公开(公告)号：KR1020120098607A

公开(公告)日：2012-09-05

申请号：KR1020127009072

申请日：2010-09-09

Applicant: 에어로바이론먼트, 인크.

Inventor： 미랄레스,카로스토마스 ,  프럼브,닉 ,  타우,슈요 ,  올센,나탄

IPC: B64C9/34 ,  B64C13/18 ,  B64C13/28 ,  B64C3/44 ,  B64C3/50 ,  B64C3/56 ,  B64C39/02 ,  B64C5/12 ,  B64C9/02 ,  B64C9/00

CPC classification number: B64C13/28 ,  B64C3/44 ,  B64C3/50 ,  B64C3/56 ,  B64C5/12 ,  B64C9/02 ,  B64C9/08 ,  B64C9/18 ,  B64C11/00 ,  B64C13/18 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/14 ,  B64C2201/145 ,  B64C2201/146 ,  B64C9/34 ,  B64C3/38

Abstract: 본 발명은, 동체 하우징 편향 액츄에이터 혼(621, 622)을 대향하는 탄성장착된 트레일링 에지를 가진 에어포일(141, 142, 1345, 1346)을 통해 키놀이, 옆놀이, 및/또는 빗놀이를 제어하도록 구성된 항공기 또는 무인 항공기(UAV)(100, 400, 1000, 1500)를 포함하는 시스템에 관한 것이다. 실시형태들은, 회전 가능하게 부착되며 이펙터 부재(1049, 1149, 1249, 1349)에 의해 작동될 수 있는 하나 이상의 방향타 요소(1045, 1046, 1145, 1146, 1245, 1345, 1346, 1445, 1446, 1545, 1546)를 포함하고, 상기 이펙터 부재는 동체 하우징(1001) 내에 배치되며, 하나 이상의 방향타 요소들과 맞물리도록 일부 신장 가능하다.

公开(公告)号：KR1020070112819A

公开(公告)日：2007-11-27

申请号：KR1020077021876

申请日：2006-02-09

Applicant: 허니웰 인터내셔널 인코포레이티드

Inventor： 구센엠레이알.

IPC: B64C27/20 ,  B64C29/00 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0016 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/201

Abstract: A dual ducted fan arrangement in which the duct components (203), engine (10), and avionics/payload pods (300, 302) are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan (201), stator (102), and control vane design. Assembly connections between ducted fans (203) and electronic modules are also identical. An engine (10) or APU drives the dual ducted fans (203) through a splined shaft (601) to a differential (600) or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator (102) hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms (603) on each of the splined shafts (601) between the differential (600) and ducted fans (203). In the electric motor case relative speed is through electronic speed control. The fans (201) are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

Abstract translation: 一种双管道风扇装置，其中管道部件（203），发动机（10）和航空电子设备/有效载荷容器（300,302）能够快速拆卸以适合普通的背包系统。 风扇（201），定子（102）和控制叶片设计中的每个管道相同。 管道风扇（203）和电子模块之间的组装连接也是相同的。 发动机（10）或APU通过花键轴（601）驱动双管道风扇（203）到差速器（600）或通过电动机驱动。 通过安装到定子（102）毂的单个齿轮将能量传递到管道风扇。 单个管道风扇的相对速度通过在差速器（600）和管道风扇（203）之间的每个花键轴（601）上的分开的摩擦或发电机负载控制制动机构（603）来控制。 在电动机壳体中，相对速度是通过电子速度控制。 风扇（201）反向旋转以进行扭矩平衡。 电子模块位置对于纵向重心是垂直可变的，用于有效载荷的变化。

公开(公告)号：KR200191404Y1

公开(公告)日：2000-08-16

申请号：KR2020000004037

申请日：2000-02-15

Applicant: 김진경

Inventor： 김진경

IPC: B64C39/00

CPC classification number: B64C39/024 ,  B64C27/22 ,  B64C27/50 ,  B64C27/82 ,  B64C2201/024 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/12 ,  B64D47/00

Abstract: 본 고안은 헬리콥터의 로터를 접거나 안으로 넣을 수 있도록 하고, 제트비행기의 날개를 접거나 안으로 넣을 수 있도록 하고, 한쌍의 로봇 팔을 부착함으로써 물건을 집거나 잡아 들어올릴 수 있도록 하는 장치에 관한 것이다.
본 고안은 상승기류를 이용하는 글라이딩을 할 수 있으면서도, 하강기류나 에어포켓에서 로터를 회전시켜 상승할 수 있고, 좁은 공간에서도 상승하거나 하강할 수 있고, 물건을 로봇 팔로 들어올리거나 할 수 있는 무선조종 장치를 제공한다.

