公开(公告)号：US09505493B2

公开(公告)日：2016-11-29

申请号：US14222158

申请日：2014-03-21

Applicant: Brandon Borko

Inventor： Brandon Borko

IPC: B64F1/06 ,  B64C39/02 ,  B64F1/02 ,  B64F1/12 ,  G05D1/10 ,  B64F1/22

CPC classification number: B64C39/024 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/182 ,  B64C2201/20 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/06 ,  B64F1/12 ,  B64F1/222 ,  G05D1/101

Abstract: A system for facilitating automated landing and takeoff of an autonomous or pilot controlled hovering air vehicle with a cooperative underbody at a stationary or mobile landing place and an automated storage system used in conjunction with the landing and takeoff mechanism that stores and services a plurality of UAVs is described. The system is primarily characterized in that the landing mechanism is settable with 6 axes in roll, pitch, yaw, and x, y and z and becomes aligned with and intercepts the air vehicle in flight and decelerates the vehicle with respect to vehicle's inertial limits. The air vehicle and capture mechanism are provided with a transmitter and receiver to coordinate vehicle priority and distance and angles between landing mechanism and air vehicle. The landing and takeoff system has means of tracking the position and orientation of the UAV in real time. The landing mechanism will be substantially aligned to the base of the air vehicle. With small UAVs, their lifting capacity is limited. Reducing sensing and computation requirements by having the landing plate perform the precision adjustments for the landing operation allows for increased flight time and/or payload capacity.

Abstract translation: 一种用于促进自主着陆和起飞的自动着陆和起飞的系统，其具有在固定或移动着陆地点的协作车身，以及与着陆和起飞机构结合使用的自动存储系统，其存储和服务多个UAV 被描述。 该系统的主要特征在于，着陆机构可设置为具有卷轴，俯仰，偏航以及x，y和z的6个轴线，并与飞行中的空中车辆对准并截取，并相对于车辆的惯性极限使车辆减速。 飞行器和捕获机构设置有发射器和接收器，以协调车辆优先级，着陆机构和机动车辆之间的距离和角度。 着陆和起飞系统具有实时跟踪无人机的位置和方向的方法。 着陆机构将基本上与机动车辆的底座对准。 对于小型无人机，起重能力有限。 通过使着陆板执行着陆操作的精确调整来减少感测和计算要求，可以增加飞行时间和/或有效载荷。

公开(公告)号：US20160264259A1

公开(公告)日：2016-09-15

申请号：US15065626

申请日：2016-03-09

Applicant: Insitu, Inc.

Inventor： Matthew Robert Dickson ,  Craig Aram Thomasian

IPC: B64F1/02 ,  B64F1/04 ,  B64C39/02

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/108 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/04

Abstract: Line capture devices for unmanned aircraft, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a line capture device body having a line slot with an open end and a closed end. A retainer is positioned proximate to the line slot and has a rotor with a plurality of rotor arms positioned to extend at least partially across the line slot as the rotor rotates relative to the body. A joint rotatably couples the rotor to the body, and a ratchet device is operably coupled to the rotor to allow the rotor to rotate in a first direction and at least restrict the rotor arm from rotating in a second direction opposite the first. In other embodiments, the retainer can include other arrangements, for example, one or more wire-shaped elements.

公开(公告)号：US09340301B2

公开(公告)日：2016-05-17

申请号：US14569443

申请日：2014-12-12

Applicant: Insitu, Inc.

Inventor： Matthew Robert Dickson ,  Craig Aram Thomasian

IPC: B64F1/02 ,  B64F1/04 ,  B64C39/02

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/108 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/04

Abstract: Line capture devices for unmanned aircraft, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a line capture device body having a line slot with an open end and a closed end. A retainer is positioned proximate to the line slot and has a rotor with a plurality of rotor arms positioned to extend at least partially across the line slot as the rotor rotates relative to the body. A joint rotatably couples the rotor to the body, and a ratchet device is operably coupled to the rotor to allow the rotor to rotate in a first direction and at least restrict the rotor arm from rotating in a second direction opposite the first. In other embodiments, the retainer can include other arrangements, for example, one or more wire-shaped elements.

公开(公告)号：US20150307209A1

公开(公告)日：2015-10-29

申请号：US14569443

申请日：2014-12-12

Applicant: Insitu, Inc.

