Elimination of Coupling Instability Using Few Parallel Connection Notch Filters for Helicopter Rotor/Power Train

LI Sheng-quan; YANG Zheng-shan; SUN Jian-guo

Chinese

您当前的位置：

首页 >

文章列表页 >

Elimination of Coupling Instability Using Few Parallel Connection Notch Filters for Helicopter Rotor/Power Train

更新时间：2026-07-07

- Elimination of Coupling Instability Using Few Parallel Connection Notch Filters for Helicopter Rotor/Power Train
- Vol. 21, Issue 3, (2006)
- 作者机构：
  
  1. 南京航空航天大学能源与动力学院,江苏,南京,210016
  2. 中国一航动力控制系统研究所,江苏,无锡,214063
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2006
- 稿件说明：
移动端阅览
LI Sheng-quan, YANG Zheng-shan, SUN Jian-guo. Elimination of Coupling Instability Using Few Parallel Connection Notch Filters for Helicopter Rotor/Power Train[J]. 2006, 21(3).
DOI：

LI Sheng-quan, YANG Zheng-shan, SUN Jian-guo. Elimination of Coupling Instability Using Few Parallel Connection Notch Filters for Helicopter Rotor/Power Train[J]. 2006, 21(3). DOI：

摘要

为了解决直升机动力传动链扭振系统与动力控制系统的耦合不稳定性问题

提出了一种采用多个陷波滤波器并联组合、根据发动机不同的工作模态选择不同滤波器实现扭振滤波的方法。对陷波滤波器进行了改进

使得引入控制系统通频带的附加相移减小

降低了对系统控制性能的影响。通过直升机联合试验

验证了该方法是有效的。

Abstract

A solution was proposed which eliminated the coupling instability between helicopter power transmitting train torsional vibration system and power control system.A combination of notch filters in parallel and filters selected according to engine working modes have been used to achieve torsional vibration filtration.The modification of the notch filter made the extra phase-shifting introduced to the control system passband reduced and so the control performance was improved.The method was demonstrated successfully on a helicopter integrated test-bed.

关键词

Keywords

references

Views

384

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Development trends of aero turboshaft engines

Online optimization control of turboshaft engines based on variable inlet guide vane

Numerical simulation on the temperature field of a helicopter accessory cabin

Optimizing control of turboshaft engines based on variable rotor speed

Helicopoter coupled rotor/fuselage air resonance dynamic stability in forward flight

Related Author

ZOU Wangzhi

ZHENG Xinqian

YAO Wen-rong

XIE Yong-qi

YU Jian-zu

WANG Xian-wei

LI De-qiang

XUE Hai-feng

Related Institution

School of Aeronautic Science and Technology, Beijing Unirersty of Aeronautics and Astronautics

China Helicopter Research and Development Institute

Military Representative of PLA Navy at Angang

Naval Aeronautical Engineering Academy Qingdao Branch

School of Aeronautics Science and Technology, Beijing University of Aeronautics and Astronautics

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