无伞末敏弹双S形尾翼弯折角对气动特性影响研究

The dual-wings terminal sensitive projectile bending angle effect on the aerodynamic characteristics

为获得双S形尾翼末敏弹弯折角对气动特性的影响,基于计算流体力学方法对两片尾翼弯折角分别为10°、20°和30°的九种组合结构模型气动特性展开研究。获得了模型表面压力分布及阻力系数、升力系数和转动力矩系数随迎角由-30°到30°变化的规律。并通过高塔投放的自由飞行试验进行了动态气动特性研究。双S形尾翼无伞末敏弹流场计算结果显示,随着尾翼弯折角增大,双S形尾翼末敏弹阻力系数减小而转动力矩系数增加。弯折角变化对双S形尾翼末敏弹升力系数影响作用较小。试验结果显示,尾翼弯折角增大时,试验末敏弹弹轴与铅直轴夹角亦增加,即扫描角变大,但随着弯折角继续增加末敏弹的稳定性下降甚至出现翻转失稳而不能实现稳态扫描。通过本文的研究可以为改进末敏弹稳态扫描平台设计提供参考。

The design of terminal sensitive projectile scanning platform requires a better understanding of its aerodynamic characteristics.The dual-wings terminal sensitive projectile has a complex aerodynamic shape construct with small length to diameter ratio cylindrical body installed with two low aspect-ratio wings. There are many influencing factors determining the aerodynamic characteristics.The study focused on the effect of bending angle on aerodynamic characteristics through investigating on different configurations with three different bending angle of 10,20,30degree.From the CFD simulation,pressure distribute characteristic,drag coefficient,lift coefficient and rolling moment coefficient varied with angle of attack were obtained.A free flying experimental investigation focused on the kinetic aerodynamics was developed.Results show that wings provide sufficient drag to balance the terminal sensitive projectile weight so as to keep it at low and stable speed.Bending angle offers better aerodynamic characteristics on the rolling moment coefficient.Moreover,it appears that bending angle have no significant effect on lift coefficient.The model revolved around its own axisand rewolved around the vertical axis in the meantime.As bending angle increasing lead to terminal sensitive projectile model axis angle of inclination increasing significantly refer to vertical axis.