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    UNMANNED AERIAL VEHICLE WITH COUNTER-ROTATING DUCTED ROTORS AND SHROUDED PUSHER-PROP
    2.
    发明公开
    UNMANNED AERIAL VEHICLE WITH COUNTER-ROTATING DUCTED ROTORS AND SHROUDED PUSHER-PROP 审中-公开
    具有凹陷反对旋转的转子和外衣推力螺旋桨无人机

    公开(公告)号：EP1173360A1

    公开(公告)日：2002-01-23

    申请号：EP00942624.8

    申请日：2000-04-12

    申请人： Sikorsky Aircraft Corporation

    发明人： CYCON, James ,  SCOTT, Mark, W. ,  DEWITT, Christopher, W.

    IPC分类号： B64C39/02 ,  B64C27/20

    CPC分类号： B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165

    摘要： An unmanned aerial vehicle that includes a fuselage (12) with a partial toroidal forward portion, and an aft portion. A duct (18) is formed through the fuselage and extends from the top to the bottom of the fuselage. Two counter-rotating rotor assemblies (16) are mounted within the duct for providing downward thrust through the duct. The rotor assemblies are supported by a plurality of support struts (20). At least one engine is mounted within the fuselage and engages with the rotor assemblies. A pusher prop assembly (50) is amounted to the aft portion of the fuselage. The pusher prop assembly is designed to provide forward thrust along the longitudinal axis of the aircraft. The pusher prop assembly includes a drive shaft (58) that is engaged with the engine. A plurality of propellers (56) are attached to and rotated by the drive shaft. A shroud (54) is mounted to the aft portion of the fuselage around the propellers and is operative for channelling the air passing through the propellers in a substantially aft direction. A pair of wings (42) is removably attached to the sides of the fuselage. Each wing preferably includes a fixed portion and a pivotal flaperon portion hinged to the fixed portion. Directional vanes (60) are preferably mounted to the shroud downstream from the propellers and control flow out of the shroud. Deflectors may be mounted to the bottom of the fuselage across a portion of the duct to control flow of air into the duct.

    RADIO FREQUENCY EMITTING HOOK SYSTEM FOR A ROTARY-WING AIRCRAFT EXTERNAL LOAD HANDLING
    3.
    发明公开
    RADIO FREQUENCY EMITTING HOOK SYSTEM FOR A ROTARY-WING AIRCRAFT EXTERNAL LOAD HANDLING 审中-公开
    射频发射HOOK SYSTEM FOR挥杆平面与外部最后的处理

    公开(公告)号：EP1989107A2

    公开(公告)日：2008-11-12

    申请号：EP07835688.8

    申请日：2007-01-31

    申请人： Sikorsky Aircraft Corporation

    发明人： EADIE, William, J. ,  SCOTT, Mark, W.

    IPC分类号： B64D1/12

    CPC分类号： B64D1/22 ,  B66C13/063 ,  B66C13/46

    摘要： An aircraft load management system that determines the position of an aircraft cargo hook for display to an aircrew. The cargo hook positional information may alternatively or additionally be communicated directly to a flight control system and a winch control system to automate and coordinate flight control inputs with winch operation to actively position the cargo hook. Data transfer from the cargo through a data link system also provides the load management system with exact position of the cargo load connection points even prior to attachment of the cargo hook to the load. The load management system also includes anti-sway algorithms for active load stability inputs to the flight control system and to alter flight control laws and automatically compensate for CG. excursions.