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    Method and system for monitoring approach of rotary wing aircraft
    73.
    发明专利
    Method and system for monitoring approach of rotary wing aircraft 审中-公开
    用于监控旋转飞机的方法和系统

    公开(公告)号：JP2008230593A

    公开(公告)日：2008-10-02

    申请号：JP2008008971

    申请日：2008-01-18

    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： ISHIHARA YASUO ,  JOHNSON STEVE C ,  CONNER KEVIN J

    IPC: B64D45/00 ,  B64C27/04

    CPC classification number: G05B23/0235

    Abstract: PROBLEM TO BE SOLVED: To provide a system and a method for generating an alert signal for a pilot if a rotary wing aircraft is approaching a hazardous situation when there is a possibility of getting the aircraft into a situation of settling with power for approaching to landing.
    SOLUTION: The system comprises output devices 36,37, a first component 32 configured to measure wind velocity and wind direction which are related to the rotary wing aircraft, a second component 30 configured to measure a rate of descent of the rotary wing aircraft, and a processing part 24 configured to be in data communication with the output devices 36,37, the first component 32, and the second component 30 to receive the measured wind velocity and direction and the measured rate of descent. The processing part 24 generates the alert signal, and transmits the alert signal to the output devices 36,37 if the received wind value is greater than a tailwind threshold value and the rate of descent value is greater than a rate of descent threshold value.
    COPYRIGHT: (C)2009,JPO&INPIT

    Abstract translation: 要解决的问题：提供一种用于为飞行员生成警报信号的系统和方法，如果旋翼机飞机在有可能使飞机进入用电的情况下接近危险情况时 接近着陆 解决方案：系统包括输出装置36,37，被配置为测量与旋转翼飞行器相关的风速和风向的第一部件32，构造成测量旋翼的下降速率的第二部件30 飞机和被配置为与输出设备36,37，第一组件32和第二组件30进行数据通信的处理部件24，以接收所测量的风速和方向以及测量的下降速率。 处理部分24产生报警信号，并且如果接收到的风值大于顺风阈值并且下降值大于下降阈值的速率，则将报警信号发送到输出装置36,37。 版权所有（C）2009，JPO＆INPIT

    Method and device for managing data of unmanned helicopter
    77.
    发明专利
    Method and device for managing data of unmanned helicopter 审中-公开
    用于管理无人直升机数据的方法和装置

    公开(公告)号：JP2008068709A

    公开(公告)日：2008-03-27

    申请号：JP2006248382

    申请日：2006-09-13

    Applicant: Yamaha Motor Co Ltd ,  ヤマハ発動機株式会社

    Inventor： KUMAOKA YOSUKE

    IPC: B64D47/00 ,  A01M7/00 ,  B64C27/04 ,  B64C39/02

    Abstract: PROBLEM TO BE SOLVED: To provide a method and a device for managing data of an unmanned helicopter capable of precisely managing data on flying of an unmanned helicopter and spray of a spray agent.
    SOLUTION: A correction part 35d corrects a flying trajectory based on a flight data. Thereby, displacement of the flight trajectory can be corrected. As a result, the data on flying of the unmanned helicopter and spray the spray agent can be precisely managed.
    COPYRIGHT: (C)2008,JPO&INPIT

    Abstract translation: 要解决的问题：提供一种用于管理无人直升机的数据的方法和装置，其能够精确地管理无人直升机飞行的数据和喷雾剂的喷雾。 解决方案：校正部分35d基于飞行数据校正飞行轨迹。 从而可以校正飞行轨迹的位移。 因此，可以精确地管理无人直升机飞行数据并喷洒喷雾剂。 版权所有（C）2008，JPO＆INPIT

    Helicopter structure, and method and device for reducing vibration of helicopter structure
    80.
    发明专利
    Helicopter structure, and method and device for reducing vibration of helicopter structure 有权
    直升机结构，以及减少直升机结构振动的方法和装置

    公开(公告)号：JP2007055602A

    公开(公告)日：2007-03-08

    申请号：JP2006315946

    申请日：2006-11-22

    Applicant: Westland Helicopters Ltd ,  ウエストランド・ヘリコプターズ・リミテッドWestland Helicopters Limited

    Inventor： VINCENT ALAN HENRY

    IPC: B64C27/04 ,  B64C27/51 ,  B64C27/00 ,  F16F7/10 ,  F16F15/02

    CPC classification number: B64C27/001 ,  B64C2027/002 ,  F16F7/1017 ,  F16F15/02

    Abstract: PROBLEM TO BE SOLVED: To provide a method and an apparatus for reducing vibration in a helicopter structure having small parasitic mass, which prevents an accelerometer and its related wiring from sustaining accidental damage, and absorbs the vibration at its source or in the vicinity thereof.
    SOLUTION: The helicopter structure 10 is provided with a plurality of actuators 19 connected between a fuselage 12 capable of relative motion at an exciting frequency and a frame body 17. The actuators are continuously oscillated at a frequency substantially corresponding to the exciting frequency by a supply source 20 of a liquid pressurizing fluid. A sensor 21 attached to a rotor blade at a selected location is adapted to generate signals representative of dynamic changes at the respective selected location, a computer 22 processes the signals and provides output signals for controlling the phase and magnitude of applied forces generated by the actuators and for varying the phase and magnitude characteristics of the forces so as to compensate for changes in the dynamic characteristic of the rotating system, whereby the overall level of vibration in the fuselage structure is reduced.
    COPYRIGHT: (C)2007,JPO&INPIT

    Abstract translation: 要解决的问题：提供一种用于减小具有小寄生质量的直升机结构中的振动的方法和装置，其防止加速度计及其相关布线维持意外损坏，并且吸收其源或在其中的振动 附近。 解决方案：直升机结构10设置有连接在能够以激励频率相对运动的机身12和框体17之间的多个致动器19.致动器以基本对应于激励频率的频率连续振荡 通过液体加压流体的供给源20。 附接到选定位置处的转子叶片的传感器21适于产生表示相应选定位置处的动态变化的信号，计算机22处理信号并提供输出信号，用于控制由致动器产生的施加力的相位和幅度 并且用于改变力的相位和幅度特性，以便补偿旋转系统的动态特性的变化，从而降低机身结构中的整体振动水平。 版权所有（C）2007，JPO＆INPIT

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