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    Vertical Takeoff and Landing Unmanned Aircraft System
    171.
    发明申请
    Vertical Takeoff and Landing Unmanned Aircraft System 审中-公开
    垂直起飞和着陆无人机系统

    公开(公告)号：US20170008625A1

    公开(公告)日：2017-01-12

    申请号：US15164718

    申请日：2016-05-25

    Applicant: Orville Olm ,  Zenon Dragan

    Inventor： Orville Olm ,  Zenon Dragan

    IPC: B64C29/02 ,  B64C3/56 ,  B64C3/32 ,  B64C39/02

    CPC classification number: B64C29/02 ,  B64C3/56 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/20 ,  Y02T50/14

    Abstract: A vertical takeoff and landing (VTOL) unmanned aircraft system (UAS) may be uniquely capable of VTOL via a folded wing design while also configured for powered flight as the wings are extended. In a powered flight regime with wings extended, the VTOL UAS may maintain controlled powered flight as a twin pusher canard design. In a zero airspeed (or near zero airspeed) nose up attitude in a VTOL flight regime with the wings folded, the unmanned aircraft system may maintain controlled flight using main engine thrust as well as vectored thrust as a vertical takeoff and landing aircraft. An airborne transition from VTOL flight regime to powered flight and vice versa may allow the VTOL UAS continuous controlled flight in each regime.

    Abstract translation: 垂直起飞和着陆（VTOL）无人驾驶飞机系统（UAS）可以通过折翼设计独特地实现垂直起降，同时还可以在机翼延伸时配置为动力飞行。 在具有扩展翼的动力飞行机构中，VTOL UAS可以保持受控的动力飞行作为双推杆的设计。 无人驾驶飞机系统可以以垂直起降飞行系统以零空速（或近零空速）起飞的姿态折叠起来，使用主发动机推力以及作为垂直起降飞机的向心推力来维持受控飞行。 从空中飞行任务飞行状态到动力飞行的空降过渡，反之亦然，可能使VTOL UAS在每个制度中持续控制飞行。

    Controlled Take-Off And Flight System Using Thrust Differentials
    174.
    发明申请
    Controlled Take-Off And Flight System Using Thrust Differentials 审中-公开
    使用推力差速控制起飞和飞行系统

    公开(公告)号：US20160244159A1

    公开(公告)日：2016-08-25

    申请号：US14862134

    申请日：2015-09-22

    Applicant: Transition Robotics, Inc.

    Inventor： JoeBen Bevirt

    IPC: B64C29/02 ,  B64C39/02

    CPC classification number: B64C29/02 ,  B64C15/00 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/02 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/165

    Abstract: A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in least two dimensions relative to the horizontal during takeoff. An aerial vehicle which uses a rotating platform of engines in fixed relationship to each other and which rotates relative to the wings of the vehicle for takeoff and landing.

    Abstract translation: 一种适用于垂直起飞和着陆的载人/无人机，使用相同的发动机起飞和着陆以及向前飞行。 一种飞行器，其适于在垂直方向上与翼起飞，而不是水平飞行姿态，以垂直姿态起飞，然后转变到水平飞行路径。 一种飞行器，其通过交替发动机的推力来控制起飞和着陆期间车辆的姿态，发动机的推力在起飞期间相对于水平线至少二维分开。 一种飞行器，其使用彼此固定关系并且相对于车辆的翼部旋转以便起飞和着陆的发动机的旋转平台。

    AIRCRAFT FOR VERTICAL TAKE-OFF AND LANDING WITH TWO WING ARRANGEMENTS
    177.
    发明申请
    AIRCRAFT FOR VERTICAL TAKE-OFF AND LANDING WITH TWO WING ARRANGEMENTS 审中-公开
    用于双向安装的垂直起落架的飞机

    公开(公告)号：US20150232178A1

    公开(公告)日：2015-08-20

    申请号：US14378604

    申请日：2013-02-13

    Applicant: Johannes REITER

    Inventor： Johannes Reiter

    IPC: B64C29/00 ,  B64C37/00 ,  B64C3/38

    CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C3/385 ,  B64C27/00 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0075 ,  B64C29/02 ,  B64C37/00 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

    Abstract: The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101).

