公开(公告)号：KR1020060005010A

公开(公告)日：2006-01-17

申请号：KR1020040053821

申请日：2004-07-12

Applicant: 박상명

Inventor： 박상명

IPC: E01C1/00 ,  B64F1/00

CPC classification number: E01C1/002 ,  B64C2201/187 ,  B64F1/00

Abstract: 본 발명은 항공기 활주로 구조에 관한것으로, 자연의 힘인 지구 중력을 항공기가 이, 착륙시에 필요한 가속과 감속에 활용 할 수 있도록하여 고안하였다.
활주로,구조

公开(公告)号：WO2016149545A1

公开(公告)日：2016-09-22

申请号：PCT/US2016/022959

申请日：2016-03-17

Applicant: AMAZON TECHNOLOGIES, INC.

Inventor： GENTRY, Nicholas Kristofer

IPC: B64C25/32 ,  B64C39/02

CPC classification number: B64C25/001 ,  B64C25/10 ,  B64C25/18 ,  B64C25/24 ,  B64C25/32 ,  B64C25/52 ,  B64C39/024 ,  B64C2025/008 ,  B64C2201/027 ,  B64C2201/128 ,  B64C2201/18 ,  B64C2201/187 ,  B64D1/02 ,  G05D1/102

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) landing gear assembly that includes adjustable landing gear extensions (251) that may be extended or contracted so that the body of the UAV is contained in a horizontal plane when the UAV is landed, even on sloping surfaces. For example, when a UAV is landing, the slope of the surface may be determined and the landing gear extensions (251) adjusted based on the slope so that the body of the UAV remains approximately horizontal when the UAV lands and is supported by the landing gear extensions.

Abstract translation: 本公开描述了一种无人飞行器（UAV）起落架组件的结构，其包括可调节的起落架延伸部（251），其可以伸缩或收缩，使得当UAV着陆时UAV的车体被包含在水平面中， 即使在倾斜的表面上。 例如，当UAV着陆时，可以确定表面的斜率，并且基于斜率调整起落架延伸部（251），使得当UAV着陆并由着陆支撑时，UAV的车身保持近似水平 齿轮延伸

公开(公告)号：WO2014209220A1

公开(公告)日：2014-12-31

申请号：PCT/SG2013/000260

申请日：2013-06-24

Applicant: SINGAPORE TECHNOLOGIES AEROSPACE LTD ,  DSO NATIONAL LABORATORIES

Inventor： CHUA Chee Nam ,  CHOON, Junwei ,  LIM, Kok Yong

IPC: B64C13/18 ,  B64C39/02 ,  G05D1/06 ,  G05D1/08 ,  G05D1/10

CPC classification number: G05D1/0676 ,  B64C13/18 ,  B64C25/32 ,  B64C39/024 ,  B64C2201/146 ,  B64C2201/187 ,  G05D1/0011 ,  G05D1/0808

Abstract: Various embodiments provide a method for landing an unmanned aerial vehicle (UAV) (2) in the presence of a wind. The method comprises: performing a first flare- maneuver whilst the UAV is flying. The flare-maneuver causes a front portion of the UAV to rise with respect to a rear portion of the UAV (202). The method also comprises steering the UAV along a path heading into a direction of the wind (204). The method further comprises performing a second flare- maneuver before the UAV impacts a landing surface to land (206). Various embodiments provide a corresponding UAV.

Abstract translation: 各种实施例提供了一种在存在风的情况下着陆无人机（UAV）（2）的方法。 该方法包括：在无人机飞行时执行第一次火炬弹。 火炬机动使UAV的前部相对于UAV（202）的后部上升。 该方法还包括沿着朝向风向（204）的方向的路径转向无人机。 该方法还包括在UAV撞击着陆面到达之前执行第二次火炬操作（206）。 各种实施例提供相应的无人机。

公开(公告)号：WO2005103939A1

公开(公告)日：2005-11-03

申请号：PCT/US2004/009080

申请日：2004-03-25

Applicant: BELL HELICOPTER TEXTRON INC ,  BUILTA, Kenneth, E. ,  HARRIS, James, E. ,  HONZA, Bryan, P. ,  EPP, Jeffrey, W. ,  SCHULTE, Kynn, J.

Inventor： BUILTA, Kenneth, E. ,  HARRIS, James, E. ,  HONZA, Bryan, P. ,  EPP, Jeffrey, W. ,  SCHULTE, Kynn, J.

IPC: G06F17/00

CPC classification number: B64C39/024 ,  B64C13/20 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/205 ,  G05D1/0027 ,  G05D1/0684

Abstract: A system for controlling flight of an aircraft has sensors (37, 43), a receiver (45), and a digital control system (57), all of which are carried aboard the aircraft. The sensors (37, 43) determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver (45) receives transmitted data (51, 55) communicating the position and movement of a reference vehicle relative to the earth. The control system (57) calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors (37, 43) and the receiver (45) and then commands flight control devices (33) on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.

