针对采用固相装药的纯燃气式弹射装置研究高压室内弹道设计过程中装药增面比参数对导弹出筒运动特性的影响,分析了5种不同装药结构的增面比表达式,通过方程组和软件数值仿真求解了高压室、低压室压强及导弹出筒速度、加速度,根据计算结果进行对比并得出结论:增面燃烧装药可以显著降低导弹出筒的峰值加速度;半球形装药可在三维方向上实现更大的增面比;在装药质量相同、出筒行程(筒长)相同的情况下,与管状增面燃烧装药结构相比,半球形装药结构可使导弹出筒运动性能得到明显提升。

This article focuses on the study of the influence of the solid propellant burning surface augmentation ratio parameter on the missile exit motion characteristics during the high-pressure indoor ballistic design process of a pure gas type ejection device using solid propellant. The expression of the burning surface augmentation ratio for five different solid propellant structures is analyzed. The pressure in the high-pressure and low-pressure chambers, as well as the missile exit velocity and acceleration, are solved through equation sets and software numerical simulation, and based on the comparison of the calculation results, it can be concluded that: The increased surface combustion solid propellant structure can significantly reduce the peak acceleration of the missile’s exit from the barrel; A hemispherical charge can achieve a greater burning surface augmentation ratio in the three-dimensional direction; Compared with the tube shaped increased surface combustion solid propellant structure, the hemispherical solid propellant structure can significantly improve the missile’s exit motion performance when the solid propellant quality is the same and the exit stroke (cylinder length) is the same.