公开(公告)号：KR1019890000530B1

公开(公告)日：1989-03-20

申请号：KR1019820003604

申请日：1982-08-11

Applicant: 레이테온 이-시스템즈 인코포레이티드

Inventor： 찰스에이취.터버주니어 ,  프레데릭에이.베렌스 ,  존에이취.헌튼

IPC: B64C39/02

CPC classification number: F41G7/22 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208 ,  B64F1/06 ,  F41G7/007

Abstract: The remotely piloted aircraft has control surfaces asymmetrical in the pitch and yaw planes, a sensor, and a guidance system operative in the terminal portions of the flight of the aircraft in a yaw-to- turn mode with a zero roll rate. The system has a directional sensor for providing azimuth and elevation error signals. A device provides guidance signals indicative of the rate of change of the azimuth and elevation signals. A guidance programmer responds to the guidance signals for providing pitch control and yaw control signals. An altitude sensor provides an altitude control signal. Roll, pitch and yaw rate gyros provide a rate control signal and a three axis autopilot.

Abstract translation: 遥控飞行器具有在俯仰和偏航平面中不对称的控制表面，传感器和在零滚动速率的偏航 - 转弯模式下在飞行器的飞行的终端部分中操作的引导系统。 该系统具有用于提供方位角和仰角误差信号的方向传感器。 装置提供指示方位角和仰角信号变化率的指导信号。 指导程序员响应用于提供俯仰控制和偏航控制信号的引导信号。 高度传感器提供高度控制信号。 滚动，俯仰和偏航率陀螺仪提供速率控制信号和三轴自动驾驶仪。

公开(公告)号：WO2017044388A1

公开(公告)日：2017-03-16

申请号：PCT/US2016/050192

申请日：2016-09-02

Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATION

Inventor： STARACE, Ralph C. ,  AUGUST, Robert A. ,  FRONIUS, Douglas L. ,  CREASMAN, Francois

IPC: B64C29/02

CPC classification number: B64C29/02 ,  B64C3/56 ,  B64C9/00 ,  B64C27/57 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  G05D1/0011 ,  G05D1/0088 ,  G05D1/0858

Abstract: One example embodiment includes a vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) (12). The VTOL UAV includes a flight control system configured to provide avionic control of the VTOL UAV in a hover mode and in a level-flight mode. The VTOL UAV also includes a body (18) encapsulating an engine and the flight control system. The VTOL UAV further includes a rotor disk (14) coupled to the engine and configured to provide vertical thrust and cyclic pitch control in the hover mode and to provide horizontal thrust for flight during the level-flight mode.

Abstract translation: 一个示例性实施例包括垂直起飞和着陆（VTOL）无人机（UAV）（12）。 VTOL无人机包括飞行控制系统，配置为以悬停模式和级别飞行模式提供垂直起降无人机的航空电子控制。 VTOL无人机还包括封装发动机的主体（18）和飞行控制系统。 垂直起落架无人机还包括联接到发动机的转子盘（14），并配置成在悬停模式下提供垂直推力和循环桨距控制，并在水平飞行模式期间为飞行提供水平推力。

公开(公告)号：WO2016170322A1

公开(公告)日：2016-10-27

申请号：PCT/GB2016/051086

申请日：2016-04-20

Applicant: COOK, George Michael

Inventor： COOK, George Michael ,  COOK, Jonathan Edward ,  COOK, Michael Kevin

IPC: B64C39/02

CPC classification number: B64C13/28 ,  B64C1/061 ,  B64C3/56 ,  B64C13/30 ,  B64C31/02 ,  B64C39/024 ,  B64C2001/0054 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2211/00

Abstract: An aerial delivery assembly (10) for autonomously delivering a load to a target location, the assembly comprising an airframe which comprises a main body (12), at least one deployable lift providing structure (30), the lift providing structure being moveable between a stowed position and a deployed position; and at least one deployable and adjustable control structure (34, 36, 38, 39) for controlling the flight of the assembly and moveable between a stowed position and a deployed position. The main body (12) comprises a compartment for receiving a load to be delivered. The assembly further comprises a control unit (20) comprising an actuation module for use in adjusting the control structure (34,36, 38, 39), wherein the control unit is releaseably connected to the airframe such that it is reusable in an aerial delivery assembly having a different airframe.

Abstract translation: 一种用于自主地将负载传送到目标位置的空中输送组件（10），所述组件包括机身，所述机身包括主体（12），至少一个可展开的提升提供结构（30），所述提升提供结构可在 收起位置和部署位置; 以及至少一个可展开和可调节的控制结构（34,36,38,39），用于控制组件的飞行并且可在收起位置和展开位置之间移动。 主体（12）包括用于接收要被输送的负载的隔间。 组件还包括控制单元（20），其包括用于调节控制结构（34,36,38,39）的致动模块，其中控制单元可释放地连接到机身，使得其可在空中传送 组件具有不同的机身。

公开(公告)号：WO2016077278A1

公开(公告)日：2016-05-19

申请号：PCT/US2015/059841

申请日：2015-11-10

Applicant: ASCENT AEROSYSTEMS LLC

Inventor： MERINGER, Jonathan, R. ,  MERINGER, Nathaniel, R.

