公开(公告)号：JP6425969B2

公开(公告)日：2018-11-21

申请号：JP2014220469

申请日：2014-10-29

Applicant: ヤンマー株式会社

Inventor： 尾崎 英一

IPC: B64C27/08 ,  B64C39/02 ,  B64D17/80 ,  B64D27/24

CPC classification number: B64D27/24 ,  B64C25/32 ,  B64C27/08 ,  B64C39/024 ,  B64C2025/325 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/185 ,  B64D17/80 ,  B64D2201/00 ,  Y02T50/44 ,  Y02T50/64

公开(公告)号：JP2017095010A

公开(公告)日：2017-06-01

申请号：JP2015231121

申请日：2015-11-26

Applicant: 株式会社オプティム

Inventor： 菅谷 俊二

IPC: B64C39/02 ,  B64C27/08 ,  B64D27/24 ,  B64D47/00 ,  B64D25/00

CPC classification number: B64D25/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/146 ,  B64C2201/185

Abstract: 【課題】無人航空機の落下による衝撃を防ぎ、無人航空機の破損を防ぐとともに、落下地点にある物体や生物を保護する。 【解決手段】回転翼10を備える無人航空機100に、衝突時に機体の衝撃を和らげる緩衝モジュール111を備える。また、バッテリー残量計測モジュール122や距離計測モジュール123によりバッテリー残量や物体との距離を計測し、計測値と閾値を比較して計測値が閾値を下回る場合には、発動モジュール121により緩衝モジュール111を発動する。 【選択図】図6

公开(公告)号：US10059459B2

公开(公告)日：2018-08-28

申请号：US14723897

申请日：2015-05-28

Applicant: Kespry, Inc.

Inventor： Robert Parker Clark

IPC: G05D1/00 ,  G05D1/08 ,  G05D3/00 ,  G06F7/00 ,  G06F17/00 ,  B64D17/62 ,  B64C39/02 ,  B64D43/02 ,  B64D17/80 ,  G05D1/10

CPC classification number: B64D17/62 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/185 ,  B64D17/80 ,  B64D43/02 ,  G05D1/0072 ,  G05D1/0077 ,  G05D1/0088 ,  G05D1/105

Abstract: An unmanned aerial vehicle includes a closely integrated emergency recovery and operation systems for an unmanned aerial vehicle with built-in levels of redundancy and independence to maximize the likelihood of a controlled velocity landing. The unmanned aerial vehicle may include multiple processors and multiple state estimating modules such as inertial measurement units to independently determine the operational and error status of the unmanned aerial vehicle. Base on predictive or projected computations, the emergency recovery system may determine a suitable time for a recovery action, such as parachute deployment, and execute the recovery action.

公开(公告)号：US09977431B2

公开(公告)日：2018-05-22

申请号：US15419804

申请日：2017-01-30

Applicant: Ford Global Technologies, LLC

Inventor： John A. Lockwood ,  Joseph F. Stanek

IPC: G05D1/02 ,  B64C39/02 ,  G05D1/00 ,  G08G1/09

CPC classification number: G05D1/0276 ,  B60R16/02 ,  B60W30/00 ,  B64C29/0008 ,  B64C29/0091 ,  B64C29/02 ,  B64C39/00 ,  B64C39/02 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/02 ,  B64C2201/08 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/12 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/14 ,  B64C2201/141 ,  B64C2201/18 ,  B64C2201/182 ,  B64C2201/185 ,  B64C2201/187 ,  B64C2201/20 ,  B64C2201/208 ,  B64C2230/00 ,  G05D1/0022 ,  G05D1/0088 ,  G05D1/0094 ,  G05D1/0202 ,  G05D1/0212 ,  G05D1/0231 ,  G05D1/0242 ,  G05D1/0255 ,  G05D1/0257 ,  G05D1/028 ,  G05D2201/0213 ,  G08C17/00 ,  G08G1/012 ,  G08G1/091

Abstract: This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced.

