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    Unmanned air system (UAS)
    242.
    发明公开
    Unmanned air system (UAS) 有权
    Unbemanntes Luftfahrzeug（UAS）

    公开(公告)号：EP2660147A1

    公开(公告)日：2013-11-06

    申请号：EP12382165.4

    申请日：2012-05-04

    Applicant: The Boeing Company

    Inventor： Criado, Alfredo

    IPC: B64C21/04

    CPC classification number: B64C23/005 ,  B64C9/38 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/165 ,  Y02T50/32 ,  Y02T50/44

    Abstract: An unmanned air system with blown flaps is disclosed. The unmanned air system is powered at least in part by a fuel cell (320). The fuel cell receives hydrogen from an on board tank (305) and oxygen form the air. An air intake (310) is arranged to guide air from outside the unmanned air system to the fuel cell for ventilating and cooling the fuel cell. The air having passed by the fuel cell is heated. A routing channel (340) is arranged to supply the heated air from the fuel cell to one or more flaps, slats or other high lift devices located on a lift device of the unmanned air system. The heated air is blown across the one or more flaps, slats or other high lift devices to provide lift. The unmanned air system with fuel cell blown flaps makes use of the heated air in increasing lift and reducing drag.

    Abstract translation: 公开了一种具有吹风襟翼的无人空中系统。 所述无人驾驶空气系统至少部分由燃料电池（320）供电。 燃料电池从板上容器（305）接收氢气，氧气形成空气。 空气入口（310）被布置成将空气从无人驾驶空气系统的外部引导到燃料电池，用于对燃料电池进行通风和冷却。 通过燃料电池的空气被加热。 布置通道（340）被布置成将来自燃料电池的加热的空气供应到位于无人驾驶空气系统的提升装置上的一个或多个襟翼，板条或其它高升程装置。 加热的空气吹过一个或多个翼片，板条或其他高升力装置以提供升力。 具有燃料电池吹风翼的无人驾驶空气系统在增加升力和减少阻力的同时利用加热的空气。

    TILT WING ROTOR VTOL
    243.
    发明公开
    TILT WING ROTOR VTOL 审中-公开
    具有垂直起降的倾斜旋翼绦

    公开(公告)号：EP2616335A1

    公开(公告)日：2013-07-24

    申请号：EP11770063.3

    申请日：2011-09-16

    Applicant: Reiter, Johannes

    Inventor： Reiter, Johannes

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

    CPC classification number: B64C29/00 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/165

    Abstract: The present invention relates to an aircraft (110) for vertical take-off and landing. The aircraft comprises a first wing (101), a second wing (102) and a fuselage (103). The first wing (101) comprises a first longitudinal wing axis (104) and the second wing (102) comprises a second longitudinal wing axis (104). The first wing (101) extends along the first longitudinal wing axis (104) and the second wing (102) extends along the second longitudinal wing axis (104) from the fuselage (103). The first wing (101) is tiltable with a first rotational direction around the first longitudinal wing axis (104) and the second wing (102) is tiltable with a second rotational direction around the second longitudinal wing axis (104). The wings (101, 102) are adapted in such a way that, in a fixed- wing flight mode, the wings (101, 102) do not rotate around a second axis (105). The wings (101, 102) are further adapted in such a way that, in a hover flight mode, the wings (101, 102) are tilted around the longitudinal wing axis (104) with respect to its orientation in the fixed- wing flight mode and that the wing (100) rotates around the second axis (105).

    Unmanned helicopter, takeoff method for unmanned helicopter, and landing method for an unmanned helicopter
    246.
    发明公开
    Unmanned helicopter, takeoff method for unmanned helicopter, and landing method for an unmanned helicopter 审中-公开
    无人直升机升空的无人直升机和着陆程序的无人直升机

    公开(公告)号：EP1645505A3

    公开(公告)日：2010-04-21

    申请号：EP05017978.7

    申请日：2003-10-07

    Applicant: Fuji Jukogyo Kabushiki Kaisha

    Inventor： Yamane, Akihiro, Fuji Jukogyo K.K.

    IPC: B64C13/20 ,  B64C39/02 ,  G05D1/06

    CPC classification number: B64C13/20 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/165 ,  G05D1/0669 ,  G05D1/0676

    Abstract: An unmanned helicopter 20 includes altitude control device for giving a command of a collective pitch blade angle based on an altitude change rate command, etc., and performing altitude control of an airframe. The unmanned helicopter further includes descending device for causing the airframe to descend to a second altitude while changing descent rate command of the altitude control device and giving a descent rate command smaller than the descent rate command to the second altitude to the altitude control device for causing the airframe to descend from the second altitude to the ground.

    Abstract translation: 机身的飞行控制器使起飞并且在从地面起飞启动命令的接收提升到预定高度。 飞行控制器增加一共同桨距舵角不进行高度控制，并且随后启动高度控制。 因此独立权利要求中包括了以下内容：（a）至无人直升机起飞方法; 和（b）至无人直升机降落方法。

    AIRCRAFT LANDING METHOD AND DEVICE
    248.
    发明授权
    AIRCRAFT LANDING METHOD AND DEVICE 有权
    飞机着陆方法和装置

    公开(公告)号：EP1827972B8

    公开(公告)日：2008-10-22

    申请号：EP05813078.2

    申请日：2005-11-30

    Applicant: Israel Aerospace Industries Ltd.

    Inventor： SIRKIS, Omri

    IPC: B64C9/18 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C9/18 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/187 ,  B64C2201/201

    Abstract: A method for landing a fixed wing aircraft is provided in which an inversion maneuver is performed so that the aircraft's back is facing the ground, and the aircraft's underside is facing away from the ground. After initiation or completion of this maneuver, deep stall is induced, and the aircraft descends almost vertically to land on its upper side, thus minimizing impact loads or damage on its underside. In a particular aerodynamic arrangement configured for carrying out the method, a flap (24), which may be stowed during normal flight, is deployed in a manner such as to aerodynamically induce a negative pitching moment on the aircraft and deep stall.

    Abstract translation: 提供了一种用于着陆固定翼飞机的方法，其中执行反转操纵，使得飞机的背面朝向地面，并且飞机的底面背离地面。 在开始或完成这种机动之后，引起深度失速，并且飞机几乎垂直下降以落在其上侧，从而最小化撞击载荷或其下侧的损坏。 在构造成用于执行该方法的特定空气动力学布置中，可以在正常飞行期间收起的襟翼（24）以诸如在空气动力学上引起飞行器上的负俯仰力矩和深度失速的方式展开。

    MODULAR ARTICULATED-WING AIRCRAFT
    249.
    发明公开
    MODULAR ARTICULATED-WING AIRCRAFT 有权
    带翅膀的链接模块化飞机

    公开(公告)号：EP1924495A2

    公开(公告)日：2008-05-28

    申请号：EP06851409.0

    申请日：2006-06-28

    Applicant: Sommer, Geoffrey S.

    Inventor： Sommer, Geoffrey S.

    IPC: B64C39/02

    CPC classification number: B64C39/024 ,  B64C37/02 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/143 ,  B64C2201/165 ,  B64C2201/206

    Abstract: Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft.

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