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    Dual mode flight vehicle
    291.
    发明授权
    Dual mode flight vehicle 有权
    双模飞行器

    公开(公告)号：US09266609B1

    公开(公告)日：2016-02-23

    申请号：US14518770

    申请日：2014-10-20

    Applicant: Insitu, Inc.

    Inventor： Peter J. Kunz

    IPC: B64C27/22 ,  B64C29/00

    CPC classification number: B64C29/0008 ,  B64C17/04 ,  B64C29/0091 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104

    Abstract: A fixed wing flight vehicle has wing, a center-mounted propulsion unit and a pod that is moveable between a center of the wing and a displaced position at or near one end of the wing. When the pod is at or near the center of the wing, that is, having a center of mass at or near a thrust vector of the propulsion unit, the flight vehicle flies with the characteristics of a regular fixed wing aircraft. However, when the pod is translated to the position at or near an end of the wing, an overall center of mass of the flight vehicle is substantially offset from the thrust vector of the propulsion unit. This causes the flight vehicle to spin like a samara, e.g., a maple seed, so that the flight vehicle can take off or land in a very limited space, much like a helicopter.

    Abstract translation: 固定翼飞行器具有机翼，中心安装的推进单元和荚，其可以在翼的中心和机翼的一端或附近的位移位置之间移动。 当荚在机翼的中心处或附近时，即具有在推进单元的推力矢量处或附近的质心时，飞行器具有常规固定翼飞机的特征。 然而，当货舱被翻译到机翼末端或其附近的位置时，飞行车辆的整体质心基本上偏离推进装置的推力矢量。 这使得飞行车辆像萨马拉一样旋转，例如枫树种子，使得飞行车辆能够在非常有限的空间中起飞或着陆，就像直升机一样。

    Multi-role aircraft with interchangeable mission modules
    293.
    发明授权
    Multi-role aircraft with interchangeable mission modules 有权
    具有可互换任务模块的多角色飞机

    公开(公告)号：US09221532B2

    公开(公告)日：2015-12-29

    申请号：US14205156

    申请日：2014-03-11

    Applicant: Abe Karem

    Inventor： Abe Karem

    IPC: B64C1/00 ,  B64C3/56 ,  B64C1/06 ,  B64C39/10 ,  B64C39/02 ,  B64D37/00 ,  B64C1/26

    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。

    REMOTELY OR AUTONOMOUSLY PILOTED REDUCED SIZE AIRCRAFT WITH VERTICAL TAKE-OFF AND LANDING CAPABILITIES
    296.
    发明申请
    REMOTELY OR AUTONOMOUSLY PILOTED REDUCED SIZE AIRCRAFT WITH VERTICAL TAKE-OFF AND LANDING CAPABILITIES 审中-公开
    远程或自动直升机减少尺寸的飞机具有垂直起落架能力

    公开(公告)号：US20150225079A1

    公开(公告)日：2015-08-13

    申请号：US14054080

    申请日：2013-10-15

    Applicant: Douglas L. Starck ,  Errica M. Starck

    Inventor： Douglas L. Starck ,  Errica M. Starck

    IPC: B64C29/00 ,  B64C39/10 ,  B64D27/16

    CPC classification number: B64C39/10 ,  B64C29/0066 ,  B64C39/024 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/22 ,  B64D27/16 ,  Y02T50/12 ,  Y02T50/44

    Abstract: An aircraft having a vertical take-off and landing (“VTOL”) propulsion system aircraft, smaller than a standard manned aircraft and remotely or autonomously piloted. The aircraft comprises a symmetrical airfoil shape for the center body section that consists of ribs and spars maintaining an open area in the center. Situated within the open area of the center of the aircraft resides a duct system consisting of a ducted fan and five outlet vents. The main outlet vent functions as the exhaust exiting the aft portion of the aircraft, with the remaining four ducts used for the VTOL capabilities exiting the underside of the aircraft. The aircraft can have a range of wingspan, which can be scaled to satisfy needs and requirements, with a blended wing body that incorporates the inlet and duct system.

