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    Delta M-Wing Unmanned Aerial Vehicle
    151.
    发明申请
    Delta M-Wing Unmanned Aerial Vehicle 审中-公开
    三角洲M型无人机

    公开(公告)号：US20150367932A1

    公开(公告)日：2015-12-24

    申请号：US14046927

    申请日：2013-10-05

    Applicant: Dillon Mehul Patel

    Inventor： Dillon Mehul Patel

    IPC: B64C3/10 ,  B64C25/10 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104

    Abstract: An aerial vehicle compromising of a streamline delta wing structure, an M-wing structure accomplished through dihedral and dropped wing tips, and a variable incidence tail. The structure of the vehicle produces high lift and drag while maintaining stability and control at high angles of attack.

    Abstract translation: 一种航空器损坏流线型三角翼结构，通过二面和落下的翼尖实现的M翼结构和可变入射尾。 车辆的结构产生高的提升和拖动，同时保持高的迎角的稳定性和控制。

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH VARIABLE WING GEOMETRY
    153.
    发明申请
    VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH VARIABLE WING GEOMETRY 有权
    垂直起落架和可变轨迹飞机

    公开(公告)号：US20150284075A1

    公开(公告)日：2015-10-08

    申请号：US14243540

    申请日：2014-04-02

    Applicant: Sikorsky Aircraft Corporation

    Inventor： Mark R. Alber

    IPC: B64C27/22 ,  B64C3/42 ,  B64C39/02 ,  B64C29/00 ,  B64C25/10

    CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

    Abstract: A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage, inboard wings extending from opposite sides of the fuselage to define a support plane and engine nacelles disposed along the wings. Each of the wings includes ground alighting elements and a variable geometry such that a portion of the ground alighting elements are alignable with the support plane during in-flight conditions and displaceable from the support plane.

    Abstract translation: 提供垂直起飞和降落（VTOL）飞机，并包括机身，内侧翅膀从机身的相对侧延伸，以限定沿机翼设置的支撑平面和发动机舱。 每个翼包括地面下落元件和可变几何形状，使得地面下落元件的一部分在飞行状态期间与支撑平面对准并且可从支撑平面移位。

    Launch Tube Restraint System For Unmanned Aerial Vehicle (UAV)
    154.
    发明申请
    Launch Tube Restraint System For Unmanned Aerial Vehicle (UAV) 有权
    无人机（UAV）发射管约束系统

    公开(公告)号：US20150267996A1

    公开(公告)日：2015-09-24

    申请号：US14281680

    申请日：2014-05-19

    Applicant: AeroVironment, Inc.

    Inventor： Guan H. Su ,  Marcos Henry Rodriguez

    IPC: F41F3/00 ,  B64C39/02

    CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/201 ,  B64F1/06 ,  F41B11/80 ,  F41F3/00 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

    Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

    Abstract translation: 公开了一种无人驾驶飞行器（UAV）发射装置，其包括具有外表面的UAV（400），从外表面延伸的飞行器（AV）突片（510），包含无人机（400）的管（440） ），所述管（440）包括构造成可控制地阻碍所述AV突片（510）经过所述突片止动件（515）的移动的突片止动件（515），以及一对相对的突片引导件（700,705），其被配置为 AV选项卡（510），用于在制表位（515）上移动。

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    155.
    发明申请
    VERTICAL TAKE-OFF AND LANDING AIRCRAFT 有权
    垂直起落架和飞机

    公开(公告)号：US20150102157A1

    公开(公告)日：2015-04-16

    申请号：US14460013

    申请日：2014-08-14

    Applicant: SWIFT ENGINEERING, INC.

    Inventor： Robert Godlasky ,  Nate Ogawa ,  Andrew Streett

    IPC: B64C29/00 ,  B64C3/56 ,  B64D27/02

    CPC classification number: B64D27/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

    Abstract: A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

    Abstract translation: 垂直起落飞行器包括至少一个牵引转子和至少一个推动器转子。 例如，VTOL飞机可以包括三个牵引转子和一个推动器转子。 静态牵引器和推动器转子的组合允许转子相对于垂直起降飞机的机翼和机身保持在固定方向（即，不需要移动的机械轴），同时能够使飞机从基本垂直的飞行 到达基本水平的飞行路径的路径。

    Long endurance vertical takeoff and landing aircraft
    156.
    发明授权
    Long endurance vertical takeoff and landing aircraft 有权
    长寿命垂直起降飞机

