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    ELECTRICALLY POWERED VTOL TAIL-SITTER AIRCRAFT FOR PROVIDING TRANSPORTATION
    1.
    发明申请
    ELECTRICALLY POWERED VTOL TAIL-SITTER AIRCRAFT FOR PROVIDING TRANSPORTATION 审中-公开

    公开(公告)号：WO2018200879A1

    公开(公告)日：2018-11-01

    申请号：PCT/US2018/029655

    申请日：2018-04-26

    Applicant: DETROIT AIRCRAFT CORPORATION

    Inventor： RIMANELLI, Jon ,  LAI, Yizhang ,  LOKHANDWALA, Qhase

    IPC: B64C27/28 ,  B64C27/08 ,  B64C27/22 ,  B64C27/24 ,  B64C29/00 ,  B64C29/02

    CPC classification number: B64C29/02 ,  B64C5/08 ,  B64C25/32 ,  B64C25/58 ,  B64C37/00 ,  B64C39/04

    Abstract: An electric tail-sitter aircraft configured to transport passengers and/or cargo between locations. The aircraft includes a flight module, a ground module and a payload module. The flight module is a wing that can rotate with respect to the rest of the aircraft, from vertical to horizontal and vice versa. A plurality of electrically driven propellers are attached to the wing, providing vector thrusting (through the rotation of the wing) and differential thrusting to control the different phases of the flight (vertical take-off and landing, horizontal, transition between the previous two). The payload module is an interchangeable component that can be a cabin for passenger transportation or a cargo container. It can actively shift its position in the aircraft in order to control the center of gravity position. The ground module may include wheels, a transmission, suspension, and carry the payload module. It is connected to the flight module through an L-shaped hinge, where the wing rotates to a plane behind the hinging point, in order to have the center of gravity adjusted as to be located on the hinging axis.

    VERTICAL TAKEOFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV)
    3.
    发明申请
    VERTICAL TAKEOFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) 审中-公开
    垂直起落架（垂直起降）无人机（UAV）

    公开(公告)号：WO2017044388A1

    公开(公告)日：2017-03-16

    申请号：PCT/US2016/050192

    申请日：2016-09-02

    Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATION

    Inventor： STARACE, Ralph C. ,  AUGUST, Robert A. ,  FRONIUS, Douglas L. ,  CREASMAN, Francois

    IPC: B64C29/02

    CPC classification number: B64C29/02 ,  B64C3/56 ,  B64C9/00 ,  B64C27/57 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  G05D1/0011 ,  G05D1/0088 ,  G05D1/0858

    Abstract: One example embodiment includes a vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) (12). The VTOL UAV includes a flight control system configured to provide avionic control of the VTOL UAV in a hover mode and in a level-flight mode. The VTOL UAV also includes a body (18) encapsulating an engine and the flight control system. The VTOL UAV further includes a rotor disk (14) coupled to the engine and configured to provide vertical thrust and cyclic pitch control in the hover mode and to provide horizontal thrust for flight during the level-flight mode.

    Abstract translation: 一个示例性实施例包括垂直起飞和着陆（VTOL）无人机（UAV）（12）。 VTOL无人机包括飞行控制系统，配置为以悬停模式和级别飞行模式提供垂直起降无人机的航空电子控制。 VTOL无人机还包括封装发动机的主体（18）和飞行控制系统。 垂直起落架无人机还包括联接到发动机的转子盘（14），并配置成在悬停模式下提供垂直推力和循环桨距控制，并在水平飞行模式期间为飞行提供水平推力。

    HIGH SPEED MULTI-ROTOR VERTICAL TAKEOFF AND LANDING AIRCRAFT
    6.
    发明申请
    HIGH SPEED MULTI-ROTOR VERTICAL TAKEOFF AND LANDING AIRCRAFT 审中-公开
    高速多转子垂直起飞和着陆飞机

    公开(公告)号：WO2016085610A4

    公开(公告)日：2016-07-28

    申请号：PCT/US2015057722

    申请日：2015-10-28

    Applicant: XCRAFT ENTPR LLC

    Inventor： CLARIDGE JERRY DANIEL ,  MANNING CHARLES FISCHER

    IPC: B64C29/02

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108

    Abstract: This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back.

