一种涡轴发动机控制系统自适应扭振抑制方法研究

推进技术 ›› 2018, Vol. 39 ›› Issue (3): 695-702.

一种涡轴发动机控制系统自适应扭振抑制方法研究

汪勇,张海波

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016

发布日期:2021-08-15
作者简介:汪勇，男，硕士生，研究领域为航空发动机建模及控制。
基金资助:
国家自然科学基金(51576096)；南京航空航天大学研究生创新基地(实验室)开放基金(kfjj20170221)。

Study on Adaptive Torsional Vibration Suppression of Turbo-Shaft Engine Control System

Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing 210016，China and Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为了解决直升机机动飞行时涡轴发动机控制系统扭振不稳定性问题，根据扭矩动力传递链特点，设计了一种基于最小均方差(LMS)的自适应滤波器，以抑制自由涡轮转速中的扭振动态，并与常规的陷波滤波器效果进行了对比。仿真结果表明，在定旋翼转速下，陷波滤波器和基于LMS的自适应滤波器均能抑制1.90Hz对应的固定扭振分量，但后者能使扭振幅值降低至5%以下，滤波效果明显优于前者；同时，变旋翼转速飞行时，发动机端的扭振基频率会随着转速变化在1.30～2.20Hz变动，此时常规陷波滤波器不再适用，而基于LMS的自适应滤波器仍可显著抑制扭振动态。

关键词: 直升机；发动机；扭振抑制；陷波滤波器；自适应滤波器

Abstract: In order to solve the problem of torsional vibration instability during helicopter maneuvering flight， with analysis of the torque transmission train， the adaptive filter based on least mean square deviation algorithm(LMS) is designed to do torsional vibration dynamic suppression of free turbine and compared with conventional notch filter in the effect of torsional vibration suppression. It is shown that both the notch filter and the adaptive filter based on LMS can eliminate the torsional vibration at the fixed frequency of 1.90Hz in the constant rotor speed， but the latter can reduce the amplitude of torsional vibration to 5% or less， whose filter effect is better than the former. Meanwhile， when the helicopter flies in the variable rotor speed， the low order torsional vibration frequency of the turbo-shaft engine will vary from 1.30Hz to 2.20Hz and the conventional notch filter is no longer applicable， nevertheless， the torsional vibration can still be significantly suppressed by utilizing adaptive filter based on LMS.

Key words: Helicopter；Engine；Torsional vibration suppression；Notch filter；Adaptive filter

汪勇,张海波. 一种涡轴发动机控制系统自适应扭振抑制方法研究[J]. 推进技术, 2018, 39(3): 695-702.

WANG Yong ,ZHANG Hai-bo. Study on Adaptive Torsional Vibration Suppression of Turbo-Shaft Engine Control System[J]. Journal of Propulsion Technology, 2018, 39(3): 695-702.

