主动侧杆引导下的Ⅱ型驾驶员诱发振荡抑制

doi:10.7527/S1000-6893.2018.21861

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

主动侧杆引导下的Ⅱ型驾驶员诱发振荡抑制

许舒婷, 谭文倩, 孙立国, 屈香菊

北京航空航天大学航空科学与工程学院, 北京 100083

收稿日期:2017-11-13 修回日期:2018-07-20 出版日期:2018-08-15 发布日期:2018-03-13
通讯作者: 谭文倩 E-mail:tanwenqian@buaa.edu.cn
基金资助:
国家自然科学基金（11502008）；航空科学基金（2017ZA51002）

Using active side-stick to prevent category Ⅱ pilot-induced oscillations

XU Shuting, TAN Wenqian, SUN Liguo, QU Xiangju

School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China

Received:2017-11-13 Revised:2018-07-20 Online:2018-08-15 Published:2018-03-13
Supported by:
National Natural Science Foundation of China (11502008);Aeronautical Science Foundation of China (2017ZA51002)

摘要/Abstract

摘要： 现代飞机采用放宽静稳定性构型和侧杆控制器操纵，使得舵面速率饱和引起的驾驶员诱发振荡（PIO）成为影响飞行品质的一个重要因素。针对舵面速率饱和引起的Ⅱ型PIO问题，设计了主动侧杆人感系统，其弹性系数随着舵面偏转速率饱和的发生而改变，从而达到抑制速率饱和的作用。基于主动侧杆引导下的人机闭环系统模型，仿真分析和飞行品质评价验证表明，基于系统误差在线调整人感系统弹性系数，能够降低舵机速率饱和的程度，改善飞行品质，有效抑制舵机速率饱和引起的Ⅱ型PIO。

关键词: 人感系统, 人感系统, 驾驶员诱发振荡, 驾驶员诱发振荡, Ⅱ型PIO抑制, Ⅱ型PIO抑制, 速率饱和, 速率饱和, 主动侧杆, 主动侧杆

Abstract: Modern fly-by-wire airframes are often designed to have relaxed static stability and side-stick control, making Pilot-Induced Oscillation (PIO) caused by actuator rate saturation as an important factor affecting flight qualities. In this paper, an active side-stick is designed as a means to alleviate pilot-induced oscillations due to actuator rate saturation. The stiffness of the active side-stick is changed with the actuator rate saturation, so as to mitigate the rate saturation. Based on the pilot-aircraft closed-loop system model with active side-stick, the simulation analysis and evaluation results show that the active side-stick to change the stiffness of the feel system can reduce the degree of saturation, improve flying qualities, and prevent category Ⅱ PIO due to actuator rate saturation effectively.

Key words: feel system, feel system, pilot-induced oscillations, pilot-induced oscillations, category Ⅱ PIO prevention, category Ⅱ PIO prevention, actuator rate saturation, actuator rate saturation, active side-stick, active side-stick

中图分类号:

V249.11

许舒婷, 谭文倩, 孙立国, 屈香菊. 主动侧杆引导下的Ⅱ型驾驶员诱发振荡抑制[J]. 航空学报, 2018, 39(8): 121861-121861.

XU Shuting, TAN Wenqian, SUN Liguo, QU Xiangju. Using active side-stick to prevent category Ⅱ pilot-induced oscillations[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(8): 121861-121861.

