公开(公告)号：US06565041B1

公开(公告)日：2003-05-20

申请号：US10028956

申请日：2001-12-27

Applicant: Eric P. Young ,  John Reynolds ,  Mathew Curran ,  Danny Gast ,  Joseph Wurts

Inventor： Eric P. Young ,  John Reynolds ,  Mathew Curran ,  Danny Gast ,  Joseph Wurts

IPC: B64D1780

CPC classification number: B64D17/40 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/165 ,  B64C2201/185 ,  B64D17/54 ,  B64D17/76 ,  B64D17/80

Abstract: A parachute system for a miniature aircraft having a storable parachute mounted on an upper surface of the aircraft. The system includes a canopy having a stored condition and an expanded condition. A plurality of suspension lines have first ends connected to the periphery of the canopy and second ends connected to an elastic member. First and second risers are connected by their first ends to the upper surface of the aircraft between the front end and center of gravity on either side of the longitudinal axis and by their second ends to the elastic member. A restraint system releasably restrains the parachute in the stored condition on the top surface of the aircraft; and a release system coupled to the restraint system releases the parachute upon command such that aerodynamic forces will cause the parachute to open.

Abstract translation: 用于具有安装在飞行器的上表面上的可存放降落伞的微型飞机的降落伞系统。 该系统包括具有存储条件和扩展状态的遮篷。 多个悬挂线具有连接到顶盖的周边的第一端和连接到弹性构件的第二端。 第一和第二立管通过其第一端连接到飞行器的上表面，在纵轴的任一侧上的前端和重心之间，并且通过其第二端连接到弹性构件。 约束系统可释放地将降落伞限制在飞机顶表面上的储存状态; 并且联接到约束系统的释放系统根据命令释放降落伞，使得空气动力将使降落伞打开。

公开(公告)号：US06460810B2

公开(公告)日：2002-10-08

申请号：US09878903

申请日：2001-01-22

Applicant: Terry Jack James

Inventor： Terry Jack James

IPC: G05D100

CPC classification number: B64C39/024 ,  B64C29/0025 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185

Abstract: A device for programming industry standard autopilots by unskilled pilots. The effect of the invention is such that when the invention is employed in a flying body comprising an industry standard autopilot with a digital flight control system, the invention provides for the safe operation of any aircraft by an unskilled pilot. The device additionally affords skilled pilots a more rapid and simplified means of programming autopilots while in flight thus reducing a skilled pilot's cockpit workload for all aircraft flight and directional steering, way points, and aircraft flight functions reducing the possibility of pilot error so as to effect safer flight operations of an aircraft by affording a skilled pilot to direct aircraft steering and function while under continuous autopilot control.

公开(公告)号：US3669385A

公开(公告)日：1972-06-13

申请号：US3669385D

申请日：1970-10-08

Applicant: FAIRCHILD INDUSTRIES

Inventor： GLANTZ EARL ,  MCCOMAS JEAN W

IPC: B64C1/00 ,  B64C39/02 ,  B64D5/00 ,  B64C1/26

CPC classification number: B64D5/00 ,  B64C1/00 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/185

Abstract: An aircraft of improved of simplified construction having forward and aft generally cylindrical and substantially identical fuselage sections that are connected to a central fuselage section that houses an engine that has an inlet located above the forward fuselage section for powering the aircraft in flight. The central long axis of the aft fuselage section is located above the central long axis of the forward fuselage section. Wings are connected to the central fuselage section and a tail assembly is connected to the aft portion of the aft fuselage section. Many of the component parts of the aircraft are interchangeable and the aircraft is especially suited for use as a drone for towing aerial targets.

Abstract translation: 具有改进的简化结构的飞机具有前后大体上圆柱形和基本相同的机身部分，其连接到中央机身部分，该中央机身部分容纳具有位于前机身部分上方的入口的发动机，用于为飞行器提供动力。 后部机身部分的中心长轴位于前机身部分的中心长轴上方。 翼连接到中央机身部分，尾部组件连接到后机身部分的后部。 飞机的许多组成部分是可互换的，飞机特别适用于作为无人驾驶用于拖曳空中目标的飞机。

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。