摘要
为了分析脉冲末修弹的气动特性,建立了末修弹横向喷流工作前后的非定常数值计算模型,计算了脉冲横流在不同作用位置时末修弹的阻力系数、升力系数和俯仰力矩系数,揭示了脉冲横流对末修弹气动特性影响随其作用位置和弹体马赫数的变化规律。结果表明:脉冲横流对弹体阻力的影响不大,对升力和俯仰力矩影响明显。末修弹产生的附加升力系数随脉冲发动机喷口位置后移而增大,且当马赫数在0.6～1.1范围时,该系数随着马赫数增加而影响减小;气动焦点位置随着喷口位置后移亦向后移动,且随着马赫数增加而移动速度减慢。
To analyze impulse cross-flow, t coefficient, lift coeffi aerodynamic characteristics for terminal correction projectile （TCP） with he unsteady aerodynamic model of TCP was established, and then the drag cient and pitching moment coefficient were calculated when impulse cross- flow acted on different position of TCP. The effect law on aerodynamic characteristics of TCP was revealed,while impulse cross-flow acting on different position of the projectile at different mach number. The results show that impulse cross-flow has little effect on drag of the projectile and has significant effect on lift and pitching moment. The extra lift coefficient caused by impulse cross-flow, increases with the position of the impulse cross-flow moving backwards, and gradually decreases with the increase of Ma at Ma = 0. 6 - 1. 1. The position of aerodynamic focus point moves backwards while the one of impulse cross-flow moves backwards,and the moving velocity of aerodynamic focus point slows down with the increase of Ma.
出处
《弹道学报》
CSCD
北大核心
2013年第1期27-31,共5页
Journal of Ballistics
基金
国家自然科学基金项目(11176012)
关键词
气动特性
脉冲横向喷流
末修弹
非定常气动模型
aerodynamic characteristics
impulse cross-flow
terminal correction projectile
unsteady aerodynamic model