    Abstract translation: 本发明涉及一种飞行器，其包括机身（100），其包括机身轴线（101），第一机翼装置（110）和第二机翼装置（120）。 第一机翼装置（110）安装到机身（100），使得第一机翼装置（110）能围绕第一机翼装置（110）的第一纵向机翼轴线（111）倾斜，并且使得第一机翼装置 （110）能够围绕机身轴线（101）旋转。 第二机翼装置（120）包括至少一个推进单元（122），其中第二机翼装置（120）安装到机身（100）上，使得第二机翼装置（120）可围绕第二纵向机翼轴线 （121），并且使得所述第二机翼装置（120）能够围绕所述机身轴线（101）旋转。 第一机翼装置（110）和第二机翼装置（120）以这样的方式适配，使得在固定翼飞行模式中，第一机翼装置（110）和第二机翼装置（120）不围绕 机身轴（101）。 第一机翼装置（110）和第二机翼装置（120）进一步适于以悬停飞行模式，第一机翼装置（110）和第二机翼装置（120）围绕相应的 第一纵向翼片轴线（111）和相应的第二纵向翼片轴线（121）相对于其在固定翼飞行模式中的定向，并且第一翼形装置（110）和第二翼形装置（120）围绕机身旋转 轴（101）。

    Systems and methods for vertical takeoff and/or landing
    178.
    发明授权
    Systems and methods for vertical takeoff and/or landing 有权
    用于垂直起飞和/或着陆的系统和方法

    公开(公告)号：US09085354B1

    公开(公告)日：2015-07-21

    申请号：US13868539

    申请日：2013-04-23

    Applicant: Google Inc.

    Inventor： Eric Peeters ,  William Graham Patrick

    IPC: B64C27/26 ,  B64C29/00

    CPC classification number: B64C29/02 ,  B64C17/00 ,  B64C2201/088

    Abstract: Systems and methods for vertical takeoff and/or landing are disclosed herein. An aerial vehicle may include a first propulsion unit and a second propulsion each rotatably connected to a body. The aerial vehicle may include a first wing and a second wing each rotatably connected to the body. And the aerial vehicle may include a control system configured to: position the first propulsion unit, the second propulsion unit, the first wing, and the second wing; operate the first propulsion unit and the second propulsion unit; and rotate the first propulsion unit, the second propulsion unit, the first wing, and the second wing.

    Abstract translation: 本文公开了用于垂直起飞和/或着陆的系统和方法。 飞行器可以包括第一推进单元和第二推进件，每个推进单元和第二推进件可旋转地连接到主体。 飞行器可以包括第一翼和第二翼，每个翼可旋转地连接到主体。 并且该飞行器可以包括控制系统，其被配置为：定位第一推进单元，第二推进单元，第一翼和第二翼; 操作第一推进单元和第二推进单元; 并且旋转第一推进单元，第二推进单元，第一翼和第二翼。

    System and method for compact and combinable aerial vehicle capable of vertical/short takeoff and landing
    179.
    发明授权
    System and method for compact and combinable aerial vehicle capable of vertical/short takeoff and landing 有权
    能够进行垂直/短时起飞和着陆的紧凑型和可组合式飞行器的系统和方法

    公开(公告)号：US08936212B1

    公开(公告)日：2015-01-20

    申请号：US12861986

    申请日：2010-08-24

    Applicant: Qiang Fu ,  Xu Zhang

    Inventor： Qiang Fu ,  Xu Zhang

    IPC: B64C15/12

    CPC classification number: B64C37/02 ,  B64C3/56 ,  B64C29/0033 ,  B64C37/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/165 ,  Y02T50/14

    Abstract: System and method to construct vertical and/or short takeoff and landing (V/STOL) aerial vehicles capable of being folded into compact size, and capable of be combined with one or more such vehicles to form bigger composite aerial vehicles. Airframe of the vehicle comprises a plurality of wings on lateral or periphery of thrust generators, wherein arrangements of wings make it possible to optionally fold wings without moving thrust generators. Folding transforms such vehicles into ground vehicles which can share roads and house parking lots with conventional ground vehicles. Therefore such vehicles can be used as V/STOL flying cars. Means are provided for attaching to and detaching from one or more similarly equipped vehicles in flight or before takeoff, so that multiple vehicles can form a large composite vehicle. Compactness, combinability and V/STOL capability enable versatile applications.

    Abstract translation: 构建能够折叠成紧凑尺寸的垂直和/或短起飞（V / STOL）飞行器的系统和方法，并且能够与一个或多个这样的车辆组合以形成更大的复合飞行器。 车辆的机身包括在推力发生器的侧面或周边上的多个翼，其中翼的布置使得可以可选地折叠翼而不移动推力发生器。 折叠将这种车辆转换成可与常规地面车辆共享道路和房屋停车场的地面车辆。 因此，这种车辆可以用作V / STOL飞行车。 提供了用于在飞行中或起飞之前附接和分离一个或多个类似装备的车辆的装置，使得多个车辆可以形成大型复合车辆。 紧凑性，组合性和V / STOL功能可实现多种应用。

    ROTOCRAFT
    180.
    发明申请
    ROTOCRAFT 审中-公开

    公开(公告)号：US20140231594A1

    公开(公告)日：2014-08-21

    申请号：US14061723

    申请日：2013-10-23

    Applicant: Robert Marcus

    Inventor： Robert Marcus

    IPC: B64C19/00 ,  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。

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