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    UNMANNED AIRCRAFT WITH FAILSAFE SYSTEM
    182.
    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。

    UNMANNED AERIAL VEHICLE AND METHODS FOR CONTROLLING SAME
    183.
    发明申请
    UNMANNED AERIAL VEHICLE AND METHODS FOR CONTROLLING SAME 有权
    无人驾驶的航空器及其控制方法

    公开(公告)号：US20140316616A1

    公开(公告)日：2014-10-23

    申请号：US14204634

    申请日：2014-03-11

    Applicant: Airphrame, Inc.

    Inventor： Bret Kugelmass

    IPC: G05D1/10 ,  H04N7/18 ,  G06T11/60

    CPC classification number: H04Q9/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/145 ,  G05D1/0088 ,  G05D1/0094 ,  G05D1/042 ,  G05D1/101 ,  G05D1/104 ,  G06T1/0014 ,  G06T11/206 ,  G06T11/60 ,  G08G5/0013 ,  G08G5/0039 ,  G08G5/0069 ,  H04N7/181 ,  H04Q2209/40 ,  H04W28/065

    Abstract: One variation of a method for imaging an area of interest includes: within a user interface, receiving a selection for a set of interest points on a digital map of a physical area and receiving a selection for a resolution of a geospatial map; identifying a ground area corresponding to the set of interest points for imaging during a mission; generating a flight path over the ground area for execution by an unmanned aerial vehicle during the mission; setting an altitude for the unmanned aerial vehicle along the flight path based on the selection for the resolution of the geospatial map and an optical system arranged within the unmanned aerial vehicle; setting a geospatial accuracy requirement for the mission based on the selection for the mission type; and assembling a set of images captured by the unmanned aerial vehicle during the mission into the geospatial map.

    Abstract translation: 用于对感兴趣区域成像的方法的一个变型包括：在用户界面内，接收对物理区域的数字地图上的一组感兴趣点的选择，并且接收对于地理空间地图的分辨率的选择; 在任务期间识别与所述一组感兴趣点成像成对应的地面区域; 在飞行任务期间通过无人驾驶飞行器在地面上产生飞行路线，以执行; 基于对地理空间地图的分辨率的选择和布置在无人机内的光学系统，设置沿着飞行路径的无人机的高度; 根据任务类型的选择，为任务确定地理空间精度要求; 并将任务期间由无人驾驶飞行器捕获的一组图像组装到地理空间图中。

    Multi-Role Aircraft With Interchangeable Mission Modules
    184.
    发明申请
    Multi-Role Aircraft With Interchangeable Mission Modules 审中-公开
    具有可互换任务模块的多角色飞机

    公开(公告)号：US20140231593A1

    公开(公告)日：2014-08-21

    申请号：US14205156

    申请日：2014-03-11

    Applicant: Abe Karem

    Inventor： Abe Karem

    IPC: B64C1/00 ,  B64D37/00 ,  B64C39/10 ,  B64C39/02 ,  B64C3/56 ,  B64C1/06

    CPC classification number: B64C39/10 ,  B64C1/00 ,  B64C1/0009 ,  B64C1/061 ,  B64C1/065 ,  B64C1/26 ,  B64C3/56 ,  B64C25/10 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/126 ,  B64C2211/00 ,  B64D37/00 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/43

    Abstract: A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.

    Abstract translation: 飞行可操作的，真正模块化的飞机具有飞行器核心，一个或多个外翼构件，机身，驾驶舱，前后联轴器，尾翼和尾翼部分可在其运行寿命期间可拆卸地联接和/或更换 的飞机。 在优选实施例中，飞机核心容纳推进发动机，航空电子设备，至少80％的燃料和所有起落架。 飞机核心优选地构造有弯曲的前向和后部复合翼梁，其在中心部分处传递载荷，同时容纳中翼构造。 飞机核心优选地具有大的中心空间，其大小可互换地携带军械发射器，监视有效载荷，电子对抗措施和其他类型的货物。 考虑的飞机可能相当大，例如具有至少80英尺的翼展。

    Modular miniature unmanned aircraft with vectored thrust control
    185.
    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
    186.
    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。

    Flying-wing aircraft
    187.
    发明授权
    Flying-wing aircraft 有权
    飞翼飞机

    公开(公告)号：US08602348B2

    公开(公告)日：2013-12-10

    申请号：US12865429

    申请日：2009-02-02

    Applicant: Ashley Christopher Bryant

    Inventor： Ashley Christopher Bryant

    IPC: B64C15/12 ,  B64C29/00 ,  B64C39/10

    CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/162 ,  B64C2201/165

    Abstract: A vertical take-off and landing flying-wing aircraft has a pair of thrust-vectoring propulsion units mounted fore and aft of the aircraft pitch axis on strakes at opposite extremities of the wing-structure, with the fore unit below, and the aft unit above, the wing-structure. The propulsion units are pivoted to the strakes, either directly or via arms, for individual angular displacement for thrust-vectored maneuvering of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. When arms are employed, the arms of fore and aft propulsion units are intercoupled via chain drives or linkages. The wing-structure may have fins, slats and flaps and other aerodynamic control-surfaces, and enlarged strakes may incorporate rudder surfaces. Only one propulsion unit may be mounted at each extremity and additional fan units may be used.

    Abstract translation: 垂直起飞和着陆的飞翼飞机具有一对推力矢量推进装置，其在机翼结构的相对两端的前翼和后部单元的前后悬架的飞机俯仰轴上前后安装 以上，翼结构。 推进单元直接或经由臂枢转到斜面，用于单独的角位移，用于以偏航，俯仰和滚动以及用于悬停和向前和向后飞行的推力向导操纵飞行器。 当使用武器时，前后推进单元的臂通过链条驱动器或连杆相互联接。 机翼结构可以具有翅片，板条和翼片以及其它空气动力学控制表面，并且扩大的履带可以包括舵面。 每个末端只能安装一个推进装置，也可以使用额外的风扇装置。

    ANNULAR AIRBORNE VEHICLE
    189.
    发明申请
    ANNULAR AIRBORNE VEHICLE 有权

    公开(公告)号：US20120305714A1

    公开(公告)日：2012-12-06

    申请号：US13466327

    申请日：2012-05-08

    Applicant: Harry George Dennis Gosling

    Inventor： Harry George Dennis Gosling

    IPC: B64C39/06

    CPC classification number: B64C39/062 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/162

    Abstract: An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device mounted to the wing-body and positioned on a second side of the plane including the wing-body axis.

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