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    MOUNTING DEVICE FOR ELECTRONIC COMPONENTS IN UAV HELICOPTERS
    1.
    发明申请
    MOUNTING DEVICE FOR ELECTRONIC COMPONENTS IN UAV HELICOPTERS 审中-公开
    无人机直升机电子部件安装装置

    公开(公告)号：WO2011068444A1

    公开(公告)日：2011-06-09

    申请号：PCT/SE2009/051362

    申请日：2009-12-02

    Applicant: SAAB AB ,  CARDELL, Per-Erik ,  JOHANSSON, Andreas

    Inventor： CARDELL, Per-Erik ,  JOHANSSON, Andreas

    IPC: H05K5/06 ,  H05K5/03

    CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C2201/024 ,  B64D43/00

    Abstract: The invention refers to a mounting device (1) for mounting electronic components of an unmanned helicopter (22) comprising a solid base plate (2) having a circumferential outer edge (3), and connecting means (4) fixedly attached to said circumferential outer edge (3) for reversibly connecting a flexible cover (5) to said base plate. Mounting devices (1) of present invention protect grouped electronic components of the helicopter against harsh weather conditions like moist, salt, dirt, dust and wind.

    Abstract translation: 本发明涉及一种用于安装无人直升机（22）的电子部件的安装装置（1），其包括具有周向外边缘（3）的实心基板（2）和连接装置（4），该连接装置固定地附接到所述圆周外 边缘（3），用于将柔性盖（5）可逆地连接到所述基板。 本发明的安装装置（1）保护直升机的分组电子部件免受诸如潮湿，盐，灰尘和风的恶劣天气条件的影响。

    MAIN ROTOR ARRANGEMENT OF AN UAV-HELICOPTER
    2.
    发明申请
    MAIN ROTOR ARRANGEMENT OF AN UAV-HELICOPTER 审中-公开
    无人机直升机的主转子安装

    公开(公告)号：WO2010144003A1

    公开(公告)日：2010-12-16

    申请号：PCT/SE2009/050704

    申请日：2009-06-10

    Applicant: SAAB AB ,  CARDELL, Per-Erik ,  STENBOM, Kjell

    Inventor： CARDELL, Per-Erik ,  STENBOM, Kjell

    IPC: B64C27/35 ,  B64C11/12

    CPC classification number: B64C27/43 ,  B64C2201/024 ,  Y10S416/50

    Abstract: The present invention relates to a main rotor arrangement (1) for an UAV-helicopter, comprising a rotor mast (3) defining a vertical axis of rotation (R), and a hub (5) for attachment of rotor blades, wherein the hub (5) is mounted to the rotor mast (3) in a tiltable way so as to reduce loads acting on the rotor blades during operation of the UAV-helicopter. The main rotor arrangement (1) comprises a damping assembly (18) for damping said tilting of the hub (5).

    Abstract translation: 本发明涉及一种用于无人机直升机的主转子装置（1），其包括限定垂直旋转轴线（R）的转子桅杆（3）和用于附接转子叶片的轮毂（5），其中所述轮毂 （5）以可倾斜的方式安装到转子桅杆（3）上，以便在无人机直升机操作期间减小作用在转子叶片上的负载。 主转子装置（1）包括用于阻止毂（5）的所述倾斜的阻尼组件（18）。

    LOAD BEARING ASSEMBLY FOR AN UAV-HELICOPTER
    3.
    发明申请
    LOAD BEARING ASSEMBLY FOR AN UAV-HELICOPTER 审中-公开
    无人机直升机负载轴承组件

    公开(公告)号：WO2010138033A1

    公开(公告)日：2010-12-02

    申请号：PCT/SE2009/050602

    申请日：2009-05-26

    Applicant: SAAB AB ,  CARDELL, Per-Erik ,  STENBOM, Kjell

    Inventor： CARDELL, Per-Erik ,  STENBOM, Kjell

    IPC: B64D9/00

    CPC classification number: B64D47/08 ,  B64C17/02 ,  B64C2201/024 ,  B64C2201/127

    Abstract: The present invention relates to a load bearing assembly (7) for an UAV-helicopter (1) and which comprises a carrier (11) for a payload, such as a camera or a radar unit, wherein the carrier (11) is movable and lockable in the longitudinal direction of the UAV-helicopter, so as to adjust the centre of gravity of the UAV-helicopter (1). The present invention also relates to an UAV-helicopter being provided with such a load bearing assembly.