参考文献

[1] Peng M. Parametric Instability Investigation and Stability Based Design for Transmission Systems Containing Face-Gear Drives[D]. KNO_xville: University of Tennessee, 2012.
[2] Peng M, DeSmidt H, Saribay Z B, et al. Parametric Instability of Face-Gear Drives with a Spur Pinion[C]. Virginia: Proceedings of American Helicopter Society 67th Annual Forum, 2011.
[3] 朱自冰, 朱如鹏, 鲍和云. 直升机尾传动系统扭转振动建模与特性[J]. 航空动力学报, 2013, 28(2): 432-438.
[4] 许兆棠. 直升机传动系统扭转振动的分析[J]. 工程力学, 2012, 29(9): 330-336.
[5] Smith B J, Zagranski R D. Next Generation Control System for Helicopter Engines[C]. Washington DC: 57th Annual Forum of AHS, 2001: 1617-1626.
[6] Zahradník P, Vlcek M. Fast Analytical Design Algorithms for FIR Notch Filters[J]. Circuits and Systems I: Regular Papers, IEEE Transactions on, 2004, 51(3): 608-623.
[7] Lee D H, Lee J H, Ahn J W. Mechanical Vibration Reduction Control of Two-Mass Permanent Magnet Synchronous Motor Using Adaptive Notch Filter with Fast Fourier Transform Analysis[J]. IET Electric Power Applications, 2012, 6(7): 455-461.
[8] 李胜泉, 杨征山, 孙健国. 多滤波器并联方式解决直升机动力传动链扭振耦合[J]. 航空动力学报, 2006, 21(3): 606-609.
[9] Germanowski P J, Stille B L, Strauss M P. Technology Assessment for Large Vertical-Lift Transport Tiltrotors[M]. California: National Aeronautics and Space Administration, Ames Research Center, 2010.
[10] Han D, Wang J, Smith E C, et al. Transient Loads Control of a Variable Speed Rotor During Lagwise Resonance Crossing[J]. AIAA Journal, 2013, 51(1): 20-29.
[11] Endwell O Daso. NASA Overview: Fundamental Aeronautics Program Research Activities on Noise Impacts[C]. Washington: Noise Impacts Roadmap Annual Meeting, 2011.
[12] Gloria K Yamauchi. NASA Subsonic Rotary Wing Project, Multidisciplinary Analysis & Technology Development:Overview[C]. Georgia: Fundamental Aeronautics Program Annual Meeting, 2009.
[13] 陈萌, 马艳红, 刘书国, 等. 航空发动机整机有限元模型转子动力学分析[J]. 北京航空航天大学学报, 2007, 33(9): 1013-1016.
[14] 徐敏. 直升机传动系统机械扭振计算与试验联合建模[J]. 振动、测试与诊断, 2004, 24(1): 41-45.
[15] 顾仲权, 杨景新. 直升机传动系统扭转振动特性分析[J]. 南京航空航天大学学报, 1997, 29(6): 674-678.
[16] 廖光煌, 焦洋, 李秋红, 等. 涡轴发动机高精度实时部件级模型研究[J]. 推进技术, 2016, 37(1): 25-33. (LIAO Guang-huang, JIAO Yang, LI Qiu-hong, et al. Research on High Accuracy Real-Time Component-Level Modeling Method for Turbo-Shaft Engine[J]. Journal of Propulsion Technology, 2016, 37(1): 25-33.)
[17] Litt J S, Edwards J M, DeCastro J A. A Sequential Shifting Algorithm for Variable Rotor Speed Control[J].Virginia Beach: Annual Forum Proceedings-American Helicopter Society, 2007, 63(2).
[18] 张海波, 姚文荣, 陈国强. 涡轴发动机/直升机综合控制仿真平台设计[J]. 推进技术, 2011, 32(3): 383-390. (ZHANG Hai-bo, YAO Wen-tong, CHEN Guo-qiang. Design of a Numeric Simulation Platform for Integrated Turbo-Shaft Engine /Helicopter Control System[J]. Journal of Propulsion Technology, 2011, 32(3):383-390.)
[19] Hopkins S A, Ruzicka G C, Ormiston R A. Analytical Investigations of Coupled Rotorcraft/Engine/Drive Train Dynamics[C]. Bridgeport: Proceedings of the American Helicopter Society 2nd International Aeromechanics Specialists Conference, 1995.
[20] Zhu Z, Gao X, Cao L, et al. Analysis on the Adaptive Filter Based on LMS Algorithm[J]. Optik-International Journal for Light and Electron Optics, 2016, 127(11):4698-4704.
[21] He Y P, Zhang H D. Design of Adaptive Filter Based on Matlab and Simulink[M]. Heidelberg: Springer Berlin, 2011: 292-297.
[22] 张凤莉, 卢娜. 自适应滤波器设计及MatLab实现研究[J]. 科技资讯, 2013, (17): 1-4.　　　　　　　　　　　　　*　收稿日期:2016-11-29；修订日期:2017-01-16。基金项目:国家自然科学基金(51576096)；南京航空航天大学研究生创新基地(实验室)开放基金(kfjj20170221)。作者简介:汪勇,男,硕士生,研究领域为航空发动机建模及控制。E-mail: wangyong1994327@163.com(编辑:梅瑛)