公开(公告)号：US20160258456A1

公开(公告)日：2016-09-08

申请号：US15059604

申请日：2016-03-03

Applicant: Becklin Holdings, Inc.

Inventor： Matthew P. Phelan ,  Adrian P. Tayne

IPC: F16B2/10 ,  B65D85/68 ,  B64C39/02

CPC classification number: F16B2/10 ,  B64C39/024 ,  B64C2201/201 ,  B65D85/68 ,  B65D2585/687 ,  F16B43/003 ,  F16M9/00

Abstract: A retention system includes a base supporting a wing spar and a post extending through the base from a first side of the base to a second side of the base. The post inserts through an aperture in the spar. A stop is selectively securable to the post over the second side of the base. A locking member engages the post on the first side of the base. The locking member is configured to selectively move the post from an unlocked position to a locked position in which the post is withdrawn toward the first side relative to the unlocked position. A biasing member encircles the post and is positioned between the stop and the second side. When the locking member is in a closed position the biasing member expands to engage the aperture and resist movement of the wing spar. A plurality of cradles may support the wing.

公开(公告)号：US20160229299A1

公开(公告)日：2016-08-11

申请号：US14504828

申请日：2014-10-02

Applicant: Swift Engineering, Inc.

Inventor： Andrew Streett

IPC: B60L11/18 ,  B64C39/02 ,  G05D1/00 ,  H02J7/35

CPC classification number: B60L11/182 ,  B64C39/024 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/222 ,  G05D1/0011 ,  G05D1/0088 ,  H02J7/35

Abstract: A transportable ground station for a UAV includes a container in which the UAV may be transported and housed. The container includes a wireless or contact-based recharging station that recharges the UAV's batteries or other power sources after the UAV returns from a mission. The recharging station may be directly or indirectly connected to one or more solar panels that generate energy to power the recharging station. The ground station may be deployed virtually anywhere, from any vehicle (e.g., plane, train, boat, truck, etc.), and may operate over an extended period of time without human intervention.

Abstract translation: 无人机的可运输地面站包括可以运输和收纳无人机的容器。 该集装箱包括一个无线或接触式充电站，在无人机从任务返回后，为无人机的电池或其他电源充电。 充电站可以直接或间接地连接到一个或多个太阳能电池板，该太阳能电池板产生能量以为充电站供电。 地面站几乎可以从任何车辆（例如，飞机，火车，船，卡车等）部署到任何地方，并且可以在较长时间内进行操作而无需人为干预。

公开(公告)号：US20160039536A1

公开(公告)日：2016-02-11

申请号：US14887675

申请日：2015-10-20

Applicant: AEROVIRONMENT, INC.

Inventor： Carlos Thomas Miralles ,  Guan H. Su ,  Alexander Andryukov ,  John McNeil

IPC: B64F1/04 ,  B64C39/02

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/201 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14

Abstract: An unmanned aerial vehicle (UAV) launch tube (100)that comprises at least one inner layer of prepreg substrate (370) disposed about a right parallelepiped aperture (305), at least one outer layer of prepreg substrate (380) disposed about the right parallelepiped aperture, and one or more structural panels (341-344) disposed between the at least one inner layer of prepreg substrate (340) and the at least one outer layer of prepreg substrate (380). An unmanned aerial vehicle (UAV) launch tube (100) that comprises a tethered sabot (700,740) configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot(700,740) dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot (700,740) is hollow having an open end oriented toward a high pressure volume and a tether (740) attached within a hollow (910) of the sabot(700) and attached to the inner wall retaining the high pressure volume or attach to the inner base wall (1013). A system comprising a communication node (1500-1505) and a launcher (1520) comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node (1500-1505).

Abstract translation: 一种无人驾驶飞行器（UAV）发射管（100），其包括设置在右平行六面体孔（305）周围的至少一个预浸料衬底内层（370），至少一个预浸料衬底外周层 平行六面体的孔和设置在至少一层预浸料衬底（340）的内层与至少一层预浸料衬底（380）之间的一个或多个结构面板（341-344）。 一种无人驾驶飞行器（UAV）发射管（100），其包括被构造成接合由内壁限定的发射器体积内的UAV的拴系的膛体（700,740），所述拴系的炮（700,740）的尺寸被设计成在内部提供压力密封 并且其中所述系留式破坏物（700,740）是中空的，具有朝向高压容积定向的开口端和连接在所述破坏物（700）的中空（910）内的系绳（740），并且附接到 所述内壁保持高压容积或附接到所述内底壁（1013）。 包括通信节点（1500-1505）和发射器（1520）的系统，其包括处于预发射状态的无人驾驶飞行器（UAV），其被配置为接收并响应来自通信节点（1500-1505）的命令输入。