    Abstract translation: 本发明涉及一种用于无人机直升机（1）的承载组件（7），其包括用于有效载荷（例如照相机或雷达单元）的载体（11），其中所述载体（11）是可移动的，并且 可以在无人机直升机的纵向锁定，以调整无人机直升机的重心（1）。 本发明还涉及一种具有这种承载组件的无人机直升机。

    A DE-ICER, A FIXTURE AND A METHOD OF ADJUSTING THE POSITION OF A DE-ICER
    5.
    发明申请
    A DE-ICER, A FIXTURE AND A METHOD OF ADJUSTING THE POSITION OF A DE-ICER 审中-公开
    一种DE-ICER，一种装置和一种调整DE-ICER位置的方法

    公开(公告)号：WO2009096838A1

    公开(公告)日：2009-08-06

    申请号：PCT/SE2008/050628

    申请日：2008-05-29

    Applicant: SAAB AB ,  CARDELL, Per-Erik ,  LINDSTRÖM, Ragnar

    Inventor： CARDELL, Per-Erik ,  LINDSTRÖM, Ragnar

    IPC: B64D15/16

    CPC classification number: B64D15/16

    Abstract: The invention relates to a de-icer (20), comprising a bracket (52) arranged on a structural member and a de-icer module (22) mounted on the bracket (52). The de-icer module (22) is adjustable arranged on the bracket (52), so that the position of the de-icer module (22) is adjustable in relation to the bracket (52). The invention also relates to a fixture (72) and a method of adjusting the position of a de-icer (20).

    Abstract translation: 本发明涉及除冰器（20），其包括布置在结构构件上的支架（52）和安装在支架（52）上的除冰器模块（22）。 除冰器模块（22）可调节地布置在支架（52）上，使得除冰器模块（22）的位置相对于支架（52）可调节。 本发明还涉及一种固定装置（72）和调节除冰器（20）的位置的方法。

    LANDING ARRESTING SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) AERIAL VEHICLES, LANDING AND TAKE-OFF PLATFORM FOR VTOL AERIAL VEHICLES AND VTOL LOCKING MEMBER FOR AERIAL VEHICLES
    6.
    发明申请
    LANDING ARRESTING SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) AERIAL VEHICLES, LANDING AND TAKE-OFF PLATFORM FOR VTOL AERIAL VEHICLES AND VTOL LOCKING MEMBER FOR AERIAL VEHICLES 审中-公开
    用于垂直起落架的垂直起落架系统（垂直起落架）空中客车，起重机和起落架平台，用于空中客车和垂直起落架的空中客车

    公开(公告)号：WO2014007705A1

    公开(公告)日：2014-01-09

    申请号：PCT/SE2012/050790

    申请日：2012-07-05

    Applicant: SAAB AB ,  CARDELL, Per-Erik ,  STENBOM, Kjell

    Inventor： CARDELL, Per-Erik ,  STENBOM, Kjell

    IPC: B64F1/12 ,  B64C25/68 ,  E01F3/00

    CPC classification number: B64F1/02 ,  B64C25/52 ,  B64C25/68 ,  B64C2025/325 ,  B64C2201/182 ,  B64F1/007 ,  B64F1/125 ,  E01F3/00 ,  Y02T50/82

    Abstract: The present invention relates to a landing arresting system for vertical take-off and landing (VTOL) aerial vehicles(1) comprising a landing and take-off platform(6) and at least one VTOL locking member (4) having a projecting portion (32) arranged at a lower portion of the vehicle (1). The landing and take-off platform(6) comprises a plurality of individually displaceable rolls (12),arranged substantially in a horizontal direction, and moveable back and forth, such that the projecting portion (32) of the VTOL locking member (4) can be entered, retained and released between two adjacent rolls (12). The present invention also relates to a landing and take-off platform for VTOL aerial vehicles and a VTOL locking member for aerial vehicles.