Abstract translation: 用于控制飞机飞行的系统具有传感器（37,43），接收器（45）和数字控制系统（57），所有这些都被携带在飞行器上。 传感器（37,43）确定飞行器相对于地球的位置和飞行器的惯性运动。 接收器（45）接收传送参考车辆相对于地球的位置和移动的传送数据（51,55）。 控制系统（57）使用来自传感器（37,43）和接收器（45）的数据来计算飞机相对于参考车辆的位置和速度，然后命令飞行器上的飞行控制装置（33）进行操纵 飞行器以相对于参考车辆保持选定位置和/或速度的方式。 该系统允许使用图形或触觉的用户界面。

公开(公告)号：WO01046009A1

公开(公告)日：2001-06-28

申请号：PCT/FR2000/003618

申请日：2000-12-20

IPC: A63H27/08 ,  A63H30/04 ,  B64C31/036 ,  B64C39/02 ,  B64D47/08

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: The invention concerns a small-size radio-controlled flying device propelled by a heat engine (20) with pusher propeller (10) for remote sensing, said device enabling short take-off and landing and a maximum flying speed of 34 Km/h. The device comprises a nacelle and a wing system, the nacelle (1) being a rigid three-wheeled carriage capable of being disassembled by denesting a more or less pyramidal jig with rear base (2) and front top (7), a lower plane (3) two lateral planes (4, 5) and an upper plane (6), the base being a single-piece welded element and comprising the engine, the propeller, a tank and the remote sensing unit, the top being a single-piece welded element, the lower plane and the two lateral planes comprising side members (11, 12) at least assembled at the base and at the top, the lower plane comprising at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being arranged overlapping forward in the top and the wheels being low pressure tyres, the wing system (13) being a wing box flexible parafoil, said wing system being linked to the nacelle adjustable by two front suspension cables (17), two braking suspension cables (18) acting on the two flaps/wings.

Abstract translation: 本发明涉及一种由具有用于遥感的推进推进器（10）的热机（20）推进的小型无线电控制飞行装置，所述装置能够进行短时起飞和着陆，并且最大飞行速度为34公里/小时。 该装置包括机舱和机翼系统，所述机舱（1）是刚性三轮车架，其能够通过使后座（2）和前顶（7）破坏或多或少的金字塔夹具而被拆卸，下平面 （3）两个横向平面（4,5）和上平面（6），底座是单件焊接元件，包括发动机，螺旋桨，油箱和遥感单元， 所述下平面和所述两个横向平面包括至少组装在所述基部和顶部处的侧部构件（11,12），所述下平面在其三个端角处包括两个后轮（8）和前轮 （9），所述前轮在顶部布置成向前，所述车轮是低压轮胎，所述机翼系统（13）是翼盒柔性parafoil，所述翼系统与所述机舱连接，所述机舱可由两个前悬挂缆索 17），两个制动悬挂电缆（18）作用在两个翼/翼上。

公开(公告)号：EP2720948A4

公开(公告)日：2015-02-11

申请号：EP11867771

申请日：2011-06-17

Applicant: SING ROBERT L

Inventor： SING ROBERT L

IPC: B64F1/22 ,  B64C13/18 ,  B64D9/00 ,  B64D45/00 ,  B64F1/28

CPC classification number: B64D9/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/187

公开(公告)号：EP2716543A1

公开(公告)日：2014-04-09

申请号：EP12187089.3

申请日：2012-10-03

Applicant: Sensefly S.A.

Inventor： Beyeler, Antoine ,  Klaptocz, Adam ,  Roberts, James F. ,  Zimmermann, Loic ,  Zufferey, Jean-Christophe

IPC: B64C1/26

CPC classification number: B64C1/26 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/187 ,  B64C2201/20

Abstract: This invention relates to a connection set that is used to attach and transfer force and torque between a wing (2a, 2b), comprising a lifting surface and a control surface (9) connected together by a hinge, and the central body (1) of an aircraft, which contains a servo-motor (10) used for actuating said control surface (9). The wing (2a, 2b) is connected to the central body (1) using a connection set comprised of two components. First, an attachment mechanism (3, 4, 5, 6) is used to align the wings (2a, 2b) relative to the central body (1) and to transfer the aerodynamic forces acting on the wing (2a, 2b) to the central body (1), preventing the wing (2a, 2b) from bending at its connection point. Second, a torque coupling mechanism (7, 8) is used to actuate the control surfaces that are present on the wings using servomotors (10) that are embedded within the central body (1). The connection set is engaged and disengaged using a single motion and does not require additional connection of electrical cables or mechanical fixations.

