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41. 发明申请

US20180065745A1 UNMANNED VEHICLES NAVIGATION TERMINATION SYSTEM 审中-公开
公开(公告)号：US20180065745A1
公开(公告)日：2018-03-08
申请号：US15698341
申请日：2017-09-07
申请人： Flytrex Aviation Ltd.
发明人： Yariv BASH , Amit REGEV , Vadim ZLOTNIK
IPC分类号： B64C39/02 , B64D17/80 , B64D31/04 , B64D31/06
CPC分类号： B64C39/024 , B64C2201/185 , B64D17/80 , B64D31/04 , B64D31/06
摘要： A navigation termination system of an unmanned vehicle (UV) is provided. The system includes a plurality of sensors connected to the UV and configured to detect motion of the UV; a power supply configured to power the movement of the UV; a processing circuitry; and a memory, the memory containing instructions that, when executed by the processing circuitry, configure the system to: determine, based on sensory signals captured by the plurality of sensors, a navigation termination event; and disrupt a connection between the power supply and a motion mechanism of the UV when the navigation termination event occurs.

42. 发明申请

US20180050805A1 INTELLIGENT PARACHUTE RESCUE SYSTEM FOR MANNED AND UNMANNED AERIAL VEHICLES 审中-公开
公开(公告)号：US20180050805A1
公开(公告)日：2018-02-22
申请号：US15556649
申请日：2016-03-10
申请人： KAPI electronics GmbH
发明人： Holger Kalinka
IPC分类号： B64D17/72 , B64D17/80 , B64D45/00
CPC分类号： B64D17/72 , B64C39/024 , B64C2201/185 , B64D17/80 , B64D25/12 , B64D45/00 , B64D2045/0085
摘要： The invention relates to a method and a device for an intelligent parachute rescue system for manned and unmanned aerial vehicles (14), wherein no pyrotechnic propellants are used, but compressed air (4a) extracted from a pressure bottle (4).

43. 发明申请

US20180009539A1 MULTI-ROCKET PARACHUTE DEPLOYMENT SYSTEM 审中-公开
公开(公告)号：US20180009539A1
公开(公告)日：2018-01-11
申请号：US15207354
申请日：2016-07-11
申请人： Kitty Hawk Corporation
发明人： Cameron Robertson , Joseph Roop , Todd Reichert , Damon Vander Lind
IPC分类号： B64D17/72 , B64D17/80
CPC分类号： B64D17/725 , B64D17/62 , B64D17/80 , B64D45/00
摘要： Techniques to deploy a parachute are disclosed. In various embodiments, a first projectile is configured to be propelled in a first direction, causing the parachute to be deployed. A second projectile configured to be propelled in a second direction is coupled to a line tethered to the parachute in such a way that a force in a direction opposite the first direction is applied to the line of the parachute when the second projectile is propelled in the second direction.

44. 发明申请

US20170369150A1 AIR-LAUNCHED UNMANNED AERIAL VEHICLE 审中-公开
公开(公告)号：US20170369150A1
公开(公告)日：2017-12-28
申请号：US15608758
申请日：2017-05-30
申请人： SIERRA NEVADA CORPORATION
发明人： Ken FINKLEA , Carlos MIRALLES
IPC分类号： B64C3/56 , B64D17/80 , B64C39/02
CPC分类号： B64C3/56 , B64C39/024 , B64C2201/021 , B64C2201/08 , B64C2201/082 , B64C2201/084 , B64C2201/102 , B64C2201/201 , B64C2201/206 , B64C2201/208 , B64D17/80
摘要： 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.

