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    Aircraft deployment and retrieval of unmanned aerial vehicles
    71.
    发明公开
    Aircraft deployment and retrieval of unmanned aerial vehicles 审中-公开
    飞机部署和撤回无人机

    公开(公告)号：EP2727835A3

    公开(公告)日：2018-02-28

    申请号：EP13189903.1

    申请日：2013-10-23

    Applicant: The Boeing Company

    Inventor： Hanna, Mark ,  Poling, David R

    IPC: B64C39/02 ,  B64D1/10 ,  B64D1/12

    CPC classification number: B64C39/024 ,  B64C2201/082 ,  B64C2201/126 ,  B64C2201/182 ,  B64C2201/206

    Abstract: An aircraft system incorporates a first aircraft 48a, 48b having a grappling device 26 including a first gripper 30 with a first actuator 36a and a second gripper 32 with a second actuator 36b. The first gripper and the second gripper are movable between an open and a closed position to engage a hooking device 18 and pivot together to change a capture angle. A first controller 72 receives a command and operates the actuators in response to open and close the first and second grippers of the grappling device. The controller also receives a second command and operates the first and second actuators to pivot the grippers and provide grappling at a range of capture angles. A second aircraft 10, which may be a UAV, incorporates the hooking device 18. The hooking device includes a ring 20 rotatable from the surface and a third actuator 22 to rotate the ring between a stowed and an extended position.

    Abstract translation: 飞行器系统包括具有擒抱装置26的第一飞机48a，48b，擒纵装置26包括具有第一致动器36a的第一抓具30和具有第二致动器36b的第二抓具32。 第一夹持器和第二夹持器可在打开位置和闭合位置之间移动，以接合挂钩装置18并且一起枢转以改变捕捉角度。 第一控制器72接收命令并响应于打开和关闭擒抱装置的第一和第二抓具而操作致动器。 控制器还接收第二命令并且操作第一致动器和第二致动器以枢转抓具并且提供捕捉角范围的抓斗。 第二架飞机10可以是无人飞行器，其包括挂钩装置18.挂钩装置包括可从表面旋转的环20和第三致动器22，以在收起位置和展开位置之间旋转环。

    AERODYNAMISCH GEFORMTER, AKTIVER SCHLEPPKÖRPER
    72.
    发明公开
    AERODYNAMISCH GEFORMTER, AKTIVER SCHLEPPKÖRPER 有权
    AERODYNAMISCH GEFORMTER，AKTIVERSCHLEPPKÖRPER

    公开(公告)号：EP3233634A1

    公开(公告)日：2017-10-25

    申请号：EP15831127.4

    申请日：2015-12-04

    Applicant: Alfred-Wegener-Institut Helmholtz-Zentrum für Polar- und Meeresforschung

    Inventor： HERBER, Andreas ,  KALMBACH, Dirk ,  GERDES, Rüdiger ,  BAYER, Hans-Jörg

    IPC: B64D3/02 ,  B64C3/16 ,  F41J9/10 ,  B64C1/00

    CPC classification number: B64D3/02 ,  B64C3/16 ,  B64C39/022 ,  B64C2001/0045 ,  B64C2201/104 ,  B64C2201/12 ,  B64C2201/141 ,  B64C2201/206 ,  F41J9/10

    Abstract: Known towed bodies can be maneuvered in all three dimensions but, as pure airborne targets, do not have a large load capacity. The towed body (01) according to the invention is designed for bearing large loads and serves exclusively scientific and commercial measurement purposes. To achieve very good aerodynamic properties, the towed body has a fuselage (02) comprising a triangular transverse plane (15), wherein the upper face (18) is designed to be wide and the lower face (19) is designed to be narrow, and comprising a curvature (23) only on the upper face (18), whereas the lower face (19) runs straight. The wings (03) are bent and consist of two segments (07, 08). Small segments (07) are arranged at the bottom of the fuselage (02), which small segments point downwards and stabilise the towed body (01), large segments (08) are connected to the small segments (07), which large segments point upwards and generate lift. In the front and middle region of the fuselage (02) and in the small segments (07) there are load chambers (10, 11) which can have user-friendly segment chambers (22). The unit chamber (09) comprising various units (27), such as a position-stabilising gyroscope system, an anti collision module, accumulators, a generator and an emergency parachute system (25), is located in the rear region of the towed body (01).

