Influencing factors of submunition separation parameters in gas-airbag separation device

燃气囊式分离装置中子弹分离参数的影响因素

¹ School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
² Xi'an Modern Chemistry Research Institute, Xi'an 710065, China

Received: 1 August 2024

Abstract

In order to explore the influence factors of submunition separation parameters on a gas-airbag separation device, its model was established using the solid propellant as fuel and the gas generator as power device. Based on the classical interior ