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    Unmanned aircraft with failsafe system
    222.
    发明授权
    Unmanned aircraft with failsafe system 有权
    无人机与故障安全系统

    公开(公告)号：US09120579B2

    公开(公告)日：2015-09-01

    申请号：US14221126

    申请日：2014-03-20

    Applicant: Gatewing NV

    Inventor： Bjorn De Smet ,  Maarten De Moor ,  Peter Cosyn

    IPC: B64D31/06 ,  G05D1/06 ,  B64C39/00 ,  G05D1/00 ,  B64C11/00

    CPC classification number: B64D31/06 ,  B64C11/002 ,  B64C39/00 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64C2201/18 ,  G05D1/0055 ,  G05D1/0676

    Abstract: An unmanned aircraft configured to fall or crash in a controlled and safe manner. The unmanned aircraft includes a drive system to thrust the unmanned aircraft during a flight, and a reverse thrust system to reverse thrust the unmanned aircraft during a landing. The unmanned aircraft further includes a controller operationally coupled to the reverse thrust system, and a detector to detect and notify to the controller that the unmanned aircraft is in an uncontrolled situation during the flight. The controller is adapted to activate the reverse thrust system in order to reverse thrust the unmanned aircraft in-flight upon notification from the detector that the unmanned aircraft is in an uncontrolled situation.

    Abstract translation: 无人驾驶飞机配置为以受控和安全的方式坠落或碰撞。 无人驾驶飞机包括在飞行期间推动无人驾驶飞机的驱动系统，以及在着陆期间反向推动无人驾驶飞机的反向推力系统。 无人驾驶飞机还包括可操作地耦合到反向推力系统的控制器，以及检测器，用于检测并通知控制器，无人驾驶飞行器在飞行期间处于不受控制的情况。 控制器适于启动反向推力系统，以便在来自检测器的通知中无人驾驶飞机处于不受控制的情况下，使无人机在飞行中反向推进。

    Modular miniature unmanned aircraft with vectored thrust control
    223.
    发明授权
    Modular miniature unmanned aircraft with vectored thrust control 有权
    具有矢量推力控制的模块化微型无人机

    公开(公告)号：US08991750B2

    公开(公告)日：2015-03-31

    申请号：US14274938

    申请日：2014-05-12

    Applicant: Aurora Flight Sciences Corporation

    Inventor： Adam Woodworth ,  Brandon Suarez

    IPC: B64C15/00 ,  B64C39/02 ,  B64C29/00

    CPC classification number: B64C15/00 ,  B64C29/0033 ,  B64C39/02 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/18 ,  B64C2201/187 ,  B64C2201/201 ,  B64C2211/00

    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 module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring 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 thrust vectoring 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。 飞机包括机身，连接到机身后部的一对翅片，连接到机身底部的一对二面支架，第一推力矢量模块和第二推力矢量模块以及电子模块。 电子模块向两个推力矢量模块提供命令。 两个推力矢量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。 使用直接铰接的电动机作为推力矢量模块使飞机能够在宽范围的空速下执行紧半径的转弯。

    UNMANNED AIRCRAFT WITH FAILSAFE SYSTEM
    225.
    发明申请
    UNMANNED AIRCRAFT WITH FAILSAFE SYSTEM 有权
    具有失效系统的无人驾驶飞机

    公开(公告)号：US20150053824A1

    公开(公告)日：2015-02-26

    申请号：US14221126

    申请日：2014-03-20

    Applicant: Gatewing NV

    Inventor： Bjorn De Smet ,  Maarten De Moor ,  Peter Cosyn

    IPC: B64D31/00 ,  B64C19/00 ,  B64C39/02

    CPC classification number: B64D31/06 ,  B64C11/002 ,  B64C39/00 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64C2201/18 ,  G05D1/0055 ,  G05D1/0676

    Abstract: An unmanned aircraft comprises: a drive system to thrust the unmanned aircraft during a flight; a reverse thrust system to reverse thrust the unmanned aircraft during a landing; a controller operationally coupled to the reverse thrust system; and a detector to detect and notify to the controller that the unmanned aircraft is in an uncontrolled situation during the flight. The controller is then adapted to activate the reverse thrust system in order to reverse thrust the unmanned aircraft in-flight upon notification from the detector that the unmanned aircraft is in an uncontrolled situation.

    Abstract translation: 无人驾驶飞机包括：在飞行期间推动无人驾驶飞机的驱动系统; 反向推力系统在着陆期间反推无人飞机; 控制器可操作地耦合到反向推力系统; 以及检测器，用于检测并通知控制器，无人驾驶飞机在飞行期间处于不受控制的情况。 然后，控制器适于激活反向推力系统，以便在来自检测器的通知中无人驾驶飞机处于不受控制的情况下反向推动无人驾驶飞行器。

    INVERTED-LANDING AIRCRAFT
    226.
    发明申请
    INVERTED-LANDING AIRCRAFT 有权
    反转式飞机

    公开(公告)号：US20140350748A1

    公开(公告)日：2014-11-27

    申请号：US13261813

    申请日：2012-08-16

    Applicant: Christopher E. Fisher ,  Thomas Robert Szarek ,  Justin B. McAllister ,  Pavel Belik

    Inventor： Christopher E. Fisher ,  Thomas Robert Szarek ,  Justin B. McAllister ,  Pavel Belik

    IPC: B64C39/02 ,  G05D1/08

    CPC classification number: G01C5/005 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/18 ,  B64D47/08 ,  G05D1/0011 ,  G05D1/0676 ,  G05D1/0808 ,  G05D1/0816

    Abstract: An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.

