为了探究不同尾翼末敏弹的气动特性,设计了带有副翼结构的无伞末敏弹模型,借助计算流体力学建立了无伞末敏弹的气动力仿真模型。数值计算结果表明不同尾翼结构对末敏弹的稳态落角和阻力系数有较大影响。当翼展从150mm增至250mm时,末敏弹的稳态落角从43°减至16°,阻力系数从0.78增至1.61。当副翼斜置角从0°增至60°时,稳态落角、导转力矩系数和阻力系数也在发生变化。这将为无伞末敏弹的设计提供有益参考。

To study aerodynamic characteristics of terminal sensitive projectile (TSP) with different wings, non-fin TSP with aileron was designed. The simulation models of non-fin TSP were established by using computational fluid dynamics. The results show that TSP has different stable angles and drag coefficients when having different wings. When the span increases to 250 mm from 150 mm, the stable angle decreases to 16° from 43°, the drag coefficient increases to 1.61 from 0.78. The stable angle, torque coefficient and drag coefficient are different when the aileron oblique angle increases to 60° from 0°. This paper can provide helpful references for design of non-fin TSP.