Inventor： Matthew Robert Dickson ,  Craig Aram Thomasian

IPC: B64F1/04 ,  B64C39/02

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/108 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/04

Abstract: Line capture devices for unmanned aircraft, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a line capture device body having a line slot with an open end and a closed end. A retainer is positioned proximate to the line slot and has a rotor with a plurality of rotor arms positioned to extend at least partially across the line slot as the rotor rotates relative to the body. A joint rotatably couples the rotor to the body, and a ratchet device is operably coupled to the rotor to allow the rotor to rotate in a first direction and at least restrict the rotor arm from rotating in a second direction opposite the first. In other embodiments, the retainer can include other arrangements, for example, one or more wire-shaped elements.

Abstract translation: 公开了用于无人机的线捕获装置，以及相关的系统和方法。 根据特定实施例的系统包括具有开口端和封闭端的线槽的线捕获装置主体。 保持器定位成靠近线槽并且具有转子，转子具有多个转子臂，转子臂定位成随着转子相对于主体旋转而至少部分地跨越线槽延伸。 关节可旋转地将转子连接到主体，并且棘轮装置可操作地联接到转子，以允许转子沿第一方向旋转，并且至少限制转子臂沿与第一方向相反的第二方向旋转。 在其他实施例中，保持器可以包括其它布置，例如一个或多个线形元件。

公开(公告)号：US20150298806A1

公开(公告)日：2015-10-22

申请号：US14485412

申请日：2014-09-12

Applicant: Google Inc.

Inventor： Damon Vander Lind ,  Thomas Van Alsenoy ,  Richard Wayne DeVaul

IPC: B64C39/02 ,  B64D3/00 ,  C07C29/141 ,  B63H9/06 ,  B64F1/36 ,  F03D9/00 ,  B64D47/00

CPC classification number: F03D9/32 ,  B63H9/0685 ,  B63H2009/0692 ,  B64C27/00 ,  B64C31/06 ,  B64C39/022 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/028 ,  B64C2201/145 ,  B64C2201/205 ,  B64C2201/206 ,  B64C2201/208 ,  B64D3/00 ,  B64D47/00 ,  B64F3/02 ,  C07C29/141 ,  F03D5/00 ,  F03D9/008 ,  F03D9/11 ,  F03D9/25 ,  F03D80/80 ,  F05B2240/917 ,  F05B2240/921 ,  H02K7/1838 ,  Y02E10/70 ,  Y02E10/725 ,  Y02E10/728

Abstract: A vehicle-based airborne wind turbine system having an aerial wing, a plurality of rotors each having a plurality of rotatable blades positioned on the aerial wing, an electrically conductive tether secured to the aerial wing and secured to a ground station positioned on a vehicle, wherein the aerial wing is adapted to receive electrical power from the vehicle that is delivered to the aerial wing through the electrically conductive tether; wherein the aerial wing is adapted to operate in a flying mode to harness wind energy to provide a first pulling force through the tether to pull the vehicle; and wherein the aerial wing is also adapted to operate in a powered flying mode wherein the rotors may be powered so that the turbine blades serve as thrust-generating propellers to provide a second pulling force through the tether to pull the vehicle

Abstract translation: 一种具有空中翼面的车载机载风力涡轮机系统，多个转子，每个转子具有位于空中飞翼上的多个可旋转叶片，固定在飞行器上并固定在位于车辆上的地面站的导电系绳， 其中所述空中翼适于从通过所述导电系绳传送到所述空中翼的车辆接收电力; 其中所述空中翼适于以飞行模式操作以利用风能以提供穿过所述系绳的第一拉力以拉动所述车辆; 并且其中所述空中翼还适于以动力飞行模式操作，其中所述转子可以被供电，使得所述涡轮机叶片用作推力产生螺旋桨以提供穿过所述系绳的第二拉力以拉动所述车辆

公开(公告)号：US08864069B2

公开(公告)日：2014-10-21

申请号：US14010176

申请日：2013-08-26

Applicant: Advanced Aerospace Technologies, Inc.