45. 发明申请

US20170225792A1 PARACHUTE DEPLOYMENT SYSTEM FOR AN UNMANNED AERIAL VEHICLE 审中-公开
公开(公告)号：US20170225792A1
公开(公告)日：2017-08-10
申请号：US15503089
申请日：2015-08-11
申请人： DroneTech Studio, LLC
发明人： Liang Wang , Daniel Joseph Bodenstein , Ryan Michael Welsh , Kevin Ian McWilliams
IPC分类号： B64D17/70 , B64D17/80 , B64C39/02
CPC分类号： B64D17/70 , B64C39/024 , B64C2201/185 , B64D17/80
摘要： Various embodiments of the present disclosure relate to a parachute deployment system for an unmanned aerial vehicle (UAV). In some examples, the parachute deployment system includes a base attached to the unmanned aerial vehicle, a deployment tray mechanically connected to the base, an acceleration mechanism for propelling the deployment tray away from the base, a parachute cover releasably secured over the deployment tray, a parachute stowed between the deployment tray and the parachute cover, and a triggering mechanism. Upon activation of the triggering mechanism, the parachute cover is released and the deployment tray is propelled away from the base, which rapidly deploys the parachute away from the UAV.

46. 发明申请

US20170101180A1 REMOTE CONTROLLED AERIAL RECONNAISSANCE VEHICLE 审中-公开
公开(公告)号：US20170101180A1
公开(公告)日：2017-04-13
申请号：US15391517
申请日：2016-12-27
申请人： Richard D. Adams
发明人： Richard D. Adams
IPC分类号： B64C39/02 , B64C1/26 , B64D17/80
CPC分类号： B64C39/024 , B64C1/26 , B64C3/56 , B64C2201/104 , B64C2201/107 , B64C2201/123 , B64C2201/127 , B64C2201/162 , B64C2201/185 , B64C2201/203 , B64D17/00 , B64D17/80
摘要： 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.

47. 发明申请

US20170096221A1 Modular and Morphable Air Vehicle 审中-公开
公开(公告)号：US20170096221A1
公开(公告)日：2017-04-06
申请号：US15205162
申请日：2016-07-08
申请人： Piasecki Aircraft Corporation
发明人： John W. Piasecki , Frederick W. Piasecki , Brian Geiger , Douglas Johnson , David Pitcairn
IPC分类号： B64C37/00 , B64D17/80 , B64C29/00 , B64C25/58 , B64C3/56 , B64C27/22 , B60F5/02 , B64D25/00
CPC分类号： B64C37/00 , B60F5/02 , B64C3/385 , B64C3/56 , B64C11/001 , B64C25/58 , B64C27/08 , B64C27/20 , B64C27/22 , B64C27/32 , B64C27/52 , B64C27/57 , B64C29/00 , B64C29/0033 , B64C39/00 , B64C39/02 , B64D17/80 , B64D25/00 , B64D2201/00 , G05D1/102
摘要： An unmanned air module includes one or more rotors, engines, a transmission and avionics. Any of several different ground modules may be attached to the air module. The air module may fly with and without the ground module attached. The ground module may be manned. The air module may have two rotors, which may be ducted fans. The air module may include a parachute, an airbag and landing gear.

48. 发明授权

US09613539B1 Damage avoidance system for unmanned aerial vehicle 有权
公开(公告)号：US09613539B1
公开(公告)日：2017-04-04
申请号：US14500826
申请日：2014-09-29
申请人： Amazon Technologies, Inc.
发明人： Jon Lewis Lindskog , Daniel Buchmueller , Samuel Park , Louis LeRoi LeGrand, III , Ricky Dean Welsh , Fabian Hensel , Christopher Aden Maynor , Ishwarya Ananthabhotla , Scott Michael Wilcox
IPC分类号： G08G5/04 , B64C39/02 , B64D45/00 , B64D17/80 , H02K7/18
CPC分类号： G08G5/04 , B64C39/02 , B64C2201/027 , B64C2201/108 , B64C2201/128 , B64D17/80 , B64D45/00 , G08G5/0008 , G08G5/0013 , G08G5/0026 , G08G5/0056 , G08G5/0069 , H02K7/183
摘要： This disclosure describes an unmanned aerial vehicle (“UAV”) and system that may perform one or more techniques for protecting objects from damage resulting from an unintended or uncontrolled impact by a UAV. As described herein, various implementations utilize a damage avoidance system that detects a risk of damage to an object caused by an impact from a UAV that has lost control and takes steps to reduce or eliminate that risk. For example, the damage avoidance system may detect that the UAV has lost power and/or is falling at a rapid rate of descent such that, upon impact, there is a risk of damage to an object with which the UAV may collide. Upon detecting the risk of damage and prior to impact, the damage avoidance system activates a damage avoidance system having one or more protection elements that work in concert to reduce or prevent damage to the object upon impact by the UAV.

