| 直升机发动机控制系统与旋翼/动力传动扭振系统耦合稳定性分析 |
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| 引用本文： | 王辉,陈华,刘志文.直升机发动机控制系统与旋翼/动力传动扭振系统耦合稳定性分析[J].直升机技术,2002(4):19-23. |
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| 作者姓名： | 王辉 陈华 刘志文 |
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| 作者单位： | 中国直升机设计研究所,景德镇,333001 |
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| 摘 要： | 直升机的发动机通过传动系统驱动旋翼及尾浆,形成了一个机械扭振系统,这个系统又与发动机控制系统相互耦合构成一个闭环的动力学系统。本文针对某型直升机建立了相应闭环系统的数学模型,分析、判断闭环系统的稳定性及稳定裕度;研究了使用下陷滤波器来改善耦合系统稳定性的设计思路和参数调整的试验方法。
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| 关 键 词： | 直升机 旋翼 动力传动 耦合稳定性分析 |
THE STABILITY ANALYSIS OF THE COUPLED SYSTEM CONSISTS OF HELICOPTER ENGINE CONTROL SYSTEM、ROTOR AND DRIVE TRAIN |
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| Authors: | WANG Hui CHENG Hua LIU Zhi-wen |
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| Abstract: | A mechanic system of torsional oscillation consists of helicopter' s engine , drive systenu rotor and tail rotor. This torsion-al system is also coupled with the fuel control of turbine engine. This paper investigates this closed- loop feedback system, formulates the mathematical model, analysis the stability and stable margin of this closed- loop feedback system. Develops a resolution to improve the instability of the couple system by using notch filter in the engine fuel control system. |
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| Keywords: | helicopter rotor drive train analysis of coupled system's stability |
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