Inventor： William R. McDonnell

IPC: B64F1/02 ,  B64C25/68

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract translation: 一种发射和检索无人机（无人机）的方法（10）。 优选的发射方法是将无人机（10）运送到高度，使用类似于用来搭载高层游客的伞（8）。 无人机被丢弃，并在潜水中获得足够的空速，执行上升到等级控制飞行。 回收的首选方法是使UAV飞入并锁定在悬挂拖线（4）上或悬挂在拖绳上的电缆，然后被绞盘回到船（2）。

公开(公告)号：US20140252162A1

公开(公告)日：2014-09-11

申请号：US14197389

申请日：2014-03-05

Applicant: IGOR TELLER ,  PAVEL SOIFER

Inventor： IGOR TELLER

IPC: B64F1/10

CPC classification number: B64F1/10 ,  B64C2201/08 ,  B64C2201/205 ,  B64C2201/208

Abstract: A system for launching an unmanned aerial vehicle (UAV) from a moving platform, the system comprising: a platform configured to carry the UAV; one or more sensors configured to measure forces acting between said platform and said UAV in one or more directions; a mooring mechanism configured to moor said UAV to said platform; and a controller configured to: transmit at least one trimming command to said UAV based on measurements of said one or more sensors, and cause said mooring mechanism to release said UAV from said platform following the transmitting of the at least one trimming command, when the measurements of said one or more sensors indicate that a lift force is sufficiently close to a weight of the UAV.

Abstract translation: 一种用于从移动平台发射无人机（UAV）的系统，该系统包括：被配置为承载无人机的平台; 一个或多个传感器被配置为在一个或多个方向上测量在所述平台和所述UAV之间作用的力; 系泊机构，其构造成将所述无人机停泊在所述平台上; 以及控制器，其被配置为：基于所述一个或多个传感器的测量将至少一个修整命令发送到所述UAV，并且在所述至少一个修整命令的发送之后使所述系泊机构从所述平台释放所述UAV， 所述一个或多个传感器的测量指示提升力足够接近无人机的重量。

公开(公告)号：US08662441B2

公开(公告)日：2014-03-04

申请号：US13367494

申请日：2012-02-07

Applicant: David Powell ,  Earl Mark ,  John T. Houck ,  Keith Huber

Inventor： David Powell ,  Earl Mark ,  John T. Houck ,  Keith Huber

IPC: B64F1/10

CPC classification number: B64C39/024 ,  B63G8/30 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/205

Abstract: A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.

Abstract translation: 用于发射无人机（UAV）有效载荷的系统包括发射管，液体火箭和发射控制组件。 火箭定位在发射管中，并包含无人机的有效载荷。 增压组件可以包括部分地填充有液体的罐。 气瓶内充满压缩气体。 液体被气体预加压或在发射前与气体混合，使得在发射时，液体和气体推进阶段将火箭发射到阈值高度。 无人机有效载荷在达到阈值高度后部署。 可选的稳定管可以连接到发射管，其可以浮动用于水基操作。 可选的系绳可以连接到液体火箭，以在达到远地点之前停止其飞行。 无人机有效载荷不直接由气/液混合发射。 还公开了一种启动无人机有效载荷的方法。

公开(公告)号：US08567718B1

公开(公告)日：2013-10-29

申请号：US13783575

申请日：2013-03-04

Applicant: Advanced Aerospace Technologies, Inc.

Inventor： William Randall McDonnell

IPC: B64C25/68 ,  B64F1/02

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract translation: 一种发射和检索无人机（无人机）的方法（10）。 优选的发射方法是将无人机（10）运送到高度，使用类似于用来搭载高层游客的伞（8）。 无人机被丢弃，并在潜水中获得足够的空速，执行上升到等级控制飞行。 回收的首选方法是使UAV飞入并锁定在悬挂拖线（4）上或悬挂在拖绳上的电缆，然后被绞盘回到船（2）。

公开(公告)号：US20120138727A1

公开(公告)日：2012-06-07

申请号：US13097394

申请日：2011-04-29

Applicant: Jeremy F. Fisher

Inventor： Jeremy F. Fisher

IPC: F42B15/01 ,  B64D1/02 ,  B64C3/56 ,  F42B10/14

CPC classification number: F42B15/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205 ,  F41F1/08 ,  F41F3/042

Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.

Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身的发动机，并且可操作以通过飞行推进声纳浮标;以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置用于飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。