摘要
针对现有模型在非定常气动参数辨识中存在的局限性,该文对大迎角机动过程非定常气动特性进行了研究,提出了一种建模方法。该方法结合物理机理,以广义气动导数模型为基础,受到Wiener模型建模思想的启发,建立了动态特性和静态特性分解的模块化级联模型。通过平方相关系数评价各模型项对非定常特性的贡献,确定最终模型结构,并给出了参数估计中相关的数据处理方法。用类F-22模型的风洞试验数据验证了提出的辨识方法,结果表明:模型辨识精度高,相对误差可控制在5%以内,可以有效地描述工程中非定常气动参数。
Existing models cannot accurately identify aircraft at high angles of attack due to the unsteady aerodynamic characteristics high angle of attack flight.This paper presents a model using a dynamic block with a static block based on a general aerodynamic derivatives model,which was inspired by the modelling structure of the Wiener model.The model identification is then based on a squared correlation coefficient that estimates the contribution of each model term.The data processing procedure for the parameter estimations is given.Wind tunnel tests with a model similar to an F-22 are used to verify the method.The results show that the method is able to accurately identify the unsteady aerodynamic parameters with a relative error below 5%.The model can effectively describe the unsteady aerodynamic parameters.
作者
张婉鑫
朱纪洪
ZHANG Wanxin ZHU Jihong(Department of Computer Science and Technology Tsinghua University, Beijing 100084, China)
出处
《清华大学学报(自然科学版)》
EI
CAS
CSCD
北大核心
2017年第7期673-679,共7页
Journal of Tsinghua University(Science and Technology)
基金
国家自然科学基金资助项目(61673240
61603210)
关键词
非定常气动力
大迎角
建模
参数辨识
风洞试验
气动导数
模块化
平方相关系数
unsteady aerodynamic
high angles of attack
modeling
parameter identification
wind tunnel test
aerodynamic derivative
block oriented
squared correlation coefficient