公开(公告)号：US09738383B2

公开(公告)日：2017-08-22

申请号：US15391517

申请日：2016-12-27

Applicant: Richard D. Adams

Inventor： Richard D. Adams

IPC: B64D17/00 ,  B64C39/02 ,  B64D17/80 ,  B64C1/26

CPC classification number: B64C39/024 ,  B64C1/26 ,  B64C3/56 ,  B64C2201/104 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/203 ,  B64D17/00 ,  B64D17/80

Abstract: A remotely controlled or autonomously controlled UAV is disclosed. The UAV has both wings and a deployable parachute to enable both fixed wing flight and paraglider flight. The UAV can fly at a higher speed to a mission area as a fixed wing craft, and loiter over the area as a powered paraglider. In some embodiments, the wings are jettisoned over the mission area and the UAV configured as a powered paraglider completes its mission. In other embodiments the UAV flies to the mission area as a fixed wing craft, deploys the parachute to loiter as a powered paraglider and then jettisons the parachute to fly under a fixed wing back to a base. The former embodiment cannot fly back to a base, they may be used to carry and deploy bombs or grenades, while the latter may be used for surveillance, deliver supplies or the like.

公开(公告)号：US20170166309A1

公开(公告)日：2017-06-15

申请号：US15370302

申请日：2016-12-06

Applicant: DISCO CORPORATION

Inventor： Kazuma Sekiya

IPC: B64D11/00 ,  B64C39/02 ,  B64D1/22 ,  B64D17/00 ,  B64D11/06

CPC classification number: B64D11/00 ,  B64C39/024 ,  B64C39/026 ,  B64C2201/027 ,  B64C2201/12 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/185 ,  B64D1/22 ,  B64D11/062 ,  B64D17/00 ,  B64D25/00

Abstract: Disclosed herein is a human transporting drone including a drone core, a human receptacle for accommodating a human, the human receptacle being detachably housed in the drone core, ropes connected to the human receptacle, and rope winding mechanisms mounted on the drone core, for winding the ropes to house the human receptacle into the drone core and unwinding the ropes to release the human receptacle from the drone core.

公开(公告)号：US20170106986A1

公开(公告)日：2017-04-20

申请号：US15294479

申请日：2016-10-14

Applicant: Flirtey Holdings, Inc.

Inventor： Matthew Sweeny ,  Michel Fathallah ,  Tom Bass ,  Kranthi Baddam ,  John R. Foggia

IPC: B64D17/80 ,  G05D1/00 ,  B64C25/58 ,  B64C39/02

CPC classification number: B64D17/80 ,  B64C25/58 ,  B64C39/024 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/185 ,  B64D17/70 ,  B64D45/00 ,  G05D1/0038 ,  G05D1/105

Abstract: Disclosed is a technique for landing a drone using a parachute. The technique includes a parachute deployment system (PDS) that can deploy a parachute installed in a drone and land the drone safely. The parachute may be deployed automatically, e.g., in response to a variety of failures such as a free fall, or manually from a base unit operated by a remote user. For example, the PDS can determine the failure of the drone based on data obtained from an accelerometer, a gyroscope, a magnetometer and a barometer of the drone and automatically deploy the parachute if any failure is determined. In another example, the remote user can “kill” the drone, that is, cut off the power supply to the drone and deploy the parachute by activating an onboard “kill” switch from the base unit.

公开(公告)号：US09527596B1

公开(公告)日：2016-12-27

申请号：US14716785

申请日：2015-05-19

Applicant: Richard D. Adams

Inventor： Richard D. Adams

IPC: B64D17/00 ,  B64C11/00 ,  B64C39/02 ,  B64C3/56

CPC classification number: B64D17/00 ,  B64C3/56 ,  B64C11/001 ,  B64C39/024 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/203

Abstract: A remotely controlled UAV is disclosed. The UAV includes a parachute, with a cylindrical power and control module suspended vertically below the parachute. In one embodiment, a propulsion source is mounted on top of the power and control module with control lines connected to the module below the propulsion source, and in another embodiment the power and control module is suspended from a point above a propulsion source. The UAV may be flown under a parachute and guided by remote control, or the control module (fuselage) may be released from the parachute and extendable fixed wings deployed to enable the UAV to be flown as a fixed wing vehicle.