公开(公告)号：US20150266578A1

公开(公告)日：2015-09-24

申请号：US14018493

申请日：2013-09-05

Applicant: Raytheon Company

Inventor： Erick W. Elkins ,  Matthew Glenn Murphy ,  Scott D. Thomas

IPC: B64D1/12 ,  B64C39/02

CPC classification number: B64D1/12 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/206

Abstract: A container is used to launch a small aircraft, such as an unmanned aerial vehicle (UAV), from a host aircraft. The container protects the UAV from stresses during the initial ejection from a launcher that is part of the host aircraft. The initial stresses may be due to turbulence in the vicinity of the host aircraft, high airspeed, and/or tumbling that may result from the ejection from the host aircraft moving at a high airspeed. The container may deploy a drag device, such as a drogue chute, to slow the container down and reorient the container, prior to deployment of the UAV from the container. During the time between ejection from the host aircraft and deployment from the container, the UAV may be powered up and acquire data, such as global positioning system (GPS) data, to allow the UAV a “hot start” enabling immediate mission commencement.

Abstract translation: 一个集装箱用于从一架主机上发射一架小型飞机，如无人飞行器（UAV）。 该容器保护无人机在最初从作为主机的一部分的发射器弹出之前受到压力。 初始应力可能是由于主机飞机附近的湍流，高空速和/或可能由主飞机从高空速下移动而导致的翻滚造成的。 在从容器部署UAV之前，容器可以部署拖动装置，例如锥形滑槽，以使容器向下减速并重新定向容器。 在从主机飞行器和从集装箱部署之间的时间内，UAV可以被加电并且获取诸如全球定位系统（GPS）数据的数据，以允许UAV“启动”，从而能够立即启动任务。

公开(公告)号：US09114871B2

公开(公告)日：2015-08-25

申请号：US13954362

申请日：2013-07-30

Applicant: Aurora Flight Sciences Corporation

Inventor： Adam John Woodworth ,  James Peverill ,  Greg Vulikh ,  Jeremy Scott Hollman

IPC: B64D27/00 ,  B64C1/30 ,  B64D27/26 ,  B64D9/00 ,  B64C19/00 ,  B64D1/14 ,  B64C15/00 ,  B64C39/02 ,  A63H27/00

CPC classification number: B64C1/30 ,  A63H27/001 ,  A63H27/02 ,  B64C15/00 ,  B64C19/00 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/18 ,  B64C2201/187 ,  B64C2201/201 ,  B64D1/14 ,  B64D9/00 ,  B64D27/26

Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

Abstract translation: 描述了一种无人驾驶飞机。 飞行器包括机身，连接到机身的后部的一对翼片，连接到机身的底部的一对二面支架，第一推力矢量（“T / V”）模块和第二T / V模块，以及电子模块。 电子模块向两个T / V模块提供命令。 两个T / V模块被配置为通过直接控制飞行器的俯仰，滚动和偏航中的每一个的推力矢量来向飞行器提供侧向和纵向控制。 使用直接连接的电动机作为T / V模块，使飞机能够在大范围的空速下执行紧半径的转弯。

公开(公告)号：US20140027579A1

公开(公告)日：2014-01-30

申请号：US13790655

申请日：2013-03-08

Applicant: Gerald Miller ,  James Stewart

Inventor： Gerald Miller ,  James Stewart

IPC: B64C19/00

CPC classification number: B64C19/00 ,  B64C39/028 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/201 ,  B64C2201/203 ,  F41F3/042 ,  F41G7/008 ,  F41G7/2206 ,  F41G7/2253 ,  F41G7/2293 ,  F42B12/20 ,  F42B12/365 ,  F42B15/01 ,  F42B15/10 ,  G05D1/12

Abstract: An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder.

Abstract translation: 一种无人驾驶飞行器，其包括在搜索操作模式下操作的控制器，其中采集传感器的接收器搜索目标并使飞行控制表面以向下的螺旋路径引导车辆，其中采集传感器检测到的操作的终端操作 目标并使飞行控制表面引导车辆朝向目标;以及激活操作模式，其中触发传感器检测到与车辆预定距离内的目标，并且控制器激活响应者。

公开(公告)号：US08505430B2

公开(公告)日：2013-08-13

申请号：US13229377

申请日：2011-09-09

Applicant: Carlos Thomas Miralles ,  Guan H. Su ,  Oleksandr Andryukov ,  John McNeil

Inventor： Carlos Thomas Miralles ,  Guan H. Su ,  Oleksandr Andryukov ,  John McNeil

IPC: F41F3/04

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/201 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14

Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

Abstract translation: 一种无人驾驶飞行器（UAV）发射管，其包括被配置为将UAV接合在由内壁限定的发射器体积内的拴系的艉板，所述拴系的突出部的尺寸被设计成在内壁处提供压力密封并且系在内壁上，以及 其中所述系留式破碎器是中空的，其具有朝向高压容积的开口端，并且连接在所述破坏物的中空部内并且附接到保持高压容积的内壁或附接到内底壁的内壁的系绳。 一种包括通信节点和发射器的系统，其包括处于预发射状态的无人驾驶飞行器（UAV），其被配置为接收并响应来自所述通信节点的命令输入。

公开(公告)号：US08444082B1

公开(公告)日：2013-05-21

申请号：US12859639

申请日：2010-08-19

Applicant: Richard J Foch

Inventor： Richard J Foch

IPC: B64C3/56

CPC classification number: B64C3/10 ,  B64C23/072 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  Y02T50/12 ,  Y02T50/164

Abstract: An air vehicle can be folded into or unfolded from a compact tubular storage container without assembly or disassembly of the air vehicle. The air vehicle includes a fuselage, two aerodynamic surfaces rotatably mounted on the fuselage along a common axis with at least one pivot mechanism, and at least one spring mechanism configured to deploy the aerodynamic surfaces so they extend outwardly from the body. In a stowed configuration, both aerodynamic surfaces are parallel to the fuselage for stowage of the aircraft in a container. Each aerodynamic surface has a winglet located at an outer edge of the tail portion of the aerodynamic surface, and a rudder on each winglet. The aircraft does not require a vertical stabilizer or rudder system on the fuselage. An outer backward-swept wing portion can be unfolded from the outer edge of each aerodynamic surface to increase the wing aspect ratio.

Abstract translation: 空中交通工具可以从紧凑的管状存储容器折叠进入或展开，而不需要组装或拆卸空中交通工具。 机动车辆包括机身，具有至少一个枢转机构的共同轴线可旋转地安装在机身上的两个空气动力学表面，以及至少一个弹簧机构，其构造成展开空气动力学表面，使得它们从主体向外延伸。 在收起的构造中，两个空气动力学表面平行于机身，用于将飞行器存储在容器中。 每个空气动力学表面具有位于空气动力学表面的尾部的外边缘处的小翼和在每个小翼上的舵。 飞机在机身上不需要垂直稳定器或方向舵系统。 外侧后掠翼部分可以从每个空气动力学表面的外边缘展开，以增加机翼纵横比。

公开(公告)号：US08146855B2

公开(公告)日：2012-04-03

申请号：US12230638

申请日：2008-09-03

Applicant: Anvar Ismailov

Inventor： Anvar Ismailov

IPC: B64C3/56

CPC classification number: F42B10/64 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208 ,  F42B10/14

Abstract: An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.

Abstract translation: 用于军事，陆上安全等操作的无人驾驶飞行器包括设置有可折叠翼的机身，其具有前缘翼片和后缘副翼，其可以在发射时上升操作以控制翼折叠的飞行图案，翼部署成 在适当的时候打开展开位置。 车辆被容纳在发射的荚内，并且提供着陆甲板以在车辆返回陆地时减速和阻止车辆。

公开(公告)号：US20120043411A1

公开(公告)日：2012-02-23

申请号：US13149576

申请日：2011-05-31

Applicant: Peter Joseph Beck ,  Nikhil Raghu

Inventor： Peter Joseph Beck ,  Nikhil Raghu

IPC: F42B15/08 ,  F42B10/14 ,  H04N7/18 ,  B64D17/80

CPC classification number: B64C39/024 ,  B64C2201/046 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/201 ,  F41F3/042 ,  F41F3/045 ,  F42B15/08 ,  F42B15/10 ,  H04N7/183

Abstract: A UAV includes: a rocket body, having a rocket motor and a payload section; a parachute coupled with the payload section; an image capture device; a magnetometer to provide a compass reference for images taken from the image capture device; and a transmitter to communicate image and compass data to a remote receiver. Compass bearings are overlaid on image data from the image capture device. A handheld launch unit includes an ignition system, having an activation mechanism and an igniter to activate the rocket motor. A safety pin prevents electrical current from flowing to the igniter until the pin is removed. An accelerometer and/or magnetometer determines an angular orientation of the UAV. Software verifies that the angle is within a user-defined safety limit before activating the igniter.

Abstract translation: 无人机包括：具有火箭发动机和有效载荷部分的火箭主体; 与有效载荷部分相连的降落伞; 图像捕获装置; 磁力计，用于为从图像捕获装置拍摄的图像提供罗盘参考; 以及用于将图像和罗盘数据传送到远程接收器的发射器。 指南针轴承覆盖在图像捕获装置的图像数据上。 手持式发射单元包括具有启动机构和点火器来激活火箭发动机的点火系统。 一个安全销防止电流流到点火器，直到引脚被移除。 加速度计和/或磁力计确定无人机的角度取向。 激活点火器之前，软件将验证角度在用户定义的安全极限内。