共轴式直升机旋翼气动干扰对航向操纵的影响  

Effect of Aerodynamic Interactions between Dual Rotors of Coaxial Helicopter on Course Control

作　　者：邓彦敏[1] 胡继忠[1] 陶然[1] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系,北京100083

出　　处：《飞行力学》2003年第3期21-24,共4页Flight Dynamics

摘　　要：利用共轴式旋翼风洞实验结果,结合轻型共轴式直升机M16飞行中的现象,分析了上下旋翼气动干扰对共轴式直升机过渡飞行中航向操纵的影响。介绍了直升机由悬停转入垂直上升、平飞中加减速和转入爬升与下滑等过程中,由于上下旋翼干扰发生了变化,使直升机航向发生偏转后飞机的反应情况,以及在这种情况下应进行的相应操纵。所得结果对研究共轴式直升机的操稳特性有重要意义。The paper presents the effect of change in aerodynamic interactions between upper and lower rotors of the coaxial helicopter on the course control in several transition flight states, including transition from hover to vertical rise, speed up and down in horizontal flight, transition from horizontal flight to climb and descent along inclined flight path. The course of the coaxial helicopter is deflected due to change of rotor thrust and shape of rotor wake in these transition flight states. The results achieved were important for investigating the control and stability of the coaxial helicopter.

关 键 词：共轴式直升机 旋翼 气动干扰 航向操纵 影响 过渡飞行 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]