The invention relates to a calibration method for a pitch-throttle curve of an oil-driven unmanned helicopter. The calibration method comprises the following steps that S1,the unmanned helicopter is controlled to work, and the pitch and throttle opening parameters of the unmanned helicopter in the working process are recorded: S11, the pitch is increased according to set parameters in the workingprocess of the unmanned helicopter; an engine of the unmanned helicopter is kept at a rated working speed at each pitch point, and a set time T1 is kept; and S12, when the engine of the unmanned helicopter cannot keep the rated working rotating speed or the opening degree of a throttle valve of the engine of the unmanned helicopter reaches the limit position, the unmanned helicopter is controlledto reduce the throttle opening degree and the total distance until the unmanned helicopter is in an initial state, and a set time T2 is kept in the initial state of the unmanned helicopter; S2, the unmanned helicopter is controlled to stop; and S3, the pitch and the throttle opening degree of the unmanned helicopter are fitted into the curve. According to the calibration method for the pitch-throttle curve of the oil-driven unmanned helicopter and a system thereof, the pitch-throttle curve of the oil-driven unmanned helicopter can be accurately calibrated, the operation process can be effectively simplified, and the operation efficiency is improved.

    本发明是一种油动无人直升机桨距‑油门曲线标定方法,包括:S1.控制无人直升机工作,记录无人直升机在工作过程中的桨距和油门开度参数:S11.在无人直升机工作过程中按照设定参数提升桨距;在每一个桨距点保持无人直升机的发动机处于额定工作转速,保持设定时间T1;S12.当无人直升机的发动机不能保持额定工作转速或者无人直升机的发动机的节气门的开度达到极限位置时,则控制无人直升机降低油门开度及降低总距直至无人直升机的初始状态,在无人直升机的初始状态保持设定时间T2;S2.控制无人直升机停机;S3.将无人直升机的桨距、油门开度拟合成曲线;能够准确地对油动无人直升机桨距‑油门的曲线进行标定,并且能够有效简化操作过程中,提升操作效率。


    Access

    Download


    Export, share and cite



    Title :

    Calibration method for pitch-throttle curve of oil-driven unmanned helicopter and system thereof


    Additional title:

    油动无人直升机桨距-油门曲线标定方法及系统


    Contributors:

    Publication date :

    2020-12-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / F02D CONTROLLING COMBUSTION ENGINES , Steuern oder Regeln von Brennkraftmaschinen / G08C Übertragungssysteme für Messwerte, Regel-, Steuer- oder ähnliche Signale , TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS



    Response of helicopter rotor to oscillatory pitch and throttle movements

    Carpenter, P.J. / Peitzer, H.E. | Engineering Index Backfile | 1949


    Response of a helicopter rotor to oscillatory pitch and throttle movements

    Carpenter, Paul J / Peitzer, Herbert E | NTRS | 1949


    Response of a helicopter rotor to oscillatory pitch and throttle movements

    Carpenter, Paul J. / Peitzer, Herbert E. | TIBKAT | 1949


    Unmanned helicopter rotor variable pitch hinge structure

    JIN XI / ZENG DONG / RAN JUNSHUANG et al. | European Patent Office | 2021

    Free access

    Unmanned helicopter rotor variable pitch hinge structure

    ZENG DONG | European Patent Office | 2021

    Free access