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    Aircraft
    31.
    发明专利
    Aircraft 有权
    飞机

    公开(公告)号：JP2008247378A

    公开(公告)日：2008-10-16

    申请号：JP2008049880

    申请日：2008-02-29

    Applicant: Eads Deutschland Gmbh ,  イーエイーディーエス、ドイチュラント、ゲゼルシャフト、ミット、ベシュレンクテル、ハフツングEads Deutschland Gmbh

    Inventor： SCHWARZ MICHAEL

    IPC: B64D27/14

    CPC classification number: B64D27/20 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048

    Abstract: PROBLEM TO BE SOLVED: To provide an aircraft having improved aerodynamical characteristics and excellent in direction stability.
    SOLUTION: In the aircraft having a first drive unit 4 in which an air taking-in port 10 is formed on an upper side of a body 2 of the aircraft 1 and a second drive unit 5 in which an air taking-in port 10 is formed on a lower side of the body 2 of the aircraft 1, the body of the aircraft 1 has a recession part 12 for storing the drive units 4, 5, and the recession part 12 is arranged such that the first and second drive units 4, 5 are vertically superposed/arranged on a plane where a vertical axis and a perpendicular axis of the aircraft 1 are laid. The drive units 4, 5 include an engine 14, a housing 11 provided with the air taking-in port 10, a means 8 for removably fixing the drive units 4, 5 to the body 2 of the aircraft 1, and a means 9 for removably bonding an electricity feed wire, a data circuit and a fuel pipe between the drive units 4, 5 and the body 2 of the aircraft 1.
    COPYRIGHT: (C)2009,JPO&INPIT

    Abstract translation: 要解决的问题：提供具有改善的空气动力特性和优异的方向稳定性的飞机。 解决方案：在具有第一驱动单元4的飞行器中，在飞行器1的主体2的上侧形成有吸气口10，其中空气吸入口 端口10形成在飞行器1的主体2的下侧，飞行器1的主体具有用于存储驱动单元4,5的凹陷部12，并且凹部12被布置成使得第一和第二 驱动单元4,5垂直叠加/布置在飞行器1的垂直轴和垂直轴线的平面上。 驱动单元4,5包括发动机14，设置有吸气口10的壳体11，用于将驱动单元4,5可拆卸地固定到飞行器1的主体2的装置8和用于 在驱动单元4,5和飞行器1的主体2之间可拆卸地连接供电线，数据电路和燃料管。（C）2009年，JPO和INPIT

    Ducted fan core for use with an unmanned aerial vehicle
    33.
    发明公开
    Ducted fan core for use with an unmanned aerial vehicle 有权
    涵道的核心用在无人导弹

    公开(公告)号：EP2147858A3

    公开(公告)日：2012-04-11

    申请号：EP09160870.3

    申请日：2009-05-21

    Applicant: Honeywell International Inc.

    Inventor： Collette, Daniel Ross

    IPC: B64C27/20 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162

    Abstract: A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame (190), attached to which are an engine (120), gearbox assembly, fan, and a plurality of control vanes (130). A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods (240) carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

    Ducted fan core for use with an unmanned aerial vehicle
    34.
    发明公开
    Ducted fan core for use with an unmanned aerial vehicle 有权
    Mantelstromkern zur Verwendung在einem unbemanntenFlugkörper

    公开(公告)号：EP2147858A2

    公开(公告)日：2010-01-27

    申请号：EP09160870.3

    申请日：2009-05-21

    Applicant: Honeywell International Inc.

    Inventor： Collette, Daniel Ross

    IPC: B64C27/20 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162

    Abstract: A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame (190), attached to which are an engine (120), gearbox assembly, fan, and a plurality of control vanes (130). A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods (240) carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

    Abstract translation: 提供用于无人驾驶飞行器的管道风扇芯，其容纳各种有效载荷。 风管风扇芯包括附接到发动机（120），齿轮箱组件，风扇和多个控制叶片（130）的框架（190）。 框架上的第一表面包括多个连接或电迹线。 多个连接件用于可移除地附接承载各种有效载荷的各种吊舱（240）。 因此，简单地通过将不同的荚移除并附接到固定的车辆核心，可以使用相同的无人驾驶飞行器来传送各种有效载荷。 这些荚可以成形为形成车辆外部的一部分，并且当荚被附接到框架时，它们增强了车辆的空气动力学。

