[1]唐玉发,张 合,徐国泰.基于MATLAB与ANSYS的火箭弹气动特性工程计算与数值仿真[J].南京理工大学学报(自然科学版),2013,37(05):682.
 Tang Yufa,Zhang He,Xu Guotai.Engineering calculation and numerical simulation of rocket aerodynamic characteristics based on MATLAB and ANSYS[J].Journal of Nanjing University of Science and Technology,2013,37(05):682.
点击复制

基于MATLAB与ANSYS的火箭弹气动特性工程计算与数值仿真
分享到:

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

卷:
37卷
期数:
2013年05期
页码:
682
栏目:
出版日期:
2013-10-31

文章信息/Info

Title:
Engineering calculation and numerical simulation of rocket aerodynamic characteristics based on MATLAB and ANSYS
作者:
唐玉发张 合徐国泰
南京理工大学 智能弹药技术国防重点实验室,江苏 南京 210094
Author(s):
Tang YufaZhang HeXu Guotai
Ministerial Key Laboratory of ZNDY,NUST,Nanjing 210094,China
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
Keywords:
simply guided ammunitions Navier-Stokes equations engineering calculation numerical simulation aerodynamic characteristics
分类号:
V211.3
文献标志码:
A
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%。
Abstract:
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%.

参考文献/References:

[1] 张民权,刘东方,王冬梅,等.弹道修正弹发展综述[J].兵工学报,2010,31(增刊2):127-130.
Zhang Minquan,Liu Dongfang,Wang Dongmei,et al.A summary for trajectory correction projectiles[J].Acta Armamentarii,2010,31(S2):127-130.
[2]洪元军,雷雅茹.国外弹道修正引信发展现状研究[J].探测与控制学报,2001,23(4):1-5.
Hong Yanjun,Lei Yaru.The current development of foreign trajectory correction fuze[J].Journal of Detection and Control,2001,23(4):1-5.
[3]易文俊,王中原,杨凯,等.基于脉冲控制的末段修正弹道研究[J].南京理工大学学报,2007,31(2):219-223.
Yi Wenjun,Wang Zhongyuan,Yang Kai,et al.Terminal correction trajectory based on impulse control[J].Journal of Nanjing University of Science and Technology,2007,31(2):219-223.
[4]常思江.某鸭式布局防空制导炮弹的飞行弹道特性与控制方案研究[D].南京:南京理工大学能源与动力工程学院,2011.
[5]史金光,王中原,常思江,等.鸭式制导炮弹气动外形优化设计方法研究[J].南京理工大学学报,2009,33(5):555-559.
Shi Jinguang,Wang Zhongyuan,Chang Sijiang,et al.Aerodynamic shape optimum design method for guided projictiles equipped with canards[J].Journal of Nanjing University of Science and Technology,2009,33(5),555-559.
[6]王中原,周卫平.外弹道设计理论与方法[M].北京:科学出版社,2004.
[7]沈仲书,刘亚飞.弹丸空气动力学[M].北京:国防工业出版社,1984.
[8]江帆,黄鹏.FLUENT高级应用与实例分析[M].北京:清华大学出版社,2008.
[9]武频,赵润祥,郭锡福.双组尾翼弹气动特性计算与分析[J].空气动力学学报,2002,20(4):411-415.
Wu Pin,Zhao Runxiang,Guo Xifu.Aerodynamic character calculation and analysis of two sets of empennages bullet[J].Acta Aerodynamica Sinica,2002,20(4):411-415.

备注/Memo

备注/Memo:
收稿日期:2012-06-29 修回日期:2013-02-05
作者简介:唐玉发(1986-),男,博士生,主要研究方向:简易制导控制技术,E-mail:lpxy.841019@163.com; 通讯作者:张合(1957-),男,教授,博士生导师,主要研究方向:引信智能与灵巧化技术,E-mail:hezhangz@mail.njust.edu.cn。
更新日期/Last Update: 2013-10-31