IPC: B64C27/10 ,  B64C27/32 ,  B64C27/50

CPC classification number: B64C39/024 ,  B64C27/10 ,  B64C27/50 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/18

Abstract: An unmanned flying device including a body; a first blade and at least a second blade; a coupling assembly for coupling the first blade and the at least second blade to the body, wherein the coupling assembly urges the collapsing of the first blade and the at least second blade towards the body; and wherein both the first blade and the at least second blade are rotateable about the body, and wherein the first blade and the at least second blade are deployable away from the body via rotation of the first and the at least second blades about the body.

Abstract translation: 一种无人驾驶飞行装置，包括一个身体; 第一叶片和至少第二叶片; 用于将所述第一叶片和所述至少第二叶片联接到所述主体的联接组件，其中所述联接组件促使所述第一叶片和所述至少第二叶片朝向所述主体折叠; 并且其中所述第一叶片和所述至少第二叶片都可围绕所述主体旋转，并且其中所述第一叶片和所述至少第二叶片可通过所述第一叶片和所述至少第二叶片围绕所述主体的旋转而远离所述主体展开。

公开(公告)号：WO2016066790A1

公开(公告)日：2016-05-06

申请号：PCT/EP2015/075234

申请日：2015-10-30

Applicant: ÉCOLE POLYTECHNIQUE FÉDÉRALE DE LAUSANNE

Inventor： MINTCHEV, Stefano ,  DALER, Ludovic ,  FLOREANO, Dario

IPC: B64C39/02

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/127

Abstract: An aerial vehicle (100) including self-autonomous deployable arms (108) and methods of deploying the vehicle are disclosed. The arms (108) may include patterns located thereon that allow the arms (108) to transition between wrapped, flat, and deployed configurations autonomously without the need for direct intervention by a user.

Abstract translation: 公开了一种包括自主可展开臂（108）的飞行器（100）和部署车辆的方法。 臂（108）可以包括位于其上的图案，其允许臂（108）自主地在包裹的，平坦的和部署的配置之间转换，而不需要用户的直接干预。

公开(公告)号：WO2015108578A3

公开(公告)日：2015-09-03

申请号：PCT/US2014060166

申请日：2014-10-10

Applicant: SWIFT ENGINEERING INC

Inventor： GODLASKY ROBERT ,  OGAWA NATE ,  STREETT ANDREW

IPC: B64C29/00 ,  B64C3/56 ,  B64C5/02 ,  B64C29/02 ,  B64D27/02

CPC classification number: B64D27/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

Abstract: A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

Abstract translation: 垂直起落飞行器包括至少一个牵引转子和至少一个推动器转子。 例如，VTOL飞机可以包括三个牵引转子和一个推动器转子。 静态牵引器和推动器转子的组合允许转子相对于垂直起降飞机的机翼和机身保持在固定方向（即，不需要移动的机械轴），同时能够使飞机从基本垂直的飞行 到达基本水平的飞行路径的路径。

公开(公告)号：WO2014041198A1

公开(公告)日：2014-03-20

申请号：PCT/EP2013/069291

申请日：2013-09-17

Applicant: BLUE BEAR SYSTEMS RESEARCH LIMITED

Inventor： SNOOK, Michael Alexander

IPC: B64C3/40 ,  B64C3/54 ,  B64C33/02

CPC classification number: B64C3/546 ,  B64C3/40 ,  B64C3/54 ,  B64C39/024 ,  B64C2003/543 ,  B64C2201/102 ,  Y02T50/14

Abstract: Embodiments of the present invention relate to an adaptable wing (112, 114) having a variable geometry for influencing aerodynamic performance, the wing (112, 114) comprising a jointed leading edge having a main pivot (116), and a wrist joint (118), with a wing arm (126, 128) therebetween, and a distal wing hand (122, 124) depending from the wrist joint (118); the wing (12, 114) being reciprocally actuable, via the main pivot (116) and wrist joint (118), between a first state having an extended wing planform and a second state having a tucked wing planform.

Abstract translation: 本发明的实施例涉及一种具有可变几何形状以用于影响空气动力学性能的可适应翼（112,114），所述翼（112,114）包括具有主枢轴（116）和腕关节（118）的接合前缘 ），其间具有翼臂（126,128）和从腕关节（118）悬垂的远侧翼手（122,124）; 所述机翼（12,114）经由所述主枢轴（116）和腕关节（118）在具有延伸机翼平面图的第一状态和具有卷起的机翼平面图的第二状态之间可往复驱动。