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针对潜射导弹垂直发射运载器空中热分离问题,建立了轴向弹射分离模型和弹器联合体空中运动数学模型,以内弹道计算为切入点,对内外弹道进行耦合求解。基于燃气节流孔直径不同的3种分离方案,仿真研究了弹器空中分离运动特性,确定了导弹最终运动状态和最佳分离方案。该仿真结果可作为导弹进入气动飞行控制模式初始条件,为潜射导弹全弹道规划提供重要依据。
Aimed at the problem of airborne heat transfer in submarine-launched vertical launching vehicle, a mathematical model of axial ejection separation and air movement of the intermodal unit was set up. The interior ballistic calculation was used as the starting point to solve the internal and external ballistic trajectory. Based on the three kinds of separation schemes with different diameters of gas orifice, the air separation motion characteristics of the missile were simulated and the final movement status and the best separation scheme of the missile were determined. The simulation results can be used as the initial conditions for the missile to enter the aerodynamic flight control mode and provide an important basis for the whole ballistic missile submarine planning.