民机极限飞行状态的动态气动力试验与建模

doi:10.7527/S1000-6893.2020.23664

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

民机极限飞行状态的动态气动力试验与建模

岑飞^1,2, 李清¹, 刘志涛², 蒋永², 张磊²

1. 清华大学自动化系, 北京 100084;
2. 中国空气动力研究与发展中心低速空气动力研究所, 绵阳 621000

收稿日期:2019-11-19 修回日期:2020-03-07 出版日期:2020-08-15 发布日期:2020-04-10
通讯作者: 李清 E-mail:liqing@tsinghua.edu.cn
基金资助:
国家自然科学基金（61771281）；新一代人工智能重大项目（2018AAA0101605）；2018年工业和信息化部工业转型升级专项（ZB1825005）；清华大学自主科研计划（2018Z05JZY015）

Unsteady aerodynamics test and modeling of civil aircraft under extreme flight conditions

CEN Fei^1,2, LI Qing¹, LIU Zhitao², JIANG Yong², ZHANG Lei²

1. Department of Automation, Tsinghua University, Beijing 100084, China;
2. Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2019-11-19 Revised:2020-03-07 Online:2020-08-15 Published:2020-04-10
Supported by:
National Natural Science Foundation of China(61771281); the New Generation Artificial Intelligence Major Project of China(2018AAA0101605); the 2018 Industrial Internet Innovation and Development Project(ZB1825005); the Tsinghua University Initiative Scientific Research Program(2018Z05JZY015)

摘要/Abstract

摘要： 飞行失控是造成民机灾难性航空事故的重要因素，飞行失控中飞机难以避免超出正常飞行包线范围，进入具有复杂非线性和非定常动态气动特性的极限飞行状态。本文开展典型民机布局飞机极限飞行状态的动导数、大振幅试验，对大迎角动态气动力的参数影响规律以及非线性、非定常特性进行分析和建模。结果表明，在飞机失速到过失速区域，飞行姿态快速变化过程中动态气动力的非线性和非定常特征显著；在动导数试验和建模中，考虑运动角速率的影响，可以预示气动力非线性的迎角范围，并捕捉到关于飞机动稳定性演化的关键特征；利用Goman-Khrabrov状态空间模型结合大振幅试验，可以确定模型中表征非定常特征的关键时间常数，获得特定极限飞行状态运动中的非定常动态气动力特性。研究方法和结果为开展民机极限飞行状态的动态气动力风洞试验设计与建模提供了一个可行途径，能改进飞机飞行失控预防、极限状态改出、飞行模拟训练和飞行事故分析等。

关键词: 风洞试验, 民机, 大迎角, 非定常气动力, Goman-Khrabrov模型

Abstract: Loss of control is an important cause of catastrophic aviation accidents, possibly exposing the aircraft under extreme flight conditions with complex nonlinear and unsteady aerodynamic characteristics beyond the normal flight envelope. The dynamic derivative and large amplitude wind tunnel tests under the extreme flight conditions are conducted to analyze the impact factors for dynamic aerodynamics and the nonlinear and unsteady characteristics. Results show that the nonlinear and unsteady characteristics of dynamic aerodynamics are significant in stall to incipient spin regions; for dynamic derivative test and modeling, the impact of the angular velocity of motion can be considered to predict the range of angle of attack of aerodynamic nonlinearity and capture the key characteristics related to the dynamic stability of flight maneuvers; using the Goman-Khrabrov state space model combined with the large amplitude test, the key time constants of the unsteady characteristics in the model can be determined, and the unsteady aerodynamic characteristics in the specific extreme flight state motion can be obtained. The research methods and results provide a promising way for the design and modeling of the dynamic aerodynamic test of civil aircraft under extreme flight conditions.

Key words: wind tunnel tests, civil aircraft, high angle of attack, unsteady aerodynamics, Goman-Khrabrov model

中图分类号:

V211.7

岑飞, 李清, 刘志涛, 蒋永, 张磊. 民机极限飞行状态的动态气动力试验与建模[J]. 航空学报, 2020, 41(8): 123664-123664.

CEN Fei, LI Qing, LIU Zhitao, JIANG Yong, ZHANG Lei. Unsteady aerodynamics test and modeling of civil aircraft under extreme flight conditions[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(8): 123664-123664.