    公开(公告)号：US08991751B2

    公开(公告)日：2015-03-31

    申请号：US13429156

    申请日：2012-03-23

    Applicant: Mark Allan Page ,  Matthew Robert McCue ,  Robert Anthony Godlasky

    Inventor： Mark Allan Page ,  Matthew Robert McCue ,  Robert Anthony Godlasky

    IPC: B64C29/02 ,  B64C39/02

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165

    Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

    Abstract translation: 提供了一种用于固定翼飞行模式和转子飞行模式的飞机。 飞机可以包括机身，机翼和多个发动机。 机身可以包括还包括旋转支撑件的翼连接区域。 旋转部分可以包括旋转支撑件和机翼，其中多个发动机附接到旋转部分。 在转子飞行模式中，旋转部分可以围绕机身的纵向轴线旋转，为类似于直升机的转子的飞机提供升降机。 在固定翼飞行模式中，旋转部分不围绕机身的纵向轴线旋转，为类似于常规飞机的飞机提供升降机。 在转子飞行模式下为转子提供动力的相同发动机也为固定翼飞行模式下的飞机提供动力。

    Rotocraft
    157.
    发明授权
    Rotocraft 有权

    公开(公告)号：US08973862B2

    公开(公告)日：2015-03-10

    申请号：US14061723

    申请日：2013-10-23

    Applicant: Robert Marcus

    Inventor： Robert Marcus

    IPC: B64C27/08 ,  B64C19/00 ,  B64C29/00 ,  B64C39/02 ,  B64D45/00

    CPC classification number: B64C19/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/046 ,  B64C2201/088 ,  B64D45/00

    Abstract: An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle.

    Abstract translation: 飞行器包括独立控制的水平推进器和垂直升降器，以提供设计和操作简单性，同时允许六度自由度的精确飞行和使用诸如工具，传感器和仪器的安装设备。 每个水平推进器和垂直升降器可以安装为恒定间距的固定轴转子，同时仍然允许精确控制偏航，俯仰，滚动，水平运动和垂直高程。 陀螺仪和倾斜仪可用于进一步提高飞行精度。 控制器管理施加水平推进器和垂直升降器的推力，以补偿由使用安装在飞行器上的工具和其他装置产生的力和扭矩。

    Fluid dynamic device with thrust control shroud
    159.
    发明授权
    Fluid dynamic device with thrust control shroud 有权
    带推力控制护罩的流体动力装置

    公开(公告)号：US08646721B2

    公开(公告)日：2014-02-11

    申请号：US12990964

    申请日：2009-05-07

    Applicant: Greg Chapman ,  Jakub Kawka ,  Christopher Kim Schlunke

    Inventor： Greg Chapman ,  Jakub Kawka ,  Christopher Kim Schlunke

    IPC: B64C29/00 ,  B64C29/02 ,  B05B12/00

    CPC classification number: B64C27/20 ,  B64C39/064 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108

    Abstract: A fluid dynamic device (100) for directing fluid flow to generate thrust comprising a thrust control shroud (130) disposed about a central axis (210) of said fluid dynamic device (100) for directing a fluid flow between an upstream fluid intake region (220) and a downstream fluid exit region (222), forming a fluid exit area, of said shroud (130) to generate thrust wherein a displacement of said fluid exit region (222) of said shroud (130) with respect to said central axis (210) results in a translation of said fluid exit area (222) such that the level of shear stress induced in that part of the shroud (130) disposed laterally to the direction of translation of the shroud (130) is minimized.

    Abstract translation: 一种用于引导流体流动以产生推力的流体动力装置（100），包括围绕所述流体动力装置（100）的中心轴线（210）设置的推力控制罩（130），用于引导流体流在上游流体进入区域 220）和形成所述护罩（130）的流体出口区域的下游流体出口区域（222）以产生推力，其中所述护罩（130）的所述流体出口区域（222）相对于所述中心轴线 （210）的平移导致所述流体出口区域（222）的平移，使得在围绕护罩（130）的平移方向侧向设置的护罩（130）的那部分中引起的剪切应力水平最小化。

    Rotocraft
    160.
    发明授权
    Rotocraft 有权

    公开(公告)号：US08590828B2

    公开(公告)日：2013-11-26

    申请号：US12712094

    申请日：2010-02-24

    Applicant: Robert Marcus

    Inventor： Robert Marcus

    IPC: B64C27/08

    CPC classification number: B64C19/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/046 ,  B64C2201/088 ,  B64D45/00

    Abstract: An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle.

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