弹性翼S-C型末敏弹气动特性研究

采用双向流体-固体耦合方法对无伞末敏弹进行气动弹性分析，研究了末敏弹尾翼在气动力作用下的变形规律，并对尾翼变形后的末敏弹系统进行气动特性分析，总结了末敏弹气动参数、尾翼挠曲变形随运动攻角的变化规律。研究结果表明，末敏弹的阻力系数和转动力矩系数均随着攻角的增大呈先增加、后减小的趋势，升力系数则随着攻角的增大呈单调递增趋势；自由飞行试验结果显示，与刚性翼末敏弹相比，弹性翼末敏弹的气动参数仿真值与试验值更为贴近。

Research on Aerodynamic Characteristics of Terminal Sensitive Projectile with S-C Shaped Elastic Wings

Two-way fluid-structure interaction method is used to study the aeroelasticity of non-parachute terminal sensitive projectile (TSP). The wing deflection law and aerodynamic characteristics of TSP system are studied, and the effect of angle of attack on the aerodynamic parameters and wings’ deflection is analyzed as well. The results show that the drag coefficient and torque coefficient increase first and then decrease with the increase in the angle of attack, and the lift coefficient monotonically increases with the increase in the angle of attack. The free flight tests show that the simulation results of TSP with elastic wings are closer to the experimental results than the simulation results of TSP with rigid wings.