参考文献 25

[1]	CAST/ICAO Common Taxonomy Team. Aviation occurrence categories:Definitions and usage notes[EB/OL]. (2017-12-31)[2019-11-10].http://www.intlaviationstandards.org/Documents/OccurrenceCategoryDefinitions.pdf.
[2]	Boeing Aviation Safety Group. Statistical summary of commercial jet airplane accidents, worldwide operations, 1959-2017[EB/OL]. (2017-10-31)[2019-11-10]. http://www.boeing.com/resources/boeingdotcom/company/about_bca/pdf/statsum.pdf.
[3]	BELCASTRO C M, FOSTER J V, SHAH G H, et al. Aircraft loss of control problem analysis and research toward a holistic solution[J]. Journal of Guidance, Control, and Dynamics, 2017, 40(4):733-775.
[4]	伍开元. 民机空难相关非定常气动力问题研究[J]. 流体力学实验与测量, 2003, 17(2):1-9. WU K Y. Unsteady aerodynamics in fatal accidents[J]. Experiments and Measurements in Fluid Mechanics, 2003, 17(2):1-9(in Chinese).
[5]	汪清, 钱炜祺, 丁娣. 飞机大迎角非定常气动力建模研究进展[J]. 航空学报, 2016, 37(8):2331-2347. WANG Q, QIAN W Q, DING D. A review of unsteady aerodynamic modeling of aircrafts at high angle of attack[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(8):2331-2347(in Chinese).
[6]	孙海生, 姜裕标, 黄勇, 等. 现代战斗机非定常空气动力学及其风洞实验研究[J]. 空气动力学学报, 2008, 26(增刊):59-65. SUN H S, JIANG Y B, HUANG Y, et al. Unsteady aerodynamics of modern fighter plane and experiment research in W.T.[J]. Acta Aerodynamica Sinica, 2008, 26(Supplement):59-65(in Chinese).
[7]	KALVISTE J. Use of rotary balance and forced oscillation test data in six degrees of freedom simulation[C]//9th AIAA Atmospheric Flight Mechanics Conference. Reston:AIAA, 1982.
[8]	ETKIN B, REID L D. Dynamics of atmospheric flight:stability and control[M]. New York:John Wiley& Sons Inc, 1972:264-293.
[9]	TOBAK M, SCHIFF L B. Aerodynamic mathematical modelling-basic concepts:AGARD LS-114[R]. 1981.
[10]	GOMAN M, KHRABROV A. State-space representation of aerodynamic characteristics of an aircraft at high angles of attack[J]. Journal of Aircraft, 1994, 31(5):1109-1115.
[11]	汪清, 蔡金狮. 飞机大攻角非定常气动力建模与辨识[J]. 航空学报, 1996,17(4):391-398. WANG Q, CAI J S. Unsteady aerodynamic modeling and identification of airplane at high angles of attack[J]. Acta Aeronautica et Astronautica Sinica, 1996,17(4):391-398(in Chinese).
[12]	龚正, 沈宏良. 非定常气动力的结构自适应神经网络建模方法[J]. 飞行力学, 2007, 25(4):13-16. GONG Z, SHEN H L. Structure self-adapting ANN method in modeling of unsteady aerodynamics[J]. Flight Dynamics, 2007, 25(4):13-16(in Chinese).
[13]	WANG Z, LAN C E, BRANDON J. Fuzzy logic modeling of nonlinear unsteady aerodynamics[C]//23rd AIAA Atmospheric Flight Mechanics Conference. Reston:AIAA, 1998.
[14]	WANG Q, QIAN W Q, HE K F. Unsteady aerodynamic modeling at high angles of attack using support vector machines[J]. Chinese Journal of Aeronautics, 2015,28(3):659-668.
[15]	GOMAN M, KHRABROV A, USOLTSEV S P. Unsteady aerodynamic model for large amplitude maneuvers and its parameter identificaton[C]//The Inernational Federation of Automatic Control, 11th IFAC Symposium on System Identification. Kitakyushu:IFAC,1997.
[16]	SMITH M S. Analysis of wind tunnel oscillatory data of the X-31A aircraft:NASA CR-1999-208725[R]. Washington, D.C.:NASA, 1999.
[17]	汪清, 何开锋, 钱炜祺,等. 飞机大迎角空间机动气动力建模研究[J]. 航空学报, 2004,25(5):447-451. WANG Q, HE K F, QIAN W Q, et al. Aerodynamic modeling of spatial maneuvering aircraft at high angle of attack[J]. Acta Aeronautica et Astronautica Sinica, 2004,25(5):447-451(in Chinese).
[18]	BRANDON J M, FOSTER J V, SHAH G H, et al. Comparison of rolling moment characteristics during roll oscillation for a low and a high aspect ratio configuration[C]//2004 AIAA Atmospheric Flight Mechanics Conference and Exhibit. Reston:AIAA, 2004.
[19]	Industry Airplane Upset Recovery Training Aid Team. Airplane upset recovery training aid, Rev. 2[M]. Virginia:Flight Safety Foundation, 2008:368-379.
[20]	RIVERS M. Common research model[EB/OL]. (2012-02-10)[2018-10-10].https://commonresearchmodel.larc.nasa.gov/geometry/.
[21]	ATINAULT O, HUE D. Design of a vertical tail for the CRM configuration:RT 1/21960 GMT/DAAP[R]. Châtillon Cedex:ONERA, 2014.
[22]	VASSBERG J, DEHAAN M A, RIVERS M. Development of a common research model for applied CFD validation studies[C]//26th AIAA Applied Aerodynamics Conference. Reston:AIAA, 2008.
[23]	李周复. 风洞特种试验技术[M]. 北京:航空工业出版社, 2010:208-209. LI Z F. Special test techniques in wind tunnel[M]. Beijing:Aircraft Industry Press, 2010:208-209(in Chinese).
[24]	PASHILKAR A A, PRADEEP S. Unsteady aerodynamic modelling using multivariate orthogonal polynomials:AIAA-1999-4014[R]. Reston:AIAA, 2013.
[25]	FAN Y G, LUTZE F H. Identification of an unsteady aerodynamic model at high angles of attack:AIAA-1996-3407[R]. Reston:AIAA, 1996.

