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    Attitude control of an aircraft in a ditching condition
    4.
    发明公开
    Attitude control of an aircraft in a ditching condition 有权
    Lageregelung eines Flugzeuges in einer Notwasserungssituation

    公开(公告)号：EP2815962A1

    公开(公告)日：2014-12-24

    申请号：EP14165640.5

    申请日：2014-04-23

    申请人： The Boeing Company

    发明人： Boren, Kelly L. ,  Barmichev, Sergey D.

    IPC分类号： B64C17/00 ,  B64C17/02

    CPC分类号： B64D25/00 ,  B64C17/08

    摘要： Configurations provide rapid adjustment to an aircraft attitude in the water upon an emergency water landing. In one configuration, an aircraft fuselage (202; 402) has a forward compartment (204; 404) that includes a water intake (206; 406) and an air vent (208; 410). The water intake (206; 406) is located below an expected waterline (102) upon ditching the aircraft (100) in water and transports a flow of water to the forward compartment (204; 404) at a designed flow rate. The air vent (208; 410) is positioned at a height in the forward compartment (204; 404) and allows a desired volume of water to fill the forward compartment (204; 404) and adjust an attitude of the aircraft (100) within a time period. (Fig. 2)

    摘要翻译： 配置可以在紧急水上着陆时迅速调整飞机在水中的态度。 在一种构造中，飞行器机身（202; 402）具有包括进水口（206; 406）和排气口（208; 410）的前部隔间（204; 404）。 在水中切割飞机（100）时，进水口（206; 406）位于预期的水线（102）下方，并以设计的流速将水流输送到前部隔间（204; 404）。 空气通道（208; 410）定位在前舱（204; 404）中的高度处，并且允许期望体积的水填充前舱（204,404）并调节飞行器（100）内的姿态 一段时间 （图2）

    APPARATUS AND METHOD FOR BALANCING AIRCRAFT WITH ROBOTIC ARMS
    5.
    发明公开
    APPARATUS AND METHOD FOR BALANCING AIRCRAFT WITH ROBOTIC ARMS 审中-公开

    公开(公告)号：EP3978363A1

    公开(公告)日：2022-04-06

    申请号：EP21208869.4

    申请日：2017-10-11

    申请人： Poltorak, Alexander

    发明人： Poltorak, Alexander

    IPC分类号： B64D1/00 ,  B64C39/02 ,  B64C17/02 ,  B64C27/04

    摘要： A hover-capable flying machine (100) such as a drone includes a robotic arm (120) extending from the body (110), and an instrumentality for balancing the machine in response to disturbances such as those caused by picking up and dropping of the payload by the extended robotic arm (120). In embodiments, the end of the arm (120) is equipped with a balancing rotor assembly (140) that may provide lift sufficient to counteract the weight of the payload and/or of the arm (105). In embodiments, the machine's power pack is shifted in response to the disturbances. The power pack may be moved, for example, on a rail within and/or extending beyond the machine in a direction generally opposite to the extended arm (120). The power pack may also be built into a bandolier-like device that can be rolled-in and rolled out, thus changing the center of gravity of the machine.

    ACTIVE VIBRATION CONTROL ACTUATOR
    7.
    发明授权
    ACTIVE VIBRATION CONTROL ACTUATOR 有权

    公开(公告)号：EP3055206B1

    公开(公告)日：2018-12-05

    申请号：EP14853088.4

    申请日：2014-10-03

    申请人： Sikorsky Aircraft Corporation

    发明人： WELSH, William A.

    IPC分类号： B64C17/02

    CPC分类号： B64C27/001 ,  B64C2027/004

    摘要： A vibration control actuator includes a housing having a length between ends and a rotatable shaft located in the housing and extending along a housing length and which rotates about a shaft axis substantially parallel to the length. An inertia wheel assembly is operably connected to the rotatable shaft and configured to rotate therewith about the shaft axis. The inertia wheel assembly is in frictional contact with an inner wall of the housing and translatable to travel within the housing between the ends along at least a portion of the shaft axis.

    ROTORCRAFT
    8.
    发明公开
    ROTORCRAFT 审中-公开
    旋翼机

    公开(公告)号：EP3299282A1

    公开(公告)日：2018-03-28

    申请号：EP15892572.7

    申请日：2015-05-19

    申请人： Aeronext Inc.

    发明人： SUZUKI, Youichi

    IPC分类号： B64C27/08 ,  B64C17/02 ,  B64C39/02

    CPC分类号： B64C27/08 ,  B64C17/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64D47/08

    摘要： A center C of a connecting portion 16 coincides with a center U of lift generated in a body of a rotary-wing aircraft 10. The center C of the connecting portion 16 is a point of action of gravitational force of a support rod 21 and a first mounting portion with respect to the connecting portion 16. The center U of the lift is a point of action of the lift on the rotary-wing aircraft 10 and is the center of rotation of the connecting portion 16. Since the center U of the lift generated in the rotary-wing aircraft 10 is positioned at the center C of the connecting portion as described above, even in the case where the body of the rotary-wing aircraft 10 is inclined, the support rod 21 and the first mounting portion rotate around the center C of the connecting portion, and thus no rotational moment due to heavy load such as a camera 28 occurs around the center U of the lift. This makes it possible to reduce, in a case where a rotary-wing aircraft including a plurality of rotary wings travels in the horizontal direction, the difference in the rotational speeds of rotary wings on the front side and on the rear side in the traveling direction compared with a conventional case.

    摘要翻译： 连接部分16的中心C与在旋翼飞机10的主体中产生的升力的中心U重合。连接部分16的中心C是支撑杆21的重力的作用点， 第一安装部分相对于连接部分16的中心。升降机的中心U是旋翼飞行器10上升降机的作用点，并且是连接部分16的旋转中心。由于 即使在旋翼飞行器10的主体倾斜的情况下，旋转翼飞机10中产生的升力也位于连接部的中心C处，支撑杆21和第一安装部旋转 围绕连接部分的中心C，并且因此在升降机的中心U周围不会出现由诸如照相机28的重负载引起的转动力矩。 由此，在包含多个旋转翼的旋翼飞机沿水平方向行驶的情况下，能够减小行驶方向前侧和后侧的旋转翼的旋转速度差 与传统案例相比。