共轴刚性旋翼直升机与单旋翼直升机操稳特性对比研究

Comparative study of control and stability characteristics between single rotor and coaxial rigid rotor helicopter

为研究共轴刚性旋翼直升机与传统单旋翼直升机飞行动力学特性的差异,分别针对两种构型的直升机建立了飞行动力学模型。根据全机平衡方程进行了不同飞行速度下两种构型直升机的配平特性验证计算;依据“小扰动”假设建立了线化运动方程组,对悬停及前飞状态下的样例直升机进行了操稳特性的对比计算与分析。结果表明:两种构型样例直升机在操稳特性总体表现较为相似。在稳定性表现上,单旋翼构型直升机的非周期模态、螺旋模态及前飞时的操纵性能均优于共轴刚性旋翼构型直升机;不同于单旋翼构型,悬停及前飞状态下共轴刚性旋翼直升机的滚转与偏航操纵性能均变差。

To investigate the differences in flight dynamics characteristics between single rotor and coaxial rigid-rotor helicopter, flight dynamics models were developed based on the characteristics of the selected single rotor and coaxial rigid rotor helicopter configuration. According to the equilibrium equation of the helicopter, the trim characteristics of the two configuration samples at each flight speed were validated. A linear motion equation set was established based on the “ small disturbance” assumption to carrying out a contrast calculation and analysis of the sample helicopter’s control and stability characteristics in the states of hovering and forward-flying. The results show that the overall control and stability characteristics in two helicopter configurations are relatively similar. The stability of the single-rotor sample helicopter performance is better than that of the coaxial model helicopter in non-periodic mode and helical mode of the stability and the control characteristics during forward flight. Unlike the single rotor configuration, the roll and yaw control capability of the coaxial rigid rotor helicopter in the hover and forward flight become worse.