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

民机极限飞行状态的动态气动力试验与建模

Unsteady aerodynamics test and modeling of civil aircraft under extreme flight conditions

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献 25

相关文章 15

编辑推荐

Metrics

本文评价

[1]	孙朋朋, 刘平安, 樊枫, 曾伟. 悬停状态共轴刚性旋翼机身气动干扰特性[J]. 航空学报, 2024, 45(9): 529284-529284.
[2]	王畅, 何龙, 徐栋霞, 唐敏, 马率, 吴希明. 共轴刚性旋翼桨毂流动控制减阻研究[J]. 航空学报, 2024, 45(9): 529084-529084.
[3]	张卫国, 唐敏, 武杰, 彭先敏, 章贵川, 聂博文, 王亮权, 李超群. 倾转旋翼机风洞试验综述[J]. 航空学报, 2024, 45(9): 530114-530114.
[4]	聂博文, 王亮权, 黄志银, 何龙, 杨仕鹏, 颜鸿涛, 章贵川. 复合式高速无人直升机飞行动力学建模与控制策略设计[J]. 航空学报, 2024, 45(9): 529848-529848.
[5]	刘柳, 向先宏, 张宇飞, 陈海昕, 魏闯, 朱剑, 杨普. 一种高升阻比非常规翼身融合燕尾气动布局[J]. 航空学报, 2024, 45(6): 629630-629630.
[6]	李军府, 陈晴, 王伟, 韩忠华, 谭玉婷, 丁玉临, 谢露, 乔建领, 宋科, 艾俊强. 一种先进超声速民机低声爆高效气动布局设计[J]. 航空学报, 2024, 45(6): 629613-629613.
[7]	李海星, 周峰, 颜巍, 白峰, 赵克良. 砂纸冰对民机平尾气动特性的影响[J]. 航空学报, 2024, 45(2): 128657-128657.
[8]	李学良, 李创创, 苏伟, 吴杰. 分布式粗糙元对高超声速边界层不稳定性的影响试验[J]. 航空学报, 2024, 45(2): 128627-128627.
[9]	张桂玮, 刘召庆, 朱镭, 张衡, 田玮, 李伟光, 杨智春. 地面颤振模拟试验技术研究进展[J]. 航空学报, 2024, 45(10): 29229-029229.
[10]	许岭松, 吴渊, 朱东宇, 张付昆, 刘昱. FL⁃61结冰风洞翼型俯仰振荡机构研制[J]. 航空学报, 2023, 44(S2): 729296-729296.
[11]	刘宇, 秦梦婕, 王强, 易贤. 含盐海水飞沫的结冰风洞试验相似准则[J]. 航空学报, 2023, 44(S2): 729297-729297.
[12]	杨秋明, 朱永峰, 陈华伟, 刘晓林. 镂空图案化电加热组件防冰性能试验研究[J]. 航空学报, 2023, 44(S2): 729334-729334.
[13]	高世琦, 丁博, 解旭祯, 李铮, 陈林, 钱首元, 焦子涵, 白光辉. 等离子体激励在高速流动中的减阻机制[J]. 航空学报, 2023, 44(S2): 729373-729373.
[14]	李春鹏, 钱战森, 孙侠生. 远程民机变弯度机翼后缘外形变形矩阵气动设计[J]. 航空学报, 2023, 44(7): 127335-127335.
[15]	金毅, 孙姝, 郭赟杰, 谭慧俊, 张悦. 超声速可调进气道内流双解现象及其节流特性[J]. 航空学报, 2023, 44(7): 127134-127134.