参考文献

[1] MITCHELL D G, HOH R H. Development of methods and devices to predict and prevent pilot-induced oscillations:AFRL-VA-WP-TR-2000-3046[R]. Wright-Patterson AFB, OH:U.S. Air Force Research Laboratory, 2000.
[2] MITCHELL D G, KLYDE D H. Identifying a pilot-induced oscillation signature:New techniques applied to old problems[J]. Journal of Guidance, Control, and Dynamics, 2008, 31(1):215-224.
[3] BRINDLEY J, COUNSELL J M, ZAHER O S, et al. Design and simulation of a non-linear, discontinuous, flight control system using rate actuated inverse dynamics[J]. Proceedings of the Institution of Mechanical Engineers, Part G:Journal of Aerospace Engineering, 2013, 227(4):632-646.
[4] MASARATI P, QUARANTA G, JUMP M. Experimental and numerical helicopter pilot characterization for aeroelastic rotorcraft-pilot coupling analysis[J]. Proceedings of the Institution of Mechanical Engineers, Part G:Journal of Aerospace Engineering, 2013, 227(1):125-141.
[5] HESS R A, SNELL S A. Flight control system design with rate saturating actuators[J]. Journal of Guidance, Control, and Dynamics, 1997, 20(1):90-96.
[6] LIEBST B S, CHAPA M J, LEGGETT D B. Nonlinear prefilter to prevent pilot-induced oscillations due to actuator rate limiting[J]. Journal of Guidance, Control, and Dynamics, 2002, 25(4):740-747.
[7] JAMES G. A comparison of nonlinear algorithms to prevent pilot-induced oscillations caused by actuator rate limiting[R]. Wright-Patterson AFB, OH:Air Force Institute of Technology, 2003.
[8] CHAPA M J. A nonlinear pre-filter to prevent departure and/or pilot-induced oscillations (PIO) due to actuator rate limiting[R]. Wright-Patterson AFB, OH:Air Force Institute of Technology, 1999.
[9] TURNER M C, POSTLETHWAITE I. A new perspective on static and low order anti-windup synthesis[J]. International Journal of Control, 2004, 77(1):27-44.
[10] EDWARDS C, POSTLETHWAITE I. Anti-windup and bumpless transfer schemes[J]. Automatica, 1998, 34(2):199-210.
[11] GATLEY S L, TURNER M C, POSTLETHWAITE I, et al. A comparison of rate-limit compensation schemes for pilot-induced-oscillation avoidance[J]. Aerospace Science and Technology, 2006, 10(1):37-47.
[12] ACOSTA D M, YILDIZ Y, CRAUN R W, et al. Piloted evaluation of a control allocation technique to recover from pilot-induced oscillations[J]. Journal of Aircraft, 2014, 52(1):130-140.
[13] YILDIZ Y, KOLMANOVSKY I V. A control allocation technique to recover from pilot-induced oscillations (CAPIO) due to actuator rate limiting[C]//American Control Conference (ACC), 2010. Piscataway, NJ:IEEE Press, 2010:516-523.
[14] YILDIZ Y, KOLMANOVSKY I V, ACOSTA D. A control allocation system for automatic detection and compensation of phase shift due to actuator rate limiting[C]//American Control Conference (ACC), 2011. Piscataway, NJ:IEEE Press, 2011:444-449.
[15] YILDIZ Y, KOLMANOVSKY I V. Stability properties and cross-coupling performance of the control allocation scheme CAPIO[J]. Journal of Guidance, Control, and Dynamics, 2011, 34(4):1190-1196.
[16] KLYDE D H, MCRUER D. Smart-cue and smart-gain concepts development to alleviate loss of control[J]. Journal of Guidance, Control, and Dynamics, 2009, 32(5):1409-1417.
[17] KLYDE D H, LIANG C Y. Approach and landing flight evaluation of smart-cue and smart-gain concepts[J]. Journal of Guidance, Control, and Dynamics, 2009, 32(4):1057-1070.
[18] LAMPTON A K, KLYDE D H, LEE D C, et al. Development of the SAFE-Cue system component mechanization for loss of control mitigation[C]//AIAA Science and Technology Forum and Exposition. Reston, VA:AIAA, 2014:13-17.
[19] KLYDE D H, LIANG C Y, RICHARDS N, et al. Use of active inceptor cueing to mitigate pilot-vehicle system loss of control[C]//AIAA Guidance, Navigation, and Control Conference. Reston, VA:AIAA, 2012.
[20] KLYDE D H, LAMPTON A K, ALVAREZ D J, et al. Flight test evaluation of the SAFE-Cue system for loss of control mitigation[C]//AIAA Guidance, Navigation, and Control Conference. Reston, VA:AIAA, 2014.
[21] XU S, TAN W, SUN L, et al. Survey on theory and method of pilot-aircraft system with intelligent control[C]//20173rd IEEE International Conference on Control Science and Systems Engineering (ICCSSE). Piscataway, NJ:IEEE Press, 2017:92-96.
[22] XU S, TAN W, EFREMOV A V, et al. Review of control models for human pilot behavior[J]. Annual Reviews in Control, 2017, 44:274-291.
[23] HESS R A. Unified theory for aircraft handling qualities and adverse aircraft-pilot coupling[J]. Journal of Guidance, Control, and Dynamics, 1997, 20(6):1141-1148.
[24] ZEYADA Y, HESS R A, SIWAKOSIT W. Aircraft handling qualities and pilot-induced oscillation tendencies with actuator saturation[J]. Journal of Guidance, Control, and Dynamics, 1999, 22(6):852-861.
[25] HESS R A, STOUT P W. Assessing aircraft susceptibility to nonlinear aircraft-pilot coupling/pilot-induced oscillations[J]. Journal of Guidance, Control, and Dynamics, 1998, 21(6):957-964.
[26] KLYDE D H, MCRUER D. Development of Smart-Cue and Smart-Gain concepts to alleviate loss of control[C]//AIAA Atmospheric Flight Mechanics Conference and Exhibit. Reston, VA:AIAA, 2008.
[27] VAN PAASSEN M M, VAN DER VAART J C, MULDER J A. Model of the neuromuscular dynamics of the human pilot's arm[J]. Journal of Aircraft, 2004, 41(6):1482-1490.
[28] VAN PAASSEN M M. Biophysics in aircraft control:A model of the neuromuscular system of the pilot's arm[D]. Delft:Delft University of Technology, 1994.
[29] KLYDE D H, LIANG C Y. Flight Assessment of pilot behavior with smart-cue and smart-gain concepts active[C]//AIAA Atmospheric Flight Mechanics Conference. Reston, VA:AIAA, 2009.
[30] Department of Defense. Flying qualities of piloted aircraft:MIL-HDBK-1797A[S]. Washington,D.C.:Department of Defense, 1997.
[31] LIU F, WANG L, TAN X. Digital virtual flight testing and evaluation method for flight characteristics airworthiness compliance of civil aircraft based on HQRM[J]. Chinese Journal of Aeronautics, 2015, 28(1):112-120.
[32] GUO L, ZHU M, NIE B, et al. Initial virtual flight test for a dynamically similar aircraft model with control augmentation system[J]. Chinese Journal of Aeronautics, 2017, 30(2):602-610.
[33] STEVENS B L, LEWIS F L. Aircraft control and simulation[M]. New York:Wiley, 1992.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

