南京理工大学学报（自然科学版）2017，Vol.41Issue(3)：344-349,6.DOI:10.14177/j.cnki.32-1397n.2017.41.03.011
小口径弹丸头锥三自由度偏转气动特性分析
Aerodynamic characteristic analysis of small-caliber projectile with 3-DOF deflection nosecone
谢志平 1黄学功 1杨建春1
作者信息
- 1. 南京理工大学 机械工程学院,江苏 南京 210094
- 折叠
摘要
Abstract
Aerodynamic characteristics of a small-caliber projectile are analyzed to study the two dimensional(2D) trajectory correction capability of it when its nosecone deflects with 3-degree-of-freedom(3-DOF).An elastic coordinate system and a nosecone coordinate system of the projectile are established,and the relative Euler angles of the two coordinate systems are the deflection angle and the rotation angle.The aerodynamic characteristics of the projectile nosecone in different space positions are analyzed using computational fluid dynamics(CFD) software Fluent by controlling different deflection angles and rotation angles.A mathematical model of the pitching moment coefficient and the yaw moment coefficient varying with the deflection angle and the rotation angle of the projectile nosecone is obtained using data fitting method under 5 degrees of attack angle and different deflection of the nosecone.The simulation results show that the whole projectile has good stability under the condition of no-deflection of the nosecone,and the static stability reserve is 13.54%.关键词
头锥/三自由度/小口径弹丸/二维弹道修正/数据拟合方法Key words
nosecones/3-degree-of-freedom/small caliber projectiles/two dimensional trajectory correction/data fitting method分类
军事科技引用本文复制引用
谢志平,黄学功,杨建春..小口径弹丸头锥三自由度偏转气动特性分析[J].南京理工大学学报（自然科学版）,2017,41(3):344-349,6.
