The invention belongs to the technical field of overall design of helicopters, and particularly relates to a helicopter rotor rotating speed correction control law design method. Comprising the following steps: S1, acquiring static pressure and external atmospheric temperature, and calculating relative atmospheric density; calculating a corrected rotor speed omega1 based on the atmospheric density and the vacuum speed; s2, correcting the rotating speed of the rotor wing based on the rotating speed adjustment amplitude in the hovering state to obtain an unlimited corrected rotating speed omega2; s3, according to the adjusting range of the rotating speed of the rotor wing, calculating a corrected rotating speed omega3 considering boundary limitation; and S4, according to the rotor rotating speed change rate limitation, calculating to obtain the rotor target rotating speed omega of the current time step.

    本发明属于直升机总体设计技术领域,尤其涉及一种直升机旋翼转速修正控制律设计方法。包括:S1,获取静压和外部大气温度,计算相对大气密度;基于大气密度和真空速计算修正的旋翼转速Ω1;S2,基于悬停状态下的转速调整幅度对旋翼转速进行修正,得到无限制的修正转速Ω2;S3,根据旋翼转速的调节范围,计算考虑边界限制的修正转速Ω3;S4,根据旋翼转速变化速率限制,计算得到当前时间步的旋翼目标转速Ω。


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    Titel :

    Helicopter rotor rotating speed correction control law design method


    Weitere Titelangaben:

    一种直升机旋翼转速修正控制律设计方法


    Beteiligte:
    LYU YUZHU (Autor:in) / QIN CHONG (Autor:in) / XU JIANHUA (Autor:in) / DONG SHENGHUA (Autor:in) / ZHOU LINGLING (Autor:in) / ZHANG ZHIMING (Autor:in)

    Erscheinungsdatum :

    14.01.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / 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



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