FL-52 风洞Ф1. 5 m 直径共轴刚性 旋翼试验台研制.

To meet the needs of the wind tunnel test research on the aerodynamic characteristics and flow mechanism of highspeed coaxial rotor, the Ф1. 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. [ABSTRACT FROM AUTHOR]