基于FLUENT的双翼末敏弹气动特性研究

Aerodynamic characteristics of two wings terminalsensitive projectile based on FLUENT

为研究双翼末敏弹气动特性,基于计算流体力学方法,对S-C形尾翼组合的末敏弹气动外形流场进行计算。获得了末敏弹气动外形表面压力分布规律,以及阻力系数、升力系数、转动力矩系数和压力中心系数随迎角的变化规律。通过模型自由飞行试验获得了末敏弹动态阻力系数和转动力矩系数,结合末敏弹飞行姿态变化分析了双翼末敏弹动态气动特性。结果表明双翼末敏弹增阻效果明显,能够提供平衡弹体自身重量的阻力,达到减速要求。S-C形尾翼组合结构能够为末敏弹提供转动力矩,使末敏弹产生具有稳态扫描形式的运动。研究结果可以为改进末敏弹稳态扫描平台设计提供参考。

To research the aerodynamic characteristics of terminal-sensitive projectiles （TSP）, the flow field of aerodynamic shape of S-C wings terminal-sensitive projectile has been calculated based on compu- tational fluid dynamics methods（CFD）. Analysis is made on surface pressure distribution of TSP aerody- namic shape and the curve of drag coefficient, lift coefficient, rolling moment coefficient and pressure center coefficient variation of the angle of attack and on the dynamic aerodynamics characteristics of two wings TSP with the dynamic drag coefficient and rolling moment coefficient got from free flight test. Re- sults show that the wings have produced efficient drag to keep balance with TSP gravity. The TSP forms a scanning motion by aerodynamics produced by the S-C shape wings. Research results can be improved a- bout terminal-sensitive projectiles stable scanning platform designed to provide references.