摘要
简易制导弹药是在制式弹药的基础上增加了修正执行机构。为了研究简易制导弹药伸缩式舵机的气动特性对方案弹道的影响,以某火箭弹为对象,分别利用MATLAB和ANSYS对其气动特性进行了工程和数值计算,并将结果与风洞实验数据进行比较。结果表明,工程计算和数值计算的最大误差分别为16.6%和7.1%。
Compared with the model ammunition,the simply guided ammunitions has the correction implement mechanism.In order to research influence of the aerodynamic characteristics of the telescopic steering gear of the simply guided munitions on the program trajectory,the aerodynamic characteristics of the model ammunition is calculated by MATLAB engineering method and numerical ANSYS method.The maximum errors of engineering calculation and numerical simulation with the experimental data are 16.6% and 7.1%.
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2013年第5期682-686,共5页
Journal of Nanjing University of Science and Technology
关键词
简易制导弹药
雷诺平均方程
工程计算
数值仿真
气动特性
simply guided ammunitions
Navier-Stokes equations
engineering calculation
numerical simulation
aerodynamic characteristics