Abstract translation: 公开了遥控无人机。 无人机包括一个降落伞，一个圆柱形的电源和控制模块垂直悬挂在降落伞下方。 在一个实施例中，推进源安装在功率和控制模块的顶部，其控制线连接到推进源下方的模块，并且在另一个实施例中，功率和控制模块从推进源上方的点悬挂。 无人机可以在降落伞下飞行并由遥控器引导，或者控制模块（机身）可以从降落伞释放并且可伸展的固定翼部署以使无人机作为固定翼车辆飞行。

公开(公告)号：US20160368610A1

公开(公告)日：2016-12-22

申请号：US14850642

申请日：2015-09-10

Applicant: Alan Jamal ERICKSON

Inventor： Alan Jamal ERICKSON

IPC: B64D17/72 ,  B64C39/02 ,  B64D17/80

CPC classification number: B64D17/72 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/185 ,  B64D17/80 ,  B64D25/00 ,  B64D2201/00

Abstract: A system and method for resisting an uncontrolled descent or uncontrolled flight condition of an aerial vehicle. The system includes a control system, sensors, an inflation device, and a deployable, inflatable assembly. The control system detects an uncontrolled condition using the sensors, and subsequently initiates the inflation device to inflate the inflatable assembly. The assembly includes an inflatable cage stored on and deployed from the aerial vehicle upon detection of an uncontrolled condition. The inflatable cage includes a hub, a perimeter tube, and support tubes connected between the hub and perimeter tube. Fill tubes enable inflation of the support and perimeter tubes. The assembly includes a parachute-material enclosure connected to the inflatable cage and structured to create drag to reduce a velocity of the aerial vehicle when the inflatable assembly is deployed. The assembly includes weight distribution straps physically coupled between the vehicle and the enclosure or inflatable cage.

Abstract translation: 一种用于抵抗飞行器的不受控制的下降或不受控飞行状态的系统和方法。 该系统包括控制系统，传感器，充气装置和可展开的可充气组件。 控制系统使用传感器检测不受控制的状况，随后启动充气装置以使充气组件膨胀。 该组件包括在检测到不受控制的状态时存储在飞行器上并展开的可充气笼。 可充气笼包括轮毂，周边管和连接在轮毂和周边管之间的支撑管。 填充管可以支撑支架和周边管的膨胀。 组件包括连接到可充气笼的降落伞材料外壳，并被构造成当展开充气组件时产生拖曳以降低飞行器的速度。 组件包括物理耦合在车辆与外壳之间的重量分配带，或者可充气笼。

公开(公告)号：US20160332739A1

公开(公告)日：2016-11-17

申请号：US14713343

申请日：2015-05-15

Applicant: Disney Enterprises, Inc.

Inventor： Clifford Wong

IPC: B64D25/00 ,  B64C39/02

CPC classification number: B64D25/00 ,  B64C39/00 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/024 ,  B64C2201/14 ,  B64C2201/146 ,  B64C2201/18 ,  B64C2201/185

Abstract: An unmanned aerial vehicle apparatus comprises a frame. Further, the unmanned aerial vehicle apparatus comprises a propulsion mechanism coupled to the frame that propels the frame through the air. In addition, the unmanned aerial vehicle apparatus comprises a storage device that stores one or more airbags and is coupled to the frame. The unmanned aerial vehicle apparatus also comprises an inflation device coupled to the frame that receives an activation signal and inflates the one or more airbags based upon receipt of the activation signal to deploy the one or more airbags from the storage device prior to an impact of the frame with an object.

Abstract translation: 无人驾驶飞行器装置包括一个框架。 此外，无人驾驶飞行器装置包括联接到框架的推进机构，其推动框架通过空气。 此外，无人驾驶飞行器装置包括存储装置，该存储装置存储一个或多个安全气囊并且联接到该框架。 无人驾驶飞行器装置还包括联接到框架的充气装置，其接收启动信号，并且基于接收到激活信号而使一个或多个安全气囊充气，以在所述启动信号的影响之前从所述存储装置部署所述一个或多个气囊 框架与对象。