    Abstract translation: 本发明涉及一种用于垂直起飞和降落（VTOL）空中飞行器（1）的降落停止系统，其包括着陆和起飞平台（6）和至少一个具有突出部分的垂直起落架锁定构件（4） 32）布置在车辆（1）的下部。 着陆和起飞平台（6）包括基本上沿水平方向布置并可前后移动的多个单独可移动的辊（12），使得垂直起落架锁定构件（4）的突出部分（32） 可以在两个相邻的辊（12）之间进入，保持和释放。 本发明还涉及用于垂直起降飞机的着陆和起飞平台以及用于飞行器的垂直起落架锁定构件。

    ROTOR DAMPER AND TAIL ROTOR WITH SUCH A ROTOR DAMPER
    8.
    发明申请
    ROTOR DAMPER AND TAIL ROTOR WITH SUCH A ROTOR DAMPER 审中-公开
    带转子阻尼器的转子阻尼器和尾轮转子

    公开(公告)号：WO2010140933A1

    公开(公告)日：2010-12-09

    申请号：PCT/SE2009/050645

    申请日：2009-06-02

    Applicant: SAAB AB ,  CARDELL, Per-Erik ,  JOHANSSON, Tommy ,  LINDROTH, Johan ,  STENBOM, Kjell

    Inventor： CARDELL, Per-Erik ,  JOHANSSON, Tommy ,  LINDROTH, Johan ,  STENBOM, Kjell

    IPC: B64C27/82 ,  B64C11/12 ,  B64C27/35 ,  B64C27/51

    CPC classification number: B64C27/82 ,  B64C27/51 ,  B64C2027/003 ,  Y10S416/50

    Abstract: The invention relates to a rotor damper for a tail rotor (1) of a helicopter (4), comprising a main body (30) of a resilient material to be arranged between a drive shaft (6) for the tail rotor (1) and a hub (12) on which rotor blades (14) for the tail rotor (1) is coupled. A flange (38) is connected to the main body (30) of the rotor damper (2), which flange (38) is provided with an abutment surface (39) for abutting an outer surface (50) of the hub (12). The invention also relates to a tail rotor (1) provided with such a rotor damper (2).

    Abstract translation: 本发明涉及一种用于直升机（4）的尾部转子（1）的转子阻尼器，包括一个弹性材料的主体（30），该主体（30）布置在用于尾部转子（1）的驱动轴（6）和 枢轴（12），用于尾部转子（1）的转子叶片（14）联接在其上。 凸缘（38）连接到转子阻尼器（2）的主体（30）上，该凸缘（38）设置有用于邻接轮毂（12）的外表面（50）的邻接表面（39） 。 本发明还涉及设置有这种转子风门（2）的尾部转子（1）。

    MAIN ROTOR ARRANGEMENT OF AN UAV-HELICOPTER
    10.
    发明公开
    MAIN ROTOR ARRANGEMENT OF AN UAV-HELICOPTER 有权
    无人机直升机HAUPTROTOR安排

    公开(公告)号：EP2440454A1

    公开(公告)日：2012-04-18

    申请号：EP09845904.3

    申请日：2009-06-10

    Applicant: Saab AB

    Inventor： CARDELL, Per-Erik ,  STENBOM, Kjell

    IPC: B64C27/35 ,  B64C11/12

    CPC classification number: B64C27/43 ,  B64C2201/024 ,  Y10S416/50

    Abstract: The present invention relates to a main rotor arrangement (1) for an UAV-helicopter, comprising a rotor mast (3) defining a vertical axis of rotation (R), and a hub (5) for attachment of rotor blades, wherein the hub (5) is mounted to the rotor mast (3) in a tiltable way so as to reduce loads acting on the rotor blades during operation of the UAV-helicopter. The main rotor arrangement (1) comprises a damping assembly (18) for damping said tilting of the hub (5).

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