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基于状态空间法建立了直升机的全量方程,通过计算直升机对航向操纵的脉冲响应及横向稳定性特征根,分析了两种尾桨转速方案对旋翼转速优化直升机的横航向操稳特性的影响。计算结果表明,与尾桨转速不随旋翼转速变化方案相比,虽然尾桨转速随旋翼转速联动时的直升机横航向操纵性减小了一些,稳定性也轻微降低,但差异较小。因此综合比较功率节约和结构减重的优势,可以确定转速联动方案更适用于旋翼转速优化直升机。
Based on the state space method, the helicopter full-mass equation is established. By calculating the helicopter’s impulse response and transverse stability characteristic root of the heading control, the effects of the two tail rotor speed solutions on the rotor-speed optimization helicopter’s lateral handling characteristics are analyzed. The calculation results show that, compared with the scheme that the rotor speed does not change with the rotor speed, the helicopter lateral steering maneuverability decreases slightly when the rotor speed is linked with the rotor speed, and the stability decreases slightly, but the difference is small. Therefore, a comprehensive comparison of power saving and structural weight loss advantages, can determine the speed linkage scheme is more suitable for rotor speed optimization helicopters.