Φ3m直升机旋翼气动噪声试验台动力系统研制

Development ofΦ3m Helicopter Rotor Driving System for the Aeroacoustic Test

在声学风洞配套直升机旋翼气动噪声试验台是开展直升机噪声机理和降噪措施研究的重要基础。动力系统作为试验台的关键子系统,主要由120 kW永磁交流伺服电机及相应的冷却装置、变频驱动装置、监控系统等组成。其中高功率密度电机设计、驱动选型及转速精确控制、安全监控设计等是动力系统研制中的若干关键技术。上述技术的解决,使系统具备了调速范围宽、转速精度高、运行安全可靠等特性,达到了研制目的。

The development of helicopter rotor aeroacoustic test rig in acoustic wind tunnel is important for the study of helicopter noise mechanism and reduction.As the key subsystem,the driving system is composed of 120 kW permanent magnet motor,corresponding cooling system,frequency converter,monitoring system and so on.The design of high power density motor,the selection of drive type,the precise control of speed and the design safety monitoring are the key technologies.The solution of above technologies makes the system have the characteristics of wide speed range,high speed accuracy,safe and reliable operation.The purpose of development is achieved.