高超声速飞行器再入过程改进气动系数模型  

Modified aerodynamic coefficient models of hypersonic vehicle in reentry phase

作　　者：孙勇[1] 段广仁[1] 张卯瑞[1] 张泽[1] 

机构地区：[1]哈尔滨工业大学控制理论与制导技术研究中心,黑龙江哈尔滨150001

出　　处：《系统工程与电子技术》2011年第1期134-137,共4页Systems Engineering and Electronics

基　　金：国家自然科学基金(60710002)资助课题

摘　　要：针对高超声速飞行器再入过程气动系数模型和参数辨识问题,基于公开的气动系数数据,综合考虑攻角和马赫数两个主要因素,分析了气动系数与二者的函数关系,建立了高超声速飞行器的改进升力系数和阻力系数模型,采用非线性最小二乘法进行模型参数辨识,得到参数辨识结果。将已知的气动数据与改进气动系数模型计算值进行对比,升力系数和阻力系数的相对误差平均值均小于5.10%,表明所建立的改进气动系数模型具有较高的精度,可以用于高超声速飞行器再入轨迹优化和仿真。The aerodynamic coefficients model of hypersonic vehicle in reentry phase and parameters identification are considered.The relationships between the aerodynamic coefficients and main factors including angle of attack and Mach number are analyzed based on the public aerodynamic coefficients database.The modified lift and drag coefficients models are built and the parameters of the models are identified by the nonlinear least square method.The comparisons between the database and the value by the modified aerodynamic coefficients models show that the averages of the relative errors are all less than 5.10%,which demonstrates that the modified aerodynamic coefficients models have the high precision and can be used in reentry trajectory optimization and simulation.

关 键 词：参数辨识 气动系数模型 非线性最小二乘 高超声速飞行器 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]