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    THRUST VECTORING FREE WING AIRCRAFT
    171.
    发明授权
    THRUST VECTORING FREE WING AIRCRAFT 失效
    带飞翼和推力反向PLANE

    公开(公告)号：EP0629164B1

    公开(公告)日：1999-05-26

    申请号：EP93907455.5

    申请日：1993-03-12

    Applicant: SCHMITTLE, Hugh J.

    Inventor： SCHMITTLE, Hugh J.

    IPC: B64C3/38

    CPC classification number: B64C39/024 ,  B64C3/385 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

    Abstract: The VTOL aircraft (10) includes a free wing (16) having wings on opposite sides of the fuselage (12) connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators (26), rudder (24) and the differential pitch settings of the wings, respectively. At launch, the elevator (26) pitches the fuselage (12) nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing (16) rotates relative to the fuselage (12) into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and the aircraft may be gently recovered in or on a resilient surface such as a net (66).

    MOBILE AIRCRAFT RECOVERY SYSTEM
    174.
    发明授权
    MOBILE AIRCRAFT RECOVERY SYSTEM 有权
    移动式飞机恢复系统

    公开(公告)号：EP2580117B1

    公开(公告)日：2018-04-18

    申请号：EP11792831.7

    申请日：2011-05-03

    Applicant: AAI Corporation

    Inventor： MILLER, Stephen, W. ,  FOX, Steven, J. ,  SCHILL, Graham, W. ,  ASKE, Brian, A.

    IPC: B64C25/68 ,  B64F1/02

    CPC classification number: B64F1/02 ,  B64C2201/182 ,  F41H11/02 ,  F41J13/00

    Abstract: An apparatus for the recovery of an aircraft includes a capture device and first and second pole pairs. The first pole pair includes first top and bottom poles respectively placed near first top and bottom portions of the capture device. The first pole pair is configured to move from a first position, in which the pole pair holds the capture device in an open position to capture the aircraft, to a second position, in which the pole pair holds the capture device in a closed position to contain the captured aircraft after impact of the aircraft on the capture device. The second pole pair includes second top and bottom poles respectively placed near second top and bottom portions of the capture device. The second pole pair is also configured to move from the first position to the second position. Further, energy elements are coupled on one end to a respective top or bottom portion of the capture device and on another end to a respective top or bottom pole. The energy elements are disposed to absorb the force of the impact of the aircraft.

    METHODS OF DYNAMICALLY CONTROLLING AIRFLOW BEHIND A CARRIER AIRCRAFT TO REDIRECT AIR FLOW DURING AN IN-FLIGHT RECOVERY OF AN UNMANNED AERIAL VEHICLE AND AN APPARATUS THEREFOR
    176.
    发明公开
    METHODS OF DYNAMICALLY CONTROLLING AIRFLOW BEHIND A CARRIER AIRCRAFT TO REDIRECT AIR FLOW DURING AN IN-FLIGHT RECOVERY OF AN UNMANNED AERIAL VEHICLE AND AN APPARATUS THEREFOR 审中-公开
    动态控制航空器后面的气流以减少无人飞行器在飞行中恢复空气流动的载体飞行器及其装置

    公开(公告)号：EP3248872A1

    公开(公告)日：2017-11-29

    申请号：EP17172934.6

    申请日：2017-05-25

    Applicant: The Boeing Company

    Inventor： BERNHARDT, Roger D ,  LEE, Alexander D ,  HUPP, Ryan L ,  GISSEN, Abraham N ,  ROTHACKER, Benjamin A

    IPC: B64D5/00 ,  B64D3/00 ,  B64C39/02

    CPC classification number: B64C21/04 ,  B64C19/00 ,  B64C23/00 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/182 ,  B64D3/00 ,  B64D5/00

    Abstract: An apparatus (100, 700, 1100, 1500) is provided for dynamically controlling airflow behind a carrier aircraft to redirect air flow during an in-flight recovery of an unmanned aerial vehicle (UAV). The apparatus comprises a frame (110, 910, 1110, 1310) attached to an end portion of an arm member extending from the carrier aircraft. The apparatus comprises a plurality of vanes (120, 720, 1220, 1320, 1510, 1520) disposed within the frame. Each vane is controllable between an opened position and a closed position to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV. Alternatively, or in addition to, the apparatus comprises a plurality of compressed air jets (950, 1050, 1150, 1350) disposed on the frame, wherein each jet is controllable to provide active airflow to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV.

    Abstract translation: 提供了一种装置（100,700,1100,1500），用于动态地控制载机后面的气流以在无人飞行器（UAV）的飞行中恢复期间重新引导气流。 该设备包括附接到从载运飞机延伸的臂构件的端部的框架（110,910,1110,1310）。 该设备包括设置在框架内的多个叶片（120,720,1220,1320,1510,1520）。 每个叶片都可以在打开位置和关闭位置之间进行控制，以便在UAV的飞行中恢复期间动态修改运载机后面的气流。 可选地或除此之外，所述设备包括设置在所述框架上的多个压缩空气射流（950,1050,1150,1350），其中每个射流是可控制的以提供主动气流以动态修改所述载体飞机后面的所述气流 飞行中无人机的恢复。

    RELEASE AND CAPTURE OF A FIXED-WING AIRCRAFT
    179.
    发明公开
    RELEASE AND CAPTURE OF A FIXED-WING AIRCRAFT 审中-公开
    FREISETZUNG UND AUFNAHME EINESSTARRFLÜGELFLUGZEUG

    公开(公告)号：EP3127809A1

    公开(公告)日：2017-02-08

    申请号：EP16179595.0

    申请日：2016-07-15

    Applicant: Lockheed Martin Corporation

    Inventor： GAMBLE, Dustin ,  CURRAN, Matthew

    IPC: B64C39/02 ,  B64D5/00 ,  B64C27/08

    CPC classification number: B64D5/00 ,  B64C27/08 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/182 ,  B64C2201/206

    Abstract: In one embodiment, a system includes an unmanned, multirotor helicopter and a fixed-wing aircraft. The multirotor helicopter may couple to the fixed-wing aircraft to support and hold the fixed-wing aircraft. The multirotor helicopter may then elevate the fixed-wing aircraft from a launch site to a release altitude. The multirotor helicopter may also accelerate the fixed-wing aircraft to a release speed and upon reaching the release speed, release the fixed-wing aircraft. The unmanned, multirotor helicopter may then return to the launch site.

    Abstract translation: 在一个实施例中，系统包括无人驾驶的多旋翼直升机和固定翼飞机。 多旋翼直升机可以耦合到固定翼飞机，以支撑和固定固定翼飞机。 然后，多旋翼直升机可以将固定翼飞机从发射场提升到释放高度。 多转直升机也可以将固定翼飞机加速到释放速度，达到释放速度后，释放固定翼飞机。 无人驾驶的多旋翼直升机然后可以返回发射场。

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