，第一展开位置和第二展开位置之间相对于飞机机翼（102）移动整流罩200。 收起的位置是当整流罩（200）与飞机机翼（102）接触并且作为飞机机翼（102）的延续时。 第一部署位置是当整流罩（200）与飞机机翼（102）接触并位于收起位置的下方时。 第二展开位置是当整流罩（200）与前缘间隔开以在整流罩（200）和前缘之间形成间隙（402,500）时。

    SHUTTER MECHANISM FOR COVERING A WING DEPLOYMENT OPENING
    84.
    发明申请
    SHUTTER MECHANISM FOR COVERING A WING DEPLOYMENT OPENING 审中-公开
    用于覆盖部署开放的快门机制

    公开(公告)号：WO2014203237A2

    公开(公告)日：2014-12-24

    申请号：PCT/IL2014/050422

    申请日：2014-05-14

    Applicant: RAFAEL ADVANCED DEFENSE SYSTEMS LTD.

    Inventor： SAROKA, Arie ,  SCHOENMANN, Amnon

    CPC classification number: B64C1/14 ,  B64C3/40 ,  B64C7/00 ,  B64C9/02 ,  F42B10/14 ,  F42B10/38 ,  Y02T50/14 ,  Y02T50/32

    Abstract: A shutter mechanism for covering a wing's spreading opening formed in an airborne body and a method for covering such opening while implementing the shutter mechanism, wherein the shutter comprises at least one flap assembly, and wherein from the instant that a deployed wing of the airborne body passed and moved over it, it is biased by traction of at least one springy element to an angular motion around an axis, unto a condition where the flap component of the assembly is positioned so that it is substantially conformal to the outline of the outer surface of the fuselage of the airborne body and while it covers the opening through which the wing passed in its motion; and from an instant that the wing returned and connected to the flap component of the assembly, the flap is biased to an angular motion counter the spring, to the state that the wing returns and is relocated on its top surface.

    Abstract translation: 一种用于覆盖形成在空气传播体中的机翼传播开口的快门机构和一种在实现快门机构的同时覆盖这种开口的方法，其中快门包括至少一个挡板组件，并且其中从空中机体的部署翼 通过并在其上移动，它被至少一个弹性元件的牵引力偏压到围绕轴线的角运动，其中组件的折翼部件被定位成使得其基本上与外表面的轮廓一致 机身的机身，同时它覆盖机翼通过其运动的开口; 并且从翼返回并连接到组件的翼片部件的瞬间，翼片被偏压到与弹簧相反的角运动，到翼返回并被重新定位在其顶表面上的状态。

    DOUBLE SLOTTED FOWLER WING FLAP WITH CHAIN
    85.
    发明申请
    DOUBLE SLOTTED FOWLER WING FLAP WITH CHAIN 审中-公开
    双链缝合翅膀与链条

    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

    IPC: B64C9/20 ,  B64C13/00 ,  B64C13/34

    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 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。

    LIFT-REDUCING APPARATUS FOR AIRCRAFT WINGS
    87.
    发明申请
    LIFT-REDUCING APPARATUS FOR AIRCRAFT WINGS 审中-公开
    航空器减速装置

    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

    IPC: B64C9/32 ,  B64C3/48

    CPC classification number: B64C3/58 ,  B64C9/08 ,  B64C9/323 ,  Y02T50/32 ,  Y02T50/44

    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。

    AIRCRAFT SUPPLEMENTAL THRUST DEVICE AND METHOD OF OPERATING THE SAME
    88.
    发明申请
    AIRCRAFT SUPPLEMENTAL THRUST DEVICE AND METHOD OF OPERATING THE SAME 审中-公开
    飞机辅助装置及其操作方法

    公开(公告)号：WO2014113444A2

    公开(公告)日：2014-07-24

    申请号：PCT/US2014/011633

    申请日：2014-01-15

    Applicant: OTTO, William M.

    Inventor： OTTO, William M.

