摘要
为了提高线膛发射武器的射击精度,研究复杂激波系对旋转稳定弹丸气动特性的影响。通过划分局部加密的网格,采用k-epsilon双方程湍流模型求解可压缩的三维Navier-Stokes方程,数值模拟和分析旋转弹丸在复杂激波影响下的气动特性变化规律。数值模拟的结果与SOCBT(Secant ogive cylinder boat tail)弹丸风洞实验数据相吻合,验证了计算模型与方法的合理性和可靠性。数值分析旋转速度、攻角、来流马赫数等对弹丸气动特性的影响,通过耦合内弹道过程,数值模拟和分析不同旋转速度对内弹道后效期内弹丸速度增的影响规律。
In order to enhance the shot accuracy of the rifled structure gun system, aerodynamic char- acteristics of the spinning projectile are investigated while the projectile flying over the complex shock waves. The projectile aerodynamic characteristics change laws are simulated by solving three- dimensional Navier-Stokes equations applying k-epsilon turbulence model with local refinement of unstructured grids. Numerical results of SOCBT (Seeant-ogive-cylinder-boat-tail)projectile are in good agreement with experimental results, so the used computational model and CFD method are effective and relative. Aerodynamic characteristic variation laws are simulated and analyzed due to different parameters, including attack angle, projectile rotating speed and incoming Mach number. Coupled with the interior ballistic process, the projectile velocity variations in different rotating speeds are simulated and analyzed while the projectile flying over the muzzle flow field.
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2012年第4期624-628,共5页
Journal of Nanjing University of Science and Technology
基金
国家自然科学基金(BK2007531)
关键词
旋转弹丸
空气动力特性
三维数值模拟
膛口流场
spinning projectiles
aerodynamic characteristics
three dimensional numericalsimulation
muzzle flow field