公开(公告)号：EP3007788A1

公开(公告)日：2016-04-20

申请号：EP14728993.8

申请日：2014-06-10

Applicant: THALES

Inventor： CARPENTIER, Luc ,  GAUTHIER, Thierry

IPC: A63H27/14

CPC classification number: B64F1/04 ,  A63H27/14 ,  B64C39/024 ,  B64C2201/08

Abstract: The invention relates to a device designed to launch a drone, comprising a rail (21) extending along a longitudinal axis (22) and a carriage (23), movable on the rail (21), able to support and launch a drone by accelerating the carriage (23) between a loading position and an end-of-travel position, characterized in that it further comprises a spring mechanism (41) configured to exert a return force on the carriage (23) along the longitudinal axis that is substantially constant between the two positions. The spring mechanism (41) comprises at least one spring coiled around a hub, one end of the coiled spring being connected to the carriage (23), the return force exerted on the carriage being generated by winding the spring around the hub.

Abstract translation: 用于发射无人机的装置包括沿着纵向轴线延伸的轨道和在轨道上移动的滑架，其可以通过在装载位置和行程结束位置之间的滑架的加速度来支撑和发射无人机， 还包括弹簧机构，其构造成沿着所述两个位置之间基本上恒定的所述纵向轴线在所述托架上施加返回力。 弹簧机构包括围绕轮毂的至少一个螺旋弹簧，螺旋弹簧的一端连接到滑架，通过弹簧围绕毂盘绕而产生施加在滑架上的返回力。

公开(公告)号：EP2724941A1

公开(公告)日：2014-04-30

申请号：EP13189774.6

申请日：2013-10-22

Applicant: The Boeing Company

Inventor： Childress, Jamie J ,  Perron, Daniel J

IPC: B64F1/04 ,  G05D1/08

CPC classification number: B64C39/024 ,  B64C2201/08 ,  B64C2201/208 ,  B64F1/04

Abstract: Systems and methods to launch an aircraft are disclosed. In one embodiment, a system to launch an aircraft comprises a launch arm comprising at least one load cell, an aircraft coupled to the launch arm, and a release mechanism in communication with the at least one load cell, wherein the release mechanism releases the aircraft when the at least one load cell indicates that a load on the launch arm is below a predetermined threshold. Other embodiments may be described.

Abstract translation: 公开了发射飞机的系统和方法。 在一个实施例中，发射飞行器的系统包括发射臂，其包括至少一个称重传感器，耦合到发射臂的飞行器以及与所述至少一个称重传感器通信的释放机构，其中所述释放机构释放飞行器 当所述至少一个称重传感器指示所述发射臂上的负载低于预定阈值时。 可以描述其他实施例。

公开(公告)号：EP2475575A2

公开(公告)日：2012-07-18

申请号：EP10833732.0

申请日：2010-09-09

Applicant: AeroVironment, Inc.

Inventor： MIRALLES, Carlos, Thomas ,  PLUMB, Nick ,  TAU, Shuo ,  OLSEN, Nathan

IPC: B64C9/34 ,  B64C13/18 ,  B64C3/38 ,  B64C13/28

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

Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100, 400, 1000, 1500) configured to control pitch, roll, and/or yaw via airfoils (141, 142, 1345, 1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621, 622). Embodiments include one or more rudder elements (1045, 1046, 1145, 1146, 1245, 1345, 1346, 1445, 1446, 1545, 1546) which may be rotatably attached and actuated by an effector member (1049, 1149, 1249, 1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.

Abstract translation: 一种包括飞行器或无人驾驶飞行器（UAV）的系统，其被配置为经由具有弹性安装的后缘的机翼来控制俯仰，滚动和/或偏航，所述后翼与机身偏转致动器喇叭相对。 实施例包括一个或多个方向舵元件，其可以由设置在机身壳体内的效应器构件可旋转地附接和致动，并且部分地可部分地接合一个或多个舵元件。

公开(公告)号：US20190243357A1

公开(公告)日：2019-08-08

申请号：US16388168

申请日：2019-04-18

Applicant: SZ DJI TECHNOLOGY CO., LTD.

Inventor： Hualiang Qiu ,  Zhongqian You ,  Jinji Li ,  Youcheng Zhao ,  Xiaofeng Feng ,  Jian Feng

IPC: G05D1/00 ,  G05D1/10 ,  B64C39/02 ,  G05D1/12 ,  B64D47/08 ,  H04N5/232

CPC classification number: G05D1/0038 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/18 ,  B64D47/08 ,  G05D1/0016 ,  G05D1/0022 ,  G05D1/0094 ,  G05D1/0808 ,  G05D1/101 ,  G05D1/12 ,  G06F3/02 ,  G09G3/3406 ,  G09G3/36 ,  H04N5/23206

Abstract: A wearable device for controlling an unmanned aerial vehicle (UAV) includes one or more sensors configured to detect first status information of the wearable device, a communication circuit configured to transmit the first status information to the UAV and receive second status information of the UAV from the UAV, and a processor configured to generate a control instruction according to at least one of the first status information or the second status information, and control the communication circuit to transmit the control instruction to the UAV to control the UAV.

公开(公告)号：US20190185159A1

公开(公告)日：2019-06-20

申请号：US16210413

申请日：2018-12-05

Applicant: Iain Matthew Russell

Inventor： Iain Matthew Russell

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/08 ,  B64C2201/141 ,  B64C2201/18 ,  B64C2201/205 ,  B64C2201/206 ,  B64C2201/208 ,  G06Q10/00

Abstract: Various measures (for example methods, UAVs, controllers and computer programs) are provided in relation to controlling a UAV. The UAV is caused to provide energy to and receive energy from a given vehicle. The received energy is used to provide power to at least one component of the UAV.