    Abstract translation: 本公开总体上针对包括固定机翼飞行能力的高速垂直起飞和降落（VTOL）飞行器。 高速VTOL飞机可以包括至少两个与主飞行器上的飞行器的纵向轴线等距离的推力产生转子，以及至少两个与飞行器的纵向轴线在垂直翼上等距的推力产生转子。 转子可以由电动机驱动。 但是，可以使用其他动力源，例如燃烧或混合动力发动机。 通过调整转子的速度和/或俯仰角，飞机可以从垂直飞行形态转变为水平飞行形态并返回。

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    8.
    发明申请
    VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-公开
    垂直起落架和飞机

    公开(公告)号：WO2015108578A3

    公开(公告)日：2015-09-03

    申请号：PCT/US2014060166

    申请日：2014-10-10

    Applicant: SWIFT ENGINEERING INC

    Inventor： GODLASKY ROBERT ,  OGAWA NATE ,  STREETT ANDREW

    IPC: B64C29/00 ,  B64C3/56 ,  B64C5/02 ,  B64C29/02 ,  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。

    ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS
    9.
    发明申请
    ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS 审中-公开
    电动车辆和飞行控制方法

    公开(公告)号：WO2014053057A1

    公开(公告)日：2014-04-10

    申请号：PCT/CA2013/000846

    申请日：2013-10-04

    Applicant: SKYKAR INC. ,  LENG, Marcus

    Inventor： LENG, Marcus

    IPC: B64D27/24 ,  B64C27/22 ,  B64C27/28 ,  B64C29/00 ,  B64C39/08

    CPC classification number: B64C27/26 ,  B60L11/1805 ,  B60L11/1859 ,  B60L11/1861 ,  B64C1/26 ,  B64C11/46 ,  B64C15/02 ,  B64C29/00 ,  B64C29/0025 ,  B64C29/02 ,  B64C39/026 ,  B64D17/00 ,  B64D27/24 ,  B64D31/12 ,  B64D33/08

    Abstract: An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control.

    Abstract translation: 飞行器包括至少一个机翼，在所述至少一个机翼上的多个推力产生元件，多个电动马达等于用于单独驱动每个所述推力产生元件的推力产生元件的数量，至少一个用于 向电动机供电，以及用于控制车辆操作的飞行控制系统。 飞行器可以包括机身配置，以便于在水平，垂直和瞬态取向中的起飞和着陆，冗余控制和推力元件以提高可靠性，并且在低功率和多功率推进系统情况下，控制车辆的定向稳定性。 飞行器的飞行方法包括推力产生元件的旋转速度的变化，以实现主动的车辆控制。

    TAILBOOM-STABILIZED VTOL AIRCRAFT
    10.
    发明申请
    TAILBOOM-STABILIZED VTOL AIRCRAFT 审中-公开
    TAILBOOM稳定的垂直起降飞机

    公开(公告)号：WO2005039973A3

    公开(公告)日：2005-11-10

    申请号：PCT/US2004034581

    申请日：2004-10-19

    Applicant: BALDWIN DOUGLAS G

    Inventor： BALDWIN DOUGLAS G

    IPC: B64C29/00 ,  B64C39/02 ,  B64C27/28

    CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

    Abstract: A disclosed flying craft (100) includes a suspension structure (110) having a first end and a second end, a lift unit (150), and a payload unit (190). The lift unit includes a nacelle (128) and a tailboom (140), and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

    Abstract translation: 公开的飞行器（100）包括具有第一端和第二端的悬挂结构（110），升降单元（150）和有效载荷单元（190）。 提升单元包括机舱（128）和尾杆（140），并且枢转地联接到悬挂结构的第一端，并且有效载荷单元耦合到结构的第二端。 因此，尾巴可以相对于有效载荷单元枢转地联接，这有利地允许尾巴呈现对于特定飞行方式所需的取向。 在垂直飞行或悬停期间，尾巴可以以与悬挂结构基本平行的方向从提升单元悬挂，并且使得抵抗来自提升单元的降洗的阻力最小化。 在水平飞行期间，尾翼可以与悬架结构正交，向后延伸，在该方向上可以产生俯仰和偏转力矩以控制和稳定水平飞行。 还公开了有利的变型和方法。

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