Abstract translation: 本发明涉及一种用于在包括提升表面和通过铰链连接在一起的控制表面（9）的翼（2a，2b）之间附接和传递力和扭矩的连接组，以及中心体（1） 其包含用于致动所述控制表面（9）的伺服电动机（10）。 翼（2a，2b）使用由两个部件组成的连接组件连接到中心体（1）。 首先，使用附接机构（3,4,5,6）来相对于中心体（1）对准翼（2a，2b）并将作用在机翼（2a，2b）上的空气动力传递到 中心体（1），防止机翼（2a，2b）在其连接点处弯曲。 第二，扭矩联接机构（7,8）用于使用嵌入在中心体（1）内的伺服电动机（10）致动存在于机翼上的控制表面。 连接组使用单一动作进行接合和分离，不需要额外连接电缆或机械固定。

公开(公告)号：EP2413096A4

公开(公告)日：2013-12-11

申请号：EP09842038

申请日：2009-03-27

Applicant: YU QIFENG

Inventor： LEI ZHIHUI ,  ZHANG XIAOHU ,  SHANG YANG ,  ZHANG HENG ,  ZHOU XIANG

IPC: G01C11/00 ,  G01C21/10 ,  G01S5/16 ,  G05D1/06 ,  G08G5/00 ,  G08G5/02

CPC classification number: G01C11/00 ,  B64C2201/187 ,  G01C21/10 ,  G01S5/16 ,  G05D1/0676 ,  G08G5/0026 ,  G08G5/025

Abstract: The present invention provides a ground-based camera surveying and guiding method for aircraft landing and unmanned aerial vehicle recovery based on the camera surveying technology, which is a ground-based camera surveying and guiding system mainly including several video cameras arranged near the landing areas of an aircraft or an unmanned aerial vehicle. During the approaching process of the aircraft or the unmanned aerial vehicle, the system performs imaging of the aircraft in real time and detects movement parameters such as the track, velocity, acceleration, attitude and the offset relative to the glide slope of the aircraft or the unmanned aerial vehicle in real time by analyzing images and applying camera surveying method and technology, so as to provide guidance for aircraft landing or unmanned aerial vehicle recovery. The method is an autonomic guiding survey without interferences from others, which has high accuracy and reliability. The hardware devices are mature, simple and have low cost. The devices are moveable and versatile, and can be used in aircraft landing aid, unmanned aerial vehicle recovery and the like.

Abstract translation: 本发明提供了一个基于地面的照相机测量和基于照相机测量技术用于飞机着陆和无人驾驶飞行器恢复引导方法，所有这些是基于地面的照相机测量和引导系统主要包括邻近的着陆区布置多个视频摄像机 飞机或无人机。 在飞机或无人驾驶飞行器的接近过程中，系统执行实时飞行器的成像和检测移动参数：诸如轨道，速度，加速度，姿态和偏移相对于飞行器或的下滑斜度 实时无人机通过分析图像和应用相机测量方法和技术，以便为飞机着陆或无人机复苏提供指导。 该方法是在不脱离他人的干扰自主引导调查，其具有高精确度和可靠性。 硬件设备的成熟，简单，成本低。 设备是可移动的，多功能的，并且可以在飞机着陆辅助，无人驾驶飞行器恢复等来使用。

公开(公告)号：EP1590239A4

公开(公告)日：2011-06-15

申请号：EP04701733

申请日：2004-01-13

Applicant: BOXAIR ENGINEERING LLC

Inventor： STUPAKIS JOHN S

IPC: B64C39/02 ,  B64C1/00

CPC classification number: B64C39/024 ,  B64C39/02 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2211/00 ,  B64D2011/0046 ,  Y10S244/903

公开(公告)号：EP1827972B8

公开(公告)日：2008-10-22

申请号：EP05813078.2

申请日：2005-11-30

Applicant: Israel Aerospace Industries Ltd.

Inventor： SIRKIS, Omri

IPC: B64C9/18 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C9/18 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/187 ,  B64C2201/201

Abstract: A method for landing a fixed wing aircraft is provided in which an inversion maneuver is performed so that the aircraft's back is facing the ground, and the aircraft's underside is facing away from the ground. After initiation or completion of this maneuver, deep stall is induced, and the aircraft descends almost vertically to land on its upper side, thus minimizing impact loads or damage on its underside. In a particular aerodynamic arrangement configured for carrying out the method, a flap (24), which may be stowed during normal flight, is deployed in a manner such as to aerodynamically induce a negative pitching moment on the aircraft and deep stall.

Abstract translation: 提供了一种用于着陆固定翼飞机的方法，其中执行反转操纵，使得飞机的背面朝向地面，并且飞机的底面背离地面。 在开始或完成这种机动之后，引起深度失速，并且飞机几乎垂直下降以落在其上侧，从而最小化撞击载荷或其下侧的损坏。 在构造成用于执行该方法的特定空气动力学布置中，可以在正常飞行期间收起的襟翼（24）以诸如在空气动力学上引起飞行器上的负俯仰力矩和深度失速的方式展开。