公开(公告)号：US20180244402A1

公开(公告)日：2018-08-30

申请号：US15755699

申请日：2016-08-25

Applicant: UVISION AIR LTD

Inventor： MOSHE KAHLON ,  SHLOMO HAKIM

IPC: B64F1/04 ,  B64C39/02

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/201

Abstract: A launcher for unmanned aerial vehicles (UAV), the launcher having a foldable UAV stowed within said launcher, the launcher includes, a launch tube configured as a UAV launcher and a UAV carrying case. The launcher further includes a pneumatic booster connected to said UAV for accelerating said UAV during launching phase. The launcher further includes a separation mechanism operated to permits separation of the booster from the UAV when the UAV leaves the launcher tube and to transfer the kinetic energy that is created from the pneumatic booster to the UAV in the launching phase. The UAV is propelled off of the launch tube by the booster that transmits thrust in the launch tube to the space below said booster. The UAV which is connected to the booster by the separation mechanism is pushed out of the launcher tube body and leaves the launch tube, the booster is separated from the UAV by the separation mechanism and the UAV is automatically deployed. The UAV propellers are activated to propel the UAV and driven the UAV.

公开(公告)号：US20180215482A1

公开(公告)日：2018-08-02

申请号：US15419979

申请日：2017-01-30

Applicant: Hanhui ZHANG

Inventor： Hanhui ZHANG

IPC: B64F1/04 ,  B64C27/10 ,  B64C39/02 ,  B64C27/08

CPC classification number: B64F1/04 ,  B64C27/08 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/08 ,  B64C2201/108 ,  B64C2201/146

Abstract: A rotary wing unmanned aerial vehicle and pneumatic launcher system includes a rotary wing unmanned aerial vehicle and a pneumatic launcher. The rotary wing unmanned aerial vehicle includes a pressure tube, a launch detector, and a center controller. The pressure tube has an open end and a closed end. The launch detector is coupled to the center controller and detects the launch of the rotary wing unmanned aerial vehicle. The pneumatic launcher includes a launch gas reservoir, a launch tube, and a release valve. The release valve is located between the launch gas reservoir and the launch tube. The gas reservoir holds launch gas. The launch tube is inserted into the pressure tube through the open end.

公开(公告)号：US20180157276A1

公开(公告)日：2018-06-07

申请号：US15829690

申请日：2017-12-01

Applicant: Vantage Robotics, LLC

Inventor： Tobin Fisher ,  Johannes Becker Van Niekerk ,  Pavlo Manovi

IPC: G05D1/10 ,  B64C39/02 ,  G01C21/18 ,  B64D47/02

CPC classification number: G05D1/102 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/08 ,  B64C2201/14 ,  B64C2201/141 ,  B64D47/02 ,  G01C21/16 ,  G01C21/18

Abstract: A unmanned aerial vehicle (UAV) includes a body with plurality of motors, a motor controlling circuit, a microprocessor for controlling the flight state of the UAV, a plurality of motion sensors, and a capacitive touch sensor incorporated into a battery. When the user grasps the UAV by the battery, the touch sensor is activated and the microprocessor alters the flight state of the UAV.

公开(公告)号：US20180101169A1

公开(公告)日：2018-04-12

申请号：US15844207

申请日：2017-12-15

Applicant: Paul G. Applewhite

Inventor： Paul G. Applewhite

IPC: G05D1/00 ,  B64F1/04 ,  B64F1/06 ,  B64C39/02 ,  B64C27/82 ,  B64C29/02 ,  B64C29/00

CPC classification number: G05D1/0027 ,  B64C11/04 ,  B64C11/28 ,  B64C27/82 ,  B64C29/0083 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/08 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/126 ,  B64C2201/146 ,  B64F1/04 ,  B64F1/06 ,  G05D1/104 ,  G08G5/00 ,  G08G5/0008 ,  G08G5/0013 ,  G08G5/0069

Abstract: An improved unmanned aerial vehicular system having a rotor head assembly with any balanced number of rotary wings or blades, a generally tubular body assembly, a gimballed neck connecting the head to the body, and a navigation, communications and control unit such as for military and humanitarian operations, including payload delivery and pickup. The vehicle is generally guided using a global positioning satellite signal, and by pre-programmed or real time targeting. The vehicle is generally electrically powered and may be launched by one of (a) hand-launch, (b) air-drop, (c) catapult, (d) tube-launch, or (e) sea launch, and is capable of landing on both static and dynamic targets. Once launched, unmanned aerial vehicles may be formed into arrays on a target area and find use in surveillance, warfare, and in search-and-rescue operations.

公开(公告)号：US20170369150A1

公开(公告)日：2017-12-28

申请号：US15608758

申请日：2017-05-30

Applicant: SIERRA NEVADA CORPORATION

Inventor： Ken FINKLEA ,  Carlos MIRALLES

IPC: B64C3/56 ,  B64D17/80 ,  B64C39/02

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/206 ,  B64C2201/208 ,  B64D17/80

Abstract: In one embodiment, a wing for an unmanned aerial vehicle is described. The unmanned aerial vehicle includes a first body of the wing with a first end proximate a body of the vehicle. A second end is opposite the first end. A first joint is on the first end of the first main body of the wing. The joint rotatably couples the wing to the vehicle. A second joint is on the second end of the vehicle. A second body of the wing is rotatably coupled to the first body via the second joint.