舵缝尺寸对导弹气动特性仿真精度的影响研究  

Numerical simulation study of the effect of rudder slit size on missile aerodynamic characteristics

在线阅读下载全文

作  者:张彦杰 于勇[1] 陈明亮 ZHANG Yanjie;YU Yong;CHEN Mingliang(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;IAT Automobile Technology Co.,Ltd.,Guangzhou 510700,China)

机构地区:[1]北京理工大学宇航学院,北京100081 [2]阿尔特汽车技术股份有限公司,广州510700

出  处:《兵器装备工程学报》2025年第2期63-71,79,共10页Journal of Ordnance Equipment Engineering

摘  要:为了研究弹身和舵之间舵缝尺寸对导弹气动特性影响,针对文献中的标模导弹模型,使用国家数值风洞GridStar和FlowStar软件,采用重叠网格方法,通过CFD数值模拟方法计算导弹在不同迎角、不同马赫数工况下舵缝对于法向力系数、俯仰力矩系数的影响。结果表明:随着舵缝尺寸的增加,数值模拟得到的法向力系数和俯仰力矩系数与实验的误差显著增加,选取0.05倍翼展长度的舵缝尺寸能够保证绝大多数工况误差都在8%以内,满足工程精度要求;选取0.02倍翼展长度的舵缝尺寸大多数工况误差都在6%以内;比起舵缝尺寸,舵偏造成的流场拓扑变化更显著。Aiming at the influence of the rudder slit size between the body and rudder on the aerodynamic characteristics of the missile,for the standard model missile in the literature,the normal force coefficient and the pitching moment coefficient of the missile at different angles of attack and different Mach numbers with different rudder slit size are calculated using computational fluid dynamics(CFD)with National Numerical Wind Tunnel GridStar,and FlowStar software and overset mesh method is used.The results show that:with the increase of rudder slit size,the error of aerodynamic coefficients between numerical simulation and experiments increases significantly.The rudder slit size of 0.05 times the wingspan length,and it can ensure that the error of the majority of the working conditions is within 8%,which meets the engineering accuracy requirements.The rudder slit size of 0.02 times the wingspan length was chosen to be within 6%error for majority conditions.The topological change of the flow field caused by the rudder bias is more significant than that of the rudder slit size.

关 键 词:舵缝尺寸 气动特性 国家数值风洞 重叠网格 工程精度 

分 类 号:V211[航空宇航科学与技术—航空宇航推进理论与工程]

 

参考文献:

正在载入数据...

 

二级参考文献:

正在载入数据...

 

耦合文献:

正在载入数据...

 

引证文献:

正在载入数据...

 

二级引证文献:

正在载入数据...

 

同被引文献:

正在载入数据...

 

相关期刊文献:

正在载入数据...

相关的主题
相关的作者对象
相关的机构对象