    Abstract translation: 具有垂直起飞和着陆（“VTOL”）推进系统飞机的飞机，小于标准载人飞机，远程或自主驾驶。 该飞行器包括对称的翼型形状，用于中心体部分，其由在中心保持开放区域的肋和翼梁组成。 位于飞机中心开放区域内的管道系统由管道风扇和五个出风孔组成。 主出口排气口作为离开飞机尾部的排气口，剩余的四个管道用于从飞机底面离开的垂直起降能力。 飞机可以具有一系列的翼展，其可以通过混合的翼体结合入口和管道系统而被缩放以满足需要和要求。

    Unmanned aerial vehicle having an improved aerodynamic configuration
    297.
    发明授权
    Unmanned aerial vehicle having an improved aerodynamic configuration 有权
    具有改进的空气动力学配置的无人机

    公开(公告)号：US08905358B2

    公开(公告)日：2014-12-09

    申请号：US13140233

    申请日：2009-12-01

    Applicant: Abraham Abershitz

    Inventor： Abraham Abershitz

    IPC: B64C3/58 ,  B64C39/10 ,  B64C39/00 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187

    Abstract: An unmanned air vehicle includes a body having front and rear sections with at least one pair of end plates connected to the body, wherein one end plate within the at least one pair of end plates is connected to the left side of the body and another end plate within the at least one pair of end plates is connected to the right side of the body, each end plate having upper and lower sections, wherein: a) the upper section is positioned above a mean line of the body; b) the lower section is positioned below the mean line of the body; and c) a ratio of the area of the upper section to the area of the lower section is less than 1.

    Abstract translation: 一种无人驾驶飞行器包括具有连接到主体的至少一对端板的前部和后部的主体，其中至少一对端板内的一个端板连接到主体的左侧，另一端 所述至少一对端板中的板连接到所述主体的右侧，每个端板具有上部和下部，其中：a）所述上部位于所述主体的平均线之上; b）下部位于身体的平均线之下; 和c）上部区域与下部区域的面积的比率小于1。

    Wing for an unmanned aircraft
    298.
    发明授权
    Wing for an unmanned aircraft 有权
    翼无人机

    公开(公告)号：US08827206B2

    公开(公告)日：2014-09-09

    申请号：US13655382

    申请日：2012-10-18

    Applicant: Gatewing NV

    Inventor： Maarten Maurits Van Speybroeck ,  Peter Hendrik Cosyn ,  Maarten Willem Vandenbroucke

    IPC: B64C1/00 ,  B64C3/00 ,  B64C5/00

    CPC classification number: B64C3/187 ,  A63H27/00 ,  B64C3/20 ,  B64C3/24 ,  B64C39/024 ,  B64C39/028 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/127

    Abstract: A single wing for an unmanned aircraft adapted for image acquisition, surveillance or other applications consists of a ribbed frame and a foam wherein the ribbed frame is integrated during molding for stiffness and strength. The foam has a container for holding the electric and/or electronic components. The foam constitutes the outer layer of the unmanned aircraft at impact side. The wing can be produced at low cost and low complexity in large volumes, increases the impact resistance and safety when used in civil areas, and is removable and disposable thereby enabling reuse of the electric and/or electronic components.

    Abstract translation: 适用于图像采集，监视或其他应用的无人驾驶飞机的单翼包括肋框架和泡沫，其中肋框架在模制期间被整合以获得刚度和强度。 泡沫具有用于保持电气和/或电子部件的容器。 泡沫构成冲击侧的无人驾驶飞机的外层。 机翼可以低成本和低复杂性大量生产，当在民用区域中使用时增加抗冲击性和安全性，并且是可拆卸的和一次性的，从而能够重复使用电气和/或电子部件。

    WING FOR AN UNMANNED AIRCRAFT
    300.
    发明申请
    WING FOR AN UNMANNED AIRCRAFT 有权
    为无人机飞行

    公开(公告)号：US20130228645A1

    公开(公告)日：2013-09-05

    申请号：US13655382

    申请日：2012-10-18

    Applicant: GATEWING NV

    Inventor： Maarten Maurits Van Speybroeck ,  Peter Hendrik Cosyn ,  Maarten Willem Vandenbroucke

    IPC: B64C3/18

    CPC classification number: B64C3/187 ,  A63H27/00 ,  B64C3/20 ,  B64C3/24 ,  B64C39/024 ,  B64C39/028 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/127

    Abstract: A single wing for an unmanned aircraft adapted for image acquisition, surveillance or other applications consists of a ribbed frame and a foam wherein the ribbed frame is integrated during molding for stiffness and strength. The foam has a container for holding the electric and/or electronic components. The foam constitutes the outer layer of the unmanned aircraft at impact side. The wing can be produced at low cost and low complexity in large volumes, increases the impact resistance and safety when used in civil areas, and is removable and disposable thereby enabling reuse of the electric and/or electronic components.

    Abstract translation: 适用于图像采集，监视或其他应用的无人驾驶飞机的单翼包括肋框架和泡沫，其中肋框架在模制期间被整合以获得刚度和强度。 泡沫具有用于保持电气和/或电子部件的容器。 泡沫构成冲击侧的无人驾驶飞机的外层。 机翼可以低成本和低复杂性大量生产，当在民用区域中使用时增加抗冲击性和安全性，并且是可拆卸的和一次性的，从而能够重复使用电气和/或电子部件。

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