49. 发明授权

US09551990B2 Unmanned aerial vehicle landing system 有权
标题翻译：无人机登陆系统
公开(公告)号：US09551990B2
公开(公告)日：2017-01-24
申请号：US14660145
申请日：2015-03-17
申请人： Sharper Shape Oy
发明人： Tero Heinonen
IPC分类号： G05D1/00 , B64D1/08 , B64C39/02 , B64D17/80 , G05D1/10 , G08G5/00
CPC分类号： G05D1/0011 , B64C39/024 , B64C2201/128 , B64D1/08 , B64D17/80 , G05D1/101 , G05D1/105 , G08G5/0056
摘要： The present disclosure provides an unmanned flying vehicle (UAV) operable in a plurality of operating modes including a normal operations mode, a safe landing mode and an emergency landing mode. The normal operations mode is initiated when no errors are detected in the system. The safe landing mode is initiated when one or more non-critical components of the UAV are in non-responsive mode or do not work as desired. The emergency landing mode is initiated when one or more critical components are in non-responsive mode or do not work as desired. Further, the safe landing mode overrides the normal operations mode and the emergency landing mode overrides both the normal operations mode and the safe landing mode.
摘要翻译：本公开提供了一种可操作于包括正常操作模式，安全着陆模式和紧急着陆模式的多种操作模式的无人驾驶飞行器（UAV）。当系统中没有检测到错误时，启动正常操作模式。当UAV的一个或多个非关键部件处于非响应模式或不按需要工作时，开始安全着陆模式。当一个或多个关键组件处于非响应模式或不按需要工作时，启动紧急着陆模式。此外，安全着陆模式覆盖正常操作模式，并且紧急着陆模式覆盖正常操作模式和安全着陆模式。

50. 发明申请

US20160304193A1 MULTI-ROTOR PERSONAL AIR VEHICLE WITH A CENTRAL LIFTING FAN 审中-公开
标题翻译：具有中央提升风扇的多转子个人空气车辆
公开(公告)号：US20160304193A1
公开(公告)日：2016-10-20
申请号：US14987198
申请日：2016-01-04
申请人： Jesse Antoine Marcel
发明人： Jesse Antoine Marcel
IPC分类号： B64C27/08 , B64C13/50 , B64C13/04 , B64C25/00 , G05D1/10 , B64C27/20 , B64D17/72 , B64D17/80 , B64C17/06 , B64C1/14 , B64C27/12
CPC分类号： B64C27/08 , B64C27/20 , B64D27/24 , G05D1/102 , Y02T50/62
摘要： A flying vehicle with a fuselage having a longitudinal axis, a cockpit extending substantially from the center of the fuselage, a left front wing extending from the fuselage, a right front wing extending from the fuselage, a left rear wing extending from the fuselage, a right rear wing extending from the fuselage. Each wing contains a rotor rotatably mounted and a direct drive brushless motor providing directional control of the vehicle. A centrally located ducted fan encompasses the cockpit and provides VTOL capabilities. The central location of the cockpit and central ducted fan aid in balance and stability. The central ducted fan is itself a brushless motor with the stator windings encapsulated in the ducted fan housing and rotor magnets within the fan. All motors and rotatable mounts are controlled by a fly-by-wire system integrated into a central computer with avionics allowing for autonomous flight.
摘要翻译：具有机身纵轴的飞行器，基本上从机身中心延伸的驾驶舱，从机身延伸的左前翼，从机身延伸的右前翼，从机身延伸的左后翼，右后翼从机身延伸。每个翼包含可旋转地安装的转子和提供车辆的方向控制的直接驱动无刷电动机。一个位于中心的管道风扇包含驾驶舱，并提供垂直起落架功能。驾驶舱和中央风扇的中心位置有助于平衡和稳定。中央风管风扇本身是一种无刷电动机，定子绕组封装在风扇风扇壳体内，转子磁体位于风扇内。所有电机和可旋转安装座均由集成到具有允许自主飞行的航空电子设备的中央计算机的线控系统控制。

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