基于迎角分区的全局飞行器气动参数辨识方法

doi:10.12305/j.issn.1001-506X.2023.11.26

Abstract

Abstract:

In order to comprehensively consider the global aerodynamic nonlinear characteristics of the aircraft and meet the requirements of efficient global aerodynamic parameter identification of the aircraft, an improved aerodynamic parameter identification method based on the angle of attack partition is proposed. The angle of attack partition method of the orthogonal decision tree is used to divide the angle of attack variables involving a large range into multiple intervals, and the recursive least squares are used to estimate the aerodynamic derivatives for each interval, realizing the identification of linear aerodynamic characteristics in each interval. By introducing the transition method of weighted function, the calculation criteria of local model transformation to global model are given to ensure the continuity of the whole model. Finally, the aerodynamic parameter identification and comparative analysis of the angle of attack subarea are carried out through a certain aircraft model. The results show that the angle of attack subarea identification is in good agreement and has higher computational efficiency compared with the traditional global identification method, which shows the effectiveness and advantages of the angle of attack subarea identification method.

Key words: angle of attack partition, identification of aerodynamic parameters, weighting function, global modeling

CLC Number:

TP18

Jianwen ZANG, Xiaoye BI, Zhao JIN, Hao LIU, Ming YAN. Global aircraft aerodynamic parameter identification method based on angle of attack partitioning[J]. Systems Engineering and Electronics, 2023, 45(11): 3588-3596.

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References 34

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参数	数值
全机重量/kg	9 295.44
机翼面积/m²	27.87
平均几何弦长	9.144
转动惯量	85 552.1

参数	真值	辨识值	相对误差/%
m_z^α	-0.509 7	-0.498 8	2.138 5
m_z^δ_z	-0.663 6	-0.644 3	2.908 3
m_z^ω_z	-2.131 4	-2.165 4	1.595 1

参数	真值	辨识值	相对误差/%
C_L^α	-3.800 3	-3.823 6	0.615 7
C_L^δ_z	-0.483 0	-0.480 7	0.473 9

误差	迎角分区/%	传统全局/%
m_z^α平均相对误差	2.14	9.046
m_z^δ_z平均相对误差	2.91	8.75
m_z^ω_z平均相对误差	1.60	5.47
C_L^α平均相对误差	0.62	7.27
C_L^δ_z平均相对误差	0.47	4.63

试验序号	2°分区	3°分区	5°分区	传统全局
1	1.626	2.341	2.835	4.174
2	1.553	2.431	3.015	4.208
3	1.477	2.362	2.986	4.066
4	1.592	2.387	2.962	4.154
5	1.498	2.377	2.896	4.137
平均值	1.549	2.380	2.939	4.148

Global aircraft aerodynamic parameter identification method based on angle of attack partitioning

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