FL-52风洞Ф1.5 m直径共轴刚性旋翼试验台研制

Development ofФ1.5 m Diameter Coaxial Rigid Rotor Test Stand for FL-52 Wind Tunnel

为满足国内高速共轴对转旋翼气动特性及流动机理风洞试验研究的需要,在中国航空工业空气动力研究院FL-52声学风洞开展了Ф1.5 m直径共轴刚性旋翼试验台的研制(简称共轴旋翼试验台)。该共轴旋翼试验台由试验台架系统和旋翼测控系统组成,通过一台高功率密度交流变频电机驱动上下旋翼同步反转,可实现旋翼主轴倾角、旋翼转速、旋翼总距及周期变距等同步精准控制功能。通过共轴旋翼试验台地面模态测试及动平衡调整,排除了试验台转速频率与固有频率的共振关联性;利用该共轴旋翼试验台开展1.5 m直径旋翼风洞试验。结果表明:在悬停和前飞状态下,配平策略合理,悬停状态上旋翼效率大于下旋翼,扭矩配平状态下,上旋翼拉力在总拉力中的占比变化不大。

To meet the needs of the wind tunnel test research on the aerodynamic characteristics and flow mechanism of high-speed coaxial rotor,theФ1.5 m diameter coaxial rigid rotor test stand was developed in the FL-52 acoustic wind tunnel of Aviation Industry Aerodynamics Research Institute of China(referred to as the coaxial rotor test stand).The coaxial rotor test stand was composed of test stand system,rotor measurement and control system.A high power density AC frequency conversion motor drove the upper and lower rotors to reverse synchronously,which can realize the synchronous and accurate control functions such as rotor spindle inclination,rotor speed,rotor total pitch and periodic pitch.Through the ground mode test and dynamic balance adjustment of the coaxial rotor test stand,the resonance correlation between the rotating frequency and the natural frequency of the test stand was excluded.The wind tunnel test results of 1.5 m diameter rotors were carried out by using the coaxial rotor test stand.The results show that the trimming strategy is reasonable in hovering and forward flight states,the efficiency of the upper rotor is higher than that of the lower rotor in hovering state,and the proportion of the pulling force of the upper rotor in the total pulling force is not changed much in the torque trimming state.