Research on accuracy assessment method of aerodynamic parameters identified from wind tunnel free-flight test data

Zhang Tianjiao; Wang Qing; He Kaifeng; Qian Weiqi

doi:10.11729/syltlx20160148

Volume 31 Issue 1

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2017 > 31(1): 39-46

Zhang Tianjiao, Wang Qing, He Kaifeng, et al. Research on accuracy assessment method of aerodynamic parameters identified from wind tunnel free-flight test data[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(1): 39-46. doi: 10.11729/syltlx20160148

Citation:

PDF( 5857 KB)

Research on accuracy assessment method of aerodynamic parameters identified from wind tunnel free-flight test data

doi: 10.11729/syltlx20160148

Zhang Tianjiao^{1, 2
,
,},
Wang Qing^{1, 2},
He Kaifeng^{1, 2},
Qian Weiqi^{1, 2}

1.
State Key Laboratory of Aerodynamics, Mianyang Sichuan 621000, China
2.
China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Received Date: 2016-10-08
Rev Recd Date: 2016-11-30
Publish Date: 2017-02-25

Abstract

Abstract

The conventional Cramér-Rao lower bounds method is too optimistic to be a good quantitative assessment of the accuracy of aerodynamic parameters identified from the wind tunnel free-flight test data, considering the colored noise in the measurement data. This paper introduces a technique, that modified covariance matrix method, to process the residuals from a conventional maximum likelihood estimation to compute the accurate Cramér-Rao lower bounds for colored residuals. The modified accuracy assessment method is validated by Monte Carlo simulation and wind tunnel tests of pointed cone models with the semi-cone angle being 10°. The identified results indicate that the Cramér-Rao lower bounds calculated by the modified covariance matrix method are 3~5 times the quantity of the conventional. The modified results can be used as an accurate and impersonal assessment of the aerodynamic parameters estimated, which are consistent with the sample standard errors for the estimated parameters for colored residuals.
- free-flight,
- wind tunnel test,
- colored noise,
- aerodynamic parameter identification,
- accuracy assessment method

FullText(HTML)

References(23)

References

[1]	张守言. 模型自由飞试验[M]. 北京: 国防工业出版社, 2002.
[2]	Prislin R H. High amplitude dynamic stability characteristics of a blunt 10-degree cones[R]. AIAA-66-465, 1966.
[3]	Klein V. Determination of stability and control parameters of a light airplane from flight data two estimation methods[R]. NASA TP-1306, 1979.
[4]	Maine R E, Iliff K W. The theory and practice of estimating the accuracy of dynamic flight-determined coefficients[R]. NASA RP-1077, 1981.
[5]	Morelli E A, Klein V. Determining the accuracy of maximum likelihood parameter estimates with colored residuals[R]. NASA CR-194893, 1994.
[6]	Morelli E A, Klein V. Accuracy of aerodynamic model parameters estimated from flight test data[J]. Journal of Guidance, Control and Dynamics, 1997, 20 (1): 74-80. doi: 10.2514/2.3997
[7]	蔡金狮. 飞行器系统辨识学[M]. 北京: 国防工业出版社, 2003.
[8]	汪清, 钱炜祺, 何开锋. 导弹气动参数辨识与优化输入设计[J]. 宇航学报, 2008, 29 (3): 789-793. http://www.cnki.com.cn/Article/CJFDTOTAL-YHXB200803009.htm Wang Q, Qian W Q, He K F. Aerodynamic parameter identification and optimal input design for missile[J]. Journal of Astrinautics, 2008, 29 (3): 789-793. http://www.cnki.com.cn/Article/CJFDTOTAL-YHXB200803009.htm
[9]	Murphy P C. A methodology for airplane parameter estimation and confidence interval determination in nonlinear estimation problems[R]. NASA RP-1077, 1981.
[10]	Murphy P C, Klein V. Maximum likelihood algorithm using an efficient scheme for computing sensitivities and parameter confidence intervals[R]. AIAA-84-2084, 1984.
[11]	Murphy P C. Efficient computation of confidence intervals of parameters[R]. AIAA-87-2624, 1987.
[12]	Iliff K W, Maine R E. Further observations on maximum likelihood estimates of stability and control characteristics obtained from flight data[R]. AIAA-77-1133, 1977.
[13]	Maine R E, Iliff K W. Use of Cramér-Rao bounds on flight data with colored residuals[J]. Journal of Guidance, Control and Dynamics, 1981, 4 (2): 207-213. doi: 10.2514/3.56073
[14]	Balakrishnan A V, Maine R E. Improvements in aircraft extraction programs[R]. NASA CR-145090, 1975.
[15]	Morelli E A, Klein V. Determing the accuracy of aerodynamic model parameters estimated from flight test data[R]. NASA CR-203351, 1995.
[16]	Bendat J S, Piersol A G. Random data analysis and measurement procedures[M]. 2nd ed. New York: Wiley, 1986.
[17]	方振平, 陈万春, 张曙光. 航空飞行器飞行动力学[M]. 北京: 北京航空航天大学出版社, 2005.
[18]	张天姣, 钱炜祺, 何开锋, 等. 基于最大似然法的风洞自由飞试验气动力参数辨识技术研究[J]. 实验流体力学, 2015, 29 (5): 8-14. http://www.syltlx.com/CN/abstract/abstract10868.shtml Zhang T J, Qian W Q, He K F, et al. Research on aerodynamic parameter identification technology in wind tunnel free-flight test based on Maximum Likelihood Estimation[J]. Journal of Experiments in Fluid Mechanics, 2015, 29 (5): 8-14. http://www.syltlx.com/CN/abstract/abstract10868.shtml
[19]	顾均晓. 飞行稳定性和自动控制[M]. 北京: 国防工业出版社, 2008.
[20]	贾区耀, 杨益农, 陈农. 风洞自由飞实验测量M=5, 10°半锥角尖锥、钝锥气动动稳特性[J]. 空气动力学学报, 2007, 25 (2): 24-28. Jia Q Y, Yang Y N, Chen N. Measurement of aerodynamic dynamic stability characters of M=5 pointed and blunted cones with semi-cone angles equal 10° in wind tunnel free flight experiment[J]. Acta Aerodynamica Sinica, 2007, 25 (2): 24-28.
[21]	贾区耀, 杨益农. 锥动失稳与无控飞行器弹着点精度[J]. 气动物理—理论与应用, 2007, 2 (2): 183-186. Jia Q Y, Yang Y N. Conical lose of stability and unguided aircraft impact accuracy[J]. Physics of Gases: Theory and Applications, 2007, 2 (2): 183-186.
[22]	陈农, 杨益农, 贾区耀. 小迎角下钝锥气动动态稳定性[C]//全国第九届分离流, 旋涡和流动控制会议论文集, 2002: 74-83.
[23]	马家驩, 潘文欣, 翟曼玲, 等. 10°尖锥标模高超声速动导数的实验测量[J]. 空气动力学学报, 1997, 15 (4): 452-457. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX199704004.htm Ma J H, Pan W X, Zhai M L, et al. 10° Cone model free flight experiment in hypersonic impulse type wind tunnel for dynamic stability measurement[J]. Acta Aerodynamica Sinica, 1997, 15 (4): 452-457. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX199704004.htm