摘要
为了研究h=8 km,Ma=2条件附近导弹飞行试验中输入设计对气动参数辨识精度的影响,验证气动力模型的有效性,以方波信号为基础设计了3种开环舵偏指令。通过开环飞行弹道仿真试验,采用递推最小二乘法,对多项式非线性气动力模型中的气动参数进行了辨识。气动参数辨识结果表明,单级方波,偶极方波,"211"多级方波3种输入用于气动参数辨识是可行的,辨识精度是可接受的,辨识所用的纵向三自由度气动力模型是有效的。
In order to study the influence of input design on accuracy of aerodynamic parameters identification when h = 8 km,Ma = 2 in flight test,three open-loop commands of control surface deflection based on square wave signal are designed. In the open-loop flight trajectory simulation test,recursive least squares method is used to estimate the parameters of nonlinear aerodynamic model. The aerodynamic parameters identification results show that it is feasible to use three inputs including single square wave,double square wave,＂211＂multistep square wave. The identification accuracy is acceptable. The longitudinal aerodynamic model of three degrees of freedom used for identification is effective.
作者
杨闯
张弫
YANG Chuang ZHANG Zben(Beijing Institute of Electronic System Engineering,Beijing 100854, China)
出处
《现代防御技术》
北大核心
2017年第5期35-41,71,共8页
Modern Defence Technology
关键词
战术导弹
气动参数辨识
输入设计
递推最小二乘
气动模型
飞行试验
tactical missile
aerodynamic parameter identification
input design
recursive least squares
aerodynamic model
flight test