    Abstract translation: 定义直立方向和倒置方向的飞机，地面站; 以及用于远程控制飞机飞行的控制系统。 地面站具有自动地面功能，使飞机以反方向反转，失速和可控地降落，以保护从飞机向下延伸的有效载荷和舵。 在直立方向，地面站描绘从第一架飞机摄像机的视图。 当切换到倒置方向时：（1）地面站描绘从第二架飞机照相机的视图，（2）飞机切换红色和绿色翼灯的颜色，将副翼延伸为反转翼片，（3） 控制系统适应地面站控制器的倒置方向。 飞机起落架是当飞机处于直立方向时位于机翼上方的扩展的聚丙烯垫。

    Vertical takeoff and landing (VTOL) small unmanned aerial system for monitoring oil and gas pipelines
    227.
    发明授权
    Vertical takeoff and landing (VTOL) small unmanned aerial system for monitoring oil and gas pipelines 有权
    垂直起降（VTOL）用于监测油气管道的小型无人驾驶空中系统

    公开(公告)号：US08880241B2

    公开(公告)日：2014-11-04

    申请号：US13772161

    申请日：2013-02-20

    Applicant: Farrokh Mohamadi

    Inventor： Farrokh Mohamadi

    IPC: G05D1/10 ,  G01S19/01 ,  G01C21/00 ,  B64C27/10 ,  B64C19/00 ,  B64C29/00 ,  B64D47/08 ,  B64C39/02

    CPC classification number: B64C19/00 ,  B64C29/00 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/145 ,  B64C2201/146 ,  B64C2201/18 ,  B64D47/08

    Abstract: Extended-range monitoring and surveillance of facilities and infrastructure—such as oil, water, and gas pipelines and power lines—employs autonomous vertical take-off and landing (VTOL) capable, small unmanned aerial system (sUAS) aircraft and docking platforms for accommodating the sUAS aircraft. Monitoring and surveillance of facilities using one or more embodiments may be performed continually by the sUAS flying autonomously along a pre-programmed flight path. The sUAS aircraft may have an integrated gas collector and analyzer unit, and capability for downloading collected data and analyzer information from the sUAS aircraft to the docking platforms. The gas collector and analyzer unit may provide remote sensing and in-situ investigation of leaks and other environmental concerns as part of a “standoff” (e.g., remote from operators of the system or the facilities) survey that can keep field operators out of harm's way and monitor health of the environment.

    Abstract translation: 设施和基础设施（如石油，水，天然气管道和电力线）的远程监控和监视 - 采用自主垂直起降（VTOL）能力，小型无人驾驶空中系统（sUAS）飞机和对接平台 sUAS飞机。 使用一个或多个实施例的设施的监视和监视可以通过沿着预编程的飞行路径自主地飞行的sUAS来连续执行。 sUAS飞机可能具有集成的气体收集器和分析仪单元，以及将收集的数据和分析仪信息从sUAS飞机下载到对接平台的能力。 气体收集器和分析器单元可以提供对泄漏和其他环境问题的远程感测和现场调查，作为“对抗”（例如，远离系统操作员或设施的）的调查的一部分，这可以使现场操作员不受伤害 方式和监测环境的健康。

    Modular miniature unmanned aircraft with vectored thrust control
    228.
    发明授权
    Modular miniature unmanned aircraft with vectored thrust control 有权
    具有矢量推力控制的模块化微型无人机

    公开(公告)号：US08721383B2

    公开(公告)日：2014-05-13

    申请号：US12556225

    申请日：2009-09-09

    Applicant: Adam Woodworth ,  Brandon Suarez

    Inventor： Adam Woodworth ,  Brandon Suarez

    IPC: B64C13/00

    CPC classification number: B64C15/00 ,  B64C29/0033 ,  B64C39/02 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/18 ,  B64C2201/187 ,  B64C2201/201 ,  B64C2211/00

    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 module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring 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 thrust vectoring 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。 飞机包括机身，连接到机身后部的一对翅片，连接到机身底部的一对二面支架，第一推力矢量模块和第二推力矢量模块以及电子模块。 电子模块向两个推力矢量模块提供命令。 两个推力矢量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。 使用直接铰接的电动机作为推力矢量模块使飞机能够在宽范围的空速下执行紧半径的转弯。

    MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL
    229.
    发明申请
    MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL 有权
    具有矢量控制的模块化MINIATURE UNIMANNED飞机

    公开(公告)号：US20140061390A1

    公开(公告)日：2014-03-06

    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: B64C15/00

    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。

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