直升机双旋翼气流纵向稳定性恢复方法仿真

Simulation of Recovery Method for Longitudinal Stability of Helicopter Dual Rotor Airflow

直升机双旋翼在工作过程当中受到气流的纵向干扰,出现稳定性偏移现象,需要消耗较长的恢复时间。对直升机双旋翼气流纵向稳定性恢复方法进行优化设计。建立直升机运动坐标系,并在坐标系上构建直升机双旋翼的运动状态方程,通过运动状态方程来判断双旋翼的运行状态。在双旋翼的不同状态下计算气流纵向动力,计算结果即为稳定性恢复幅值。最终利用安装在直升机上的稳定恢复控制器,分别通过气流压缩分离、驱动急拉杆/急推杆以及电压稳定恢复三个步骤,实现直升机双旋翼的稳定性恢复。通过仿真得出结论,直升机双旋翼气流纵向稳定性恢复方法的平均稳定性恢复时间为19.93s,比传统方法节省13.91s,上述方法的稳定性恢复时间较短。

The helicopter dual rotors are disturbed by the longitudinal air flow during the working process,resulting in stability deviation.In addition,the helicopter dual rotor requires a long recovery time.In this paper,a method of restoring the longitudinal stability of helicopter dual-rotor airflow was optimized and designed.At first,the motion coordinate system of helicopter was established,and then the motion state equation was constructed in the coordinate system.Secondly,the moving state of helicopter dual rotors was judged by the motion state equation.Thirdly,the longitudinal power of dual rotors was calculated under different conditions,so that the calculated results were the stability recovery amplitude.Finally,the stabilization recovery controller installed on the helicopter was used to achieve the stabilization recovery for the helicopter dual rotors through three steps:air compression separation,the pull rod/push rod driving,and voltage stabilization recovery.Simulation results show that the average stability recovery time of the proposed method is 19.93s,which saves 13.91s compared with the traditional method.Meanwhile,the stability recovery time of the proposed method is shorter.