主动侧杆引导下的Ⅱ型驾驶员诱发振荡抑制

Using active side-stick to prevent category Ⅱ pilot-induced oscillations

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 9

编辑推荐

Metrics

本文评价

[1]	朱纪洪, 和阳, 黄志毅. 舵机特征模型及其故障检测方法[J]. 航空学报, 2015, 36(2): 640-650.
[2]	曹启蒙, 李颖晖, 徐浩军. 基于线性矩阵不等式的电传飞机人机闭环系统稳定域[J]. 航空学报, 2013, 34(1): 19-27.
[3]	孟捷;徐浩军;张建康. Ⅱ型PIO反馈与前馈抑制系统对比[J]. 航空学报, 2010, 31(9): 1701-1707.
[4]	李建平;杨朝旭;罗欣. 作动器速率饱和时的PIO抑制方法[J]. 航空学报, 2003, 24(3): 263-265.
[5]	吴蔚;方振平. 某电传操纵飞机的Ⅱ型PIO预测和抑制对策研究[J]. 航空学报, 2002, 23(3): 231-233.
[6]	高庆玉;方振平. 操纵系统非线性因素对飞机纵向驾驶员诱发振荡影响的探讨[J]. 航空学报, 2000, 21(1): 21-24.
[7]	王永熙. 飞行控制系统对驾驶员诱发振荡的影响[J]. 航空学报, 1997, 18(1): 17-21.
[8]	陈廷楠;徐浩军. 驾驶员诱发振荡的研究[J]. 航空学报, 1991, 12(8): 339-344.
[9]	冯亚昌;莫松峰;姚铁梅;徐鑫福. 纵向“人-机"组合系统的诱发振荡研究[J]. 航空学报, 1987, 8(8): 391-398.