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

作　　者：谢志平[1] 黄学功[1] 杨建春[1] 

机构地区：[1]南京理工大学机械工程学院,江苏南京210094

出　　处：《南京理工大学学报》2017年第3期344-349,共6页Journal of Nanjing University of Science and Technology

摘　　要：为研究小口径弹丸的二维弹道修正能力,进行了头锥三自由度偏转时弹丸整体的气动特性分析。建立弹丸的弹轴坐标系和弹头坐标系,确定2个坐标系的相对欧拉角为偏角和转角。通过控制不同的偏角和转角,运用计算流体力学软件Fluent仿真分析弹丸头锥在不同空间位置的气动特性。在5°攻角和弹丸头锥的不同偏转情况下,采用数据拟合方法得到弹丸的俯仰力矩系数、偏航力矩系数随弹丸头锥偏角和转角变化的数学模型。仿真结果表明,在头锥不偏转的情况下弹丸具有较好的稳定性,静稳定储备量为13.54%。Aerodynamic characteristics of a small-caliber projectile are analyzed to study the two di-mensional 2D ）trajectory correction capability of it when its nosecone deflects with 3-degree-of- freedom（3-D0F） . 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 小口後弹丸 二维弹道修正 数据拟合方法 

分 类 号：TJ011.2[兵器科学与技术—兵器发射理论与技术]