摘要
在各轴扭转运动方程的基础上,用振型叠加原理求得中间减速器及尾减速器的传动比不等于1时尾传动系统扭转振动的解,并分析了中间减速器及尾减速器的传动比对直升机尾传动系统扭转振动的影响。其结果表明:与中间减速器及尾减速器的传动比等于1的尾传动系统相比,中间减速器或尾减速器的传动比接近且大于1时,水平传动轴和尾斜轴的扭转频响函数的最大幅值增大,尾传动系统的第2阶扭转固有频率增大,第3阶扭转固有频率变化不大,大于第3阶的扭转固有频率近似不变。
Based on the torsional motion equation of shafts, the solution of torsional vibration of a tail drive system, whose transmission ratio of an intermediate gearbox and a tail rotor gearbox is not equal to 1, is obtained by the superposition principle of vibration modes. Then, the effect of transmission ratio on torsional vibration of a helicopter tail drive system is analyzed. Results show that when transmission ratio of an intermediate gearbox or a tail rotor gearbox is slightly larger than 1, the maximum amplitude of torsional response of an intermediate drive shaft and a tail drive shaft is larger compared with the case of transmission ratio beging 1. The second torsional frequncy of a helicopter tail drive system increases, the third changes less, the frequencies of modes higher than three change little.
出处
《工程力学》
EI
CSCD
北大核心
2009年第12期249-256,共8页
Engineering Mechanics
关键词
直升机
尾传动系统
扭转角位移
传动比
振型叠加原理
helicopter
tail drive system
torsional angular displacement
transmission ratio
superposition principle of mode of vibration
