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    FLIGHT CONTROL AUGMENTATION SYSTEM AND METHOD FOR HIGH ASPECT RATIO AIRCRAFT
    321.
    发明公开
    FLIGHT CONTROL AUGMENTATION SYSTEM AND METHOD FOR HIGH ASPECT RATIO AIRCRAFT 有权
    FLUGSTEUERUNGAUGMENTATIONSSYSTEM并与高延展飞机程序

    公开(公告)号：EP2930102A1

    公开(公告)日：2015-10-14

    申请号：EP15162566.2

    申请日：2015-04-07

    Applicant: Arnold, Marc

    Inventor： Arnold, Marc

    IPC: B64C9/12 ,  B64C13/16 ,  B64C19/02 ,  G05D1/00

    CPC classification number: B64C13/28 ,  B64C9/10 ,  B64C9/12 ,  B64C9/18 ,  B64C9/20 ,  B64C13/04 ,  B64C13/16 ,  B64C19/02 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/141 ,  G05D1/0661 ,  G05D1/0676 ,  Y02T50/32 ,  Y02T50/44

    Abstract: A control augmentation system (200) for high aspect ratio aircraft has aileron/ flaperon and throttle position sensors (208, 210, 212, 214); spoiler and flap controls (219, 222); a mode switch (224) with manual, and landing modes; and a controller (202) driving left and right spoiler and flap servos (230, 232, 234), the controller (202) including at least one processor (240) with memory (242) containing firmware configured to: when the mode switch (224) is in manual mode, drive both spoiler servos (230, 232) to a symmetrical position according to the spoiler control (219); when the mode switch (224) is in landing mode, drive the left spoiler to a position dependent on aileron and throttle position, and the right spoiler to a position dependent on aileron and throttle position, the left and right spoiler positions differing whenever ailerons (104) are not centered, and an average of spoiler positions is more fully deployed when the throttle position is at a low-power setting than when the throttle position is at a high-power setting.

    Abstract translation: 的控制增强系统（200），用于高纵横比飞行器具有副翼/襟副翼和节流位置传感器（208，210，212，214）; 扰流片和对照组（219，222）; 模式开关（224）具有手动和着陆模式; 和控制器（202）驱动左和右阻流板和襟翼伺服（230，232，234），所述控制器（202）包括至少一个处理器（240）与存储器（242）包含固件被配置为：当模式开关（ 224）处于手动模式时，驱动这两个伺服系统的扰流板（230，232），以对称的位置gemäß在扰流板控制（219）; 当模式开关（224）是（在着陆模式，驱动左扰流到依赖于副翼和节气门位置，和右阻流板的位置依赖于副翼和油门位置的位置，左和右阻流板的位置不同每当副翼 104）不集中，并且平均扰流板的位置更完全展开当节气门位置是在低功率设定比当节气门位置是在高功率设置。

    MICRO UNMANNED AERIAL VEHICLE AND METHOD OF CONTROL THEREFOR
    322.
    发明公开
    MICRO UNMANNED AERIAL VEHICLE AND METHOD OF CONTROL THEREFOR 有权
    无人微弹箭与方法及其控制

    公开(公告)号：EP2909689A2

    公开(公告)日：2015-08-26

    申请号：EP13785582.1

    申请日：2013-10-22

    Applicant: BCB International Limited ,  Torquing Group Ltd.

    Inventor： REEDMAN, Ivan ,  DAVIES, Barry

    IPC: G05D1/10

    CPC classification number: B64C39/024 ,  B64C19/00 ,  B64C39/028 ,  B64C2201/00 ,  B64C2201/14 ,  B64C2201/141 ,  B64C2230/00 ,  B64C2230/02 ,  G01S15/06 ,  G01S15/88 ,  G01S15/89 ,  G01S15/8913 ,  G01S15/8929 ,  G01S15/8993 ,  G01S15/93 ,  G05D1/0088 ,  G05D1/0202 ,  G05D1/101 ,  G05D1/102 ,  Y10S367/909

    Abstract: A micro unmanned aerial vehicle or drone ("UAV") 10 is remotely controlled through an HMI (309), although this remote control is supplemented by and selectively suppressed by an on-board controller (302). The controller operates to control the generation of a sonar bubble that generally encapsulates the UAV. The sonar bubble, which may be ultrasonic in nature, is produced by a multiplicity of sonar lobes generated by specific sonar emitters associated with each axis of movement for the UAV. The emitters produce individual and beamformed sonar lobes (80-102) that partially overlap to provide stereo or bioptic data in the form of individual echo responses detected by axis- specific sonar detectors (40-68). In this way, the on-board controller is able to interpret and then generate 3-D spatial imaging of the physical environment in which the UAV is currently moving or positioned. The controller is therefore able to plot relative and absolute movement of the UAV through the 3-D space by recording measurements from on-board gyroscopes (342), magnetometers (344) and accelerometers (346). Data from the sonar bubble can therefore both proactively prevent collisions with objects by imposing a corrective instruction to rotors (12-18) and other flight control system and can also assess and compensate for sensor drift.

    Method and device for controlling the attitude of an unmanned aerial vehicle using only one axis of three-axis magnetometer
    330.
    发明公开
    Method and device for controlling the attitude of an unmanned aerial vehicle using only one axis of three-axis magnetometer 审中-公开
    用于控制使用的三轴磁力计的仅一个轴的无人驾驶飞行器的位置的方法和装置

    公开(公告)号：EP2236417A1

    公开(公告)日：2010-10-06

    申请号：EP10151453.7

    申请日：2010-01-22

    Applicant: Honeywell International Inc.

    Inventor： Fitzpatrick, David

    IPC: B64C39/02 ,  G01R33/02 ,  G05D1/08

    CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141 ,  G01R33/0206 ,  G05D1/0858

    Abstract: Measurement of only one axis of a three-axis magnetometer is used to control the performance of at least one corrective action on an unmanned aerial vehicle ("UAV"). In one example, a method includes receiving from a three-axis magnetometer a measurement representative of an attitude of a UAV, wherein the measurement is of only one axis of the magnetometer, comparing the measurement to an allowable range of attitudes, determining that the measurement is not within the allowable range of attitudes, and performing at least one corrective action on the UAV.

    Abstract translation: 仅一个三轴磁力计的轴的测量值用于在无人驾驶飞行器（“UAV”），以控制上的至少一个校正动作的性能。 在一个实施例中，一种方法包括：从一个三轴磁力计接收测量代表一个UAV的姿势的，worin测量是磁力的仅一个轴的，测量在态度容许范围进行比较来的，确定性的挖掘做了测量 不是态度在容许范围内，以及对所述UAV至少一个校正动作。

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