The invention discloses a statically unstable flying wing layout aircraft stability augmentation control method. The method specifically comprises that: a roll angle rate P signal and a sideslip anglesignal beta are introduced into an aircraft aileron rudder channel to obtain a stability augmentation controller of the aileron rudder channel; a yaw rate R and a sideslip angle signal beta are introduced into an aircraft resistance rudder channel to obtain a stability augmentation controller of the rudder channel; and the stability augmentation controller of the aileron rudder channel and the stability augmentation controller of the rudder channel jointly control the transverse and lateral stability of the aircraft. Rolling and yawing motions of the aircraft are matched, and it is guaranteedthat the aircraft has a stable and good Holland rolling damping ratio.

    本发明公开了一种静不稳定的飞翼布局飞行器增稳控制方法,具体为:在飞行器副翼舵通道中引入滚转角速率P信号和侧滑角信号β,得到副翼舵通道的增稳控制器;在飞行器阻力方向舵通道中引入偏航角速率R、侧滑角信号β,得到方向舵通道的增稳控制器;副翼舵通道的增稳控制器和方向舵通道的增稳控制器共同控制飞行器横侧向稳定。本发明使飞行器的滚转和偏航运动相匹配,保证飞行器拥有稳定良好的荷兰滚阻尼比。


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    Titel :

    Statically unstable flying wing layout aircraft stability augmentation control method


    Weitere Titelangaben:

    一种静不稳定的飞翼布局飞行器增稳控制方法


    Beteiligte:
    LI CHUNTAO (Autor:in) / LI XUEBING (Autor:in) / ZHANG PENG (Autor:in) / MENG CHONG (Autor:in) / XIE MINGYANG (Autor:in) / ZHAO ZHENHUA (Autor:in) / SU ZIKANG (Autor:in)

    Erscheinungsdatum :

    2020-06-12


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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