三角翼俯仰振荡的非定常气动力降阶方法研究  

Delta Wing Pitching Oscillation of Unsteady Aerodynamic Reduced Order Method Research

作　　者：郭嘉瑞 关世玺[1] 李立州[1] 贾凯 常晶 GUO Jiarui;GUAN Shixi;LI Lizhou;JIA Kai;CHANG Jing(School of Mechatronics Engineering North University of China,Taiyuan 030051,China)

机构地区：[1]中北大学机电工程学院

出　　处：《弹箭与制导学报》2018年第6期85-90,共6页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家自然科学基金(51775518)资助

摘　　要：为辨识三角翼俯仰振荡的气动力与力矩,利用单输入Volterra级数,提出了一种非定常气动力降阶方法。采用小波变换压缩模型的辨识参数个数,在两种平均迎角下,采用降阶方法预测3°与5°幅值三角翼正弦振荡的升力与俯仰力矩系数,研究了一阶、二阶Volterra核对气动响应的线性与非线性分量在时域和频域内的辨识效果。结果表明随着平均迎角的增加,三角翼俯仰振荡的气动力及力矩响应的线性与非线性分量均明显增大。In order to identify the aerodynamic forces and moments of the delta wing pitch oscillation,an unsteady aerodynamic reduction method is proposed by using the single input Volterra series.The number of identification parameters of the model is compressed by wavelet transform.The lift and pitch moment coefficients for sinusoidal oscillations of 3°and 5°amplitude delta wings are predicted at two average angles of attack using reduced order method.The linear and nonlinear components of the first-order and second-order Volterra kernels in the time domain and frequency domain are studied.The results show that the linear and nonlinear components of the aerodynamic and torque responses of the delta wing pitching oscillation increase significantly with the increase of the average angle of attack.

关 键 词：三角翼 非线性 VOLTERRA级数 降阶模型 小波变换 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]