S-S型旋翼末敏弹气动特性规律研究

无伞末敏弹的稳定尾翼在母弹开舱前包裹于子弹外壁，因威力要求，子弹直径需要尽可能大，导致稳定尾翼的厚度较小，而末敏子弹下落速度较快，尾翼极易在空气动力的作用下发生挠曲变形。为深入分析尾翼结构参数对末敏弹气动特性及尾翼挠曲变形的影响规律，采用双向流体-固体耦合方法对S-S型旋翼末敏弹进行分析。研究结果显示：末敏弹阻力系数随弯折角α₂₁的增大呈递增趋势，而随其余3个弯折角的增大呈递减趋势；转动力矩系数随4个弯折角的增大均呈递增趋势，随4个弯折比的增大均呈现准线性递增趋势，随两翼长宽比的增大呈递减趋势。高塔自由飞行试验结果表明，末敏弹阻力系数和转动力矩系数的仿真误差分别不超过7.8%和6.1%，证明了双向流体-固体耦合方法分析无伞末敏弹气动特性的可行性与正确性。

Research on Aerodynamic Characteristics of Terminal Sensitive Projectile with S-S-shaped Flexible Wings

The stabilizing wings are wrapped on the outer wall of terminal sensitive projectile (TSP). The diameter of TSP is generally large to meet the demand of power, which restricts wing thickness. The falling speed of TSP is so quick that the wings deform under the action of aerodynamic force. The effect of the structure parameters of wings on the aerodynamic characteristics of TSP is studied using fluid-structure interaction (FSI) method. The results show that the drag coefficient (C_d) increases with α₂₁ and decreases with other bending angles. The moment coefficient (C_m) increases with bending angles and bending ratios, C_m decreases with length-width ratio of wing. The free flight test results show that C_d and C_m are in agreement the simulated results well.