    IPC: B64D33/02

    CPC classification number: B64D33/02 ,  B64C9/16 ,  B64C9/20 ,  B64C25/14 ,  B64C2025/125 ,  F02C6/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/672

    Abstract: A supplemental thrust system for an airplane comprising a submerged inlet duct, a diffuser section in communication with the inlet duct, and a duct outlet in communication with the diffuser section, an outlet nozzle in communication with the duct outlet, a turbocharger unit comprising one or more turbocharges in communication with each other to provide compressed air to the engine and the cabin, a heat exchanger unit comprising a plurality of heat exchangers in the diffuser section to provide cooling liquid to cool pressurized air in the cabin, engine intake air and the engine jacket, where each turbocharger is coupled to the intake manifold of an engine to increase the power of the engine by introducing compressed air into the manifold.

    Abstract translation: 一种用于飞机的辅助推力系统，包括浸没入口管道，与入口管道连通的扩散器部分和与扩散器部分连通的管道出口，与管道出口连通的出口喷嘴，涡轮增压器单元，包括一个或 更多的涡轮增压彼此连通以向发动机和舱室提供压缩空气;热交换器单元，包括在扩散器部分中的多个热交换器，以提供冷却液体，以冷却舱室内的加压空气，发动机进气和发动机 夹套，其中每个涡轮增压器联接到发动机的进气歧管，以通过将压缩空气引入歧管来增加发动机的功率。

    AN AIRPLANE WING, AN AIRPLANE AND A FLAP SYSTEM
    90.
    发明申请
    AN AIRPLANE WING, AN AIRPLANE AND A FLAP SYSTEM 审中-公开
    空中飞机，飞机和飞翼系统

    公开(公告)号：WO2014073954A1

    公开(公告)日：2014-05-15

    申请号：PCT/NL2013/050767

    申请日：2013-10-29

    Applicant: FOKKER AEROSTRUCTURES B.V.

    Inventor： BASTIAANSEN, Adrianus Marinus Franciscus ,  SCHOONHOVEN, Michel

    IPC: B64C9/20 ,  B64C9/18

    CPC classification number: B64C9/38 ,  B64C9/16 ,  B64C9/18 ,  B64C13/00 ,  Y02T50/32

    Abstract: An airplane wing comprises a main wing and a flap system that has a flap at the trailing edge of the main wing. An elongate flap track member is connected to the main wing in such a manner that it can be moved substantially in its longitudinal direction and is guided by supporting bearing elements relative to the main wing between a forward retracted position and a rearward extended position. The flap is rotatably connected to the rear end of the flap track member in such a manner that it can rotate about a rotation axis that extends substantially parallel to the trailing edge of the main wing,so that the flap moves together with the flap track member when the flap track member is moved and so that the flap can be rotated about the rotation axis mechanically independently of the movement of the flap track member. The flap system comprises an actuator system having two actuators. The first actuator is connected to the main wing and has an engagement member that engages the flap or the flap track member for moving the flap together with the flap track member so that the flap track member is move able between its retracted position and its extended position. The second actuator is connected to the flap track member so that the second actuator moves together with the flap track member when the flap track member is moved by means of the first actuator. The second actuator has an engagement member that engages the flap for rotating the flap about the rotation axis.

    Abstract translation: 飞机机翼包括主翼和在主翼的后缘具有翼片的翼片系统。 细长的翼片轨道构件以这样的方式连接到主翼，使得其可以在其纵向方向上基本上移动，并且在前向缩回位置和向后延伸位置之间通过相对于主翼的支撑轴承元件来引导。 翼片可旋转地连接到翼片轨道构件的后端，使得其可以围绕基本上平行于主翼的后缘延伸的旋转轴线旋转，使得翼片与翼片轨道构件一起移动 当翼片轨道构件被移动并且使得翼片可以机械地围绕旋转轴线旋转而与挡板轨道构件的运动无关。 皮瓣系统包括具有两个致动器的致动器系统。 第一致动器连接到主翼并且具有接合翼片或翼片轨道构件的接合构件，用于将翼片与翼片轨道构件一起移动，使得翼片轨道构件能够在其缩回位置和其延伸位置之间移动 。 第二致动器连接到翼片轨道构件，使得当翼片轨道构件通过第一致动器移动时，第二致动器与翼片轨道构件一起移动。 第二致动器具有接合翼片的接合构件，用于围绕旋转轴线旋转翼片。

Patent Agency Ranking