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

系统工程与电子技术 ›› 2023, Vol. 45 ›› Issue (11): 3588-3596.doi: 10.12305/j.issn.1001-506X.2023.11.26

基于迎角分区的全局飞行器气动参数辨识方法

臧剑文¹, 毕晓烨²^,*, 金钊², 刘浩¹, 闫明¹

1. 大连理工大学航空航天学院, 辽宁大连 116024
2. 沈阳飞机设计研究所, 辽宁沈阳 110035

收稿日期:2022-08-12 出版日期:2023-10-25 发布日期:2023-10-31
通讯作者: 毕晓烨
作者简介:臧剑文(1998—), 男, 硕士研究生, 主要研究方向为飞行器导航、制导与控制
毕晓烨(1985—), 女, 高级工程师, 硕士, 主要研究方向为飞行感知技术设计、飞管系统试验设计
金钊(1994—), 男, 助理工程师, 硕士, 主要研究方向为飞行感知技术
刘浩(1996—), 男, 硕士研究生, 主要研究方向为航行器参数辨识与弹道设计
闫明(2000—), 男, 硕士研究生, 主要研究方向为飞行控制技术
基金资助:
自然科学基金(U2141229);航空科学基金(2019ZC063001)

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

Jianwen ZANG¹, Xiaoye BI²^,*, Zhao JIN², Hao LIU¹, Ming YAN¹

1. School of Aeronautics and Astronautics, Dalian University of Technology, Dalian 116024, China
2. Shenyang Aircraft Design & Research Institute, Shenyang 110035, China

Received:2022-08-12 Online:2023-10-25 Published:2023-10-31
Contact: Xiaoye BI

摘要/Abstract

摘要：

针对综合考虑飞行器全局气动非线性特性, 面向高效全局飞行器气动参数辨识需求, 提出了一种基于迎角分区的改进气动参数辨识方法, 采用轴正交决策树的迎角分区方法, 将涉及大范围的迎角变量划分为多个区间, 对每一区间使用递归最小二乘来估计气动导数, 实现在每个区间内对线性气动特性进行辨识。通过引入加权函数的过渡方法, 给出局部模型转化全局建模的计算准则, 保证了整个模型的连续性。最后, 通过某型飞机模型开展了迎角分区气动参数辨识及对比分析工作, 结果表明迎角分区辨识吻合较好, 且与传统全局辨识方法相比计算效率更高, 说明了迎角分区辨识方法的有效性和优势。

关键词: 迎角分区, 气动参数辨识, 加权函数, 全局建模

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

中图分类号:

TP18

臧剑文, 毕晓烨, 金钊, 刘浩, 闫明. 基于迎角分区的全局飞行器气动参数辨识方法[J]. 系统工程与电子技术, 2023, 45(11): 3588-3596.

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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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

基于迎角分区的全局飞行器气动参数辨识方法

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

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