    Ducted fan core used for unmanned aircraft
    36.
    发明专利
    Ducted fan core used for unmanned aircraft 有权
    用于不定期飞机的导向风扇芯

    公开(公告)号：JP2010030585A

    公开(公告)日：2010-02-12

    申请号：JP2009125187

    申请日：2009-05-25

    Applicant: Honeywell Internatl Inc ,  ハネウェル・インターナショナル・インコーポレーテッド

    Inventor： COLLETTE DANIEL ROSS

    IPC: B64C29/00 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162

    Abstract: PROBLEM TO BE SOLVED: To provide a ducted fan core for housing a wide variety of payloads for an unmanned aircraft.
    SOLUTION: A ducted fan core 100 includes a frame 110 attached to an engine 120, a gearbox assembly, a fan 140, and a plurality of control vanes 130. A first surface 112 on the frame includes a plurality of connecting sections or electrical traces. The plurality of connecting sections are used for removably attaching a variety of pods holding various payloads. Thus, the wide variety of payloads can be conveyed by using the same unmanned aircraft, simply by removing pods from the fixed core of the aircraft and attaching different pods thereto. These pods are shaped so as to form part of the exterior of the aircraft, and when the pods are attached to the frame, they enhance the characteristics of aerodynamics of the aircraft.
    COPYRIGHT: (C)2010,JPO&INPIT

    Abstract translation: 要解决的问题：提供一种用于无人驾驶飞机的用于容纳各种有效载荷的管道风扇芯。 管道风扇芯100包括附接到发动机120的框架110，齿轮箱组件，风扇140和多个控制叶片130.框架上的第一表面112包括多个连接部分或 电痕迹。 多个连接部分用于可拆卸地连接保持各种有效载荷的各种荚。 因此，可以通过使用相同的无人驾驶飞机来简单地通过从飞行器的固定核中移除舱架并且将不同舱架附接到其上来传送各种有效载荷。 这些荚形成为形成飞行器外部的一部分，并且当荚附接到框架时，它们增强了飞行器的空气动力学的特性。 版权所有（C）2010，JPO＆INPIT

    Tail boom stability vtol machine
    37.
    发明专利
    Tail boom stability vtol machine 审中-公开

    公开(公告)号：JP2007508998A

    公开(公告)日：2007-04-12

    申请号：JP2006536719

    申请日：2004-10-19

    Applicant: ボールドウィン,ダグラス,ジー.

    Inventor： ボールドウィン，ダグラス，ジー．

    IPC: B64C29/00 ,  B64C27/22 ,  B64C39/02

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

    Abstract: 【課題】
    【解決手段】ここに開示する航空機は、第１および第２の端部と、揚力ユニットと、ペイロードユニットとを具える懸垂構造を含む。 この揚力ユニットは、ナセルとテールブームとを具え、前記懸垂構造の第１の端部に回動可能に連結しており、ペイロードユニットが懸垂康応の第２の端部に連結されている。 これにより、テールブームはペイロードユニットに対し回動可能に連結され、テールブームを特定の飛行モードの向きにすることが可能となる。 垂直飛行または空中停止モードでは、テールブームは懸垂構造とほぼ平行の向きで揚力ユニットから吊り下がり、揚力ユニットの吹き下ろしの抵抗を最小限としている。 水平飛行中は、テールブームは懸垂構造に直交し、縦揺れと横揺れモーメントを制御して安定した水平飛行となるよう後側に延在する。 他にも有利な変形例や方法が開示されている。
    【選択図】図１

    테일붐-안정화 수직 이착륙 비행체
    38.
    发明公开
    테일붐-안정화 수직 이착륙 비행체 无效
    TAILBOOM稳定的垂直起降飞机

    公开(公告)号：KR1020060101497A

    公开(公告)日：2006-09-25

    申请号：KR1020067009973

    申请日：2004-10-19

    Applicant: 발드윈, 더글라스, 쥐.

    Inventor： 발드윈,더글라스,쥐.

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

    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 includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, 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: 公开的飞行技术包括具有第一端和第二端的悬挂结构，升降单元和有效载荷单元。 提升单元包括机舱和尾巴，并且枢转地联接到悬架结构的第一端，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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