为了研究两级分离布局导弹分离过程的气动特性,文中利用自主开发的数值计算程序对导弹两级分离过程进行了模拟,并完成了部分工况的风洞实验验证,分析了分离过程导弹两级气动特性的变化规律。研究范围:马赫数2.0~5.0,攻角0°~6°。结果表明:攻角和侧滑角对导弹两级的轴向位移影响较小,马赫数越高、I级模型头部锥角越小或导弹两级直径比越接近均有利于导弹两级的快速分离。

In order to research aerodynamic characteristic of missile during stage separation, in this paper, missiles' separation process was simulated by a numerical calculation program which was exploited independently, and partial tests were finished in the wind tunnel, the trend of the missiles' aerodynamic characteristic in the process was analyzed. The research range of the Mach number is 2.0 to 5.0 and the angle of attack is 0° to 6°. The results show that the angle of attack and the angle of sideslip have less affection on missiles' axial displacement, the bigger is Mach number, the smaller is cone angle of grade I and the ratio of grades' diameter is close to 1.0 are benefit for missiles' fast separation.