    Abstract translation: 已知的拖曳机构可以在所有三维空间中进行操纵，但是由于纯粹的空中目标，其载荷能力并不大。 根据本发明的拖曳主体（01）被设计用于承受大负载并且专门用于科学和商业测量目的。 为了实现非常好的空气动力学特性，被拖曳体具有包括三角形横向平面（15）的机身（02），其中上表面（18）被设计成宽的并且下表面（19）被设计成窄的， 并且仅在上表面（18）上包括曲率（23），而下表面（19）直线延伸。 翼（03）弯曲并由两个部分（07,08）组成。 在机身（02）的底部设置小段（07），小段向下指向并稳定拖曳主体（01），大段（08）连接到小段（07），大段 向上并产生升力。 在机身（02）的前部和中部区域以及小部分（07）中，存在可具有用户友好的分段腔室（22）的装载腔室（10,11）。 包括诸如位置稳定陀螺仪系统，防撞模块，蓄电池，发电机和应急降落伞系统（25）的各种单元（27）的单元室（09）位于拖曳主体 （01）。

    UNMANNED AIRCRAFT SYSTEM AND METHOD OF OPERATING SAME
    73.
    发明授权
    UNMANNED AIRCRAFT SYSTEM AND METHOD OF OPERATING SAME 有权
    维也纳爆炸品联合会制造的“联合国气候变化框架公约”

    公开(公告)号：EP2314508B1

    公开(公告)日：2017-05-24

    申请号：EP09808231.6

    申请日：2009-08-13

    Applicant: Mitsubishi Heavy Industries, Ltd.

    Inventor： SUZUKI Satoshi

    IPC: B64C37/02 ,  B64D5/00 ,  B64D47/08

    CPC classification number: B64C39/024 ,  B64C37/02 ,  B64C2201/082 ,  B64C2201/206 ,  G05D1/104

    Abstract: An unmanned aircraft system includes a manned aircraft and an unmanned aircraft. The manned aircraft includes a manned aircraft main wing, a manned aircraft fuselage, a manned aircraft landing system, and a manned aircraft joining mechanism provided at a bottom portion of the manned aircraft fuselage. The unmanned aircraft includes an unmanned aircraft main wing, an unmanned aircraft fuselage, an unmanned aircraft landing system, and an unmanned aircraft joining mechanism provided at a roof portion of the unmanned aircraft fuselage. The manned aircraft joining mechanism and the unmanned aircraft joining mechanism are detachably joined. The unmanned aircraft system can take off or land in a state that the unmanned aircraft and the manned aircraft are joined.

    Abstract translation: 无人机系统包括载人飞机和无人飞机。 载人飞机包括载人飞机主翼，载人飞机机身，载人飞机着陆系统，以及设置在载人飞机机身底部的载人飞机连接机构。 无人机包括无人机主翼，无人飞机机身，无人飞机着陆系统，以及设在无人驾驶飞机机身顶部的无人飞机接合机构。 载人飞机接合机构和无人飞行器接合机构可拆卸地接合。 无人机系统可以无人驾驶飞机和载人飞机加入的状态起飞或着陆。

    Vorrichtung zum Absetzen von unbemannten Flugkörpern aus einem Luftfahrzeug
    76.
    发明公开
    Vorrichtung zum Absetzen von unbemannten Flugkörpern aus einem Luftfahrzeug 有权
    一种用于从飞行器无人驾驶飞行器的抽出装置

    公开(公告)号：EP1873058A3

    公开(公告)日：2008-06-04

    申请号：EP07011085.3

    申请日：2007-06-06

    Applicant: LFK-Lenkflugkörpersysteme GmbH

    Inventor： Grabmeier, Michael

    IPC: B64D1/12 ,  F41F3/06

    CPC classification number: B64D1/12 ,  B64C2201/206

    Abstract: Eine Vorrichtung zum Absetzen von unbemannten Flugkörpern aus einem Luftfahrzeug mit einer Palette (19), auf der zumindest ein Behälter (2, 2') zur Aufnahme eines Flugkörpers (3, 3') vorgesehen ist, wobei der Behälter (2, 2') einen oberen Behälterabschnitt (24) aufweist, der einen Pylon zur hängenden, lösbaren Halterung des Flugkörpers (3, 3') aufweist, ist dadurch gekennzeichnet, dass der Behälter (2, 2') einen unteren Behälterabschnitt (20) aufweist, der als Stützbereich für den Flugkörper (3, 3') ausgebildet ist.

    Système d'emport de charge pour avion de transport
    80.
    发明授权
    Système d'emport de charge pour avion de transport 有权
    保持系统负载的运输机

    公开(公告)号：EP2354000B1

    公开(公告)日：2012-07-04

    申请号：EP11290030.3

    申请日：2011-01-19

    Applicant: MBDA France

    Inventor： Jaurand, Benoît

    IPC: B64D1/10 ,  B64D1/12 ,  B64D1/02

    CPC classification number: B64D1/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/201 ,  B64C2201/206

    Abstract: The system (1) an external container (15) fixed in a cargo compartment of a transport aircraft (AC). An internal container (4) is arranged in the external container to bring the internal container from a position in which the internal container is entirely located inside the external container to another position (P2) in which the internal container is shifted toward a rear side of the aircraft with respect to the former position such that a release part (7) of the internal container is located outside the aircraft through an opening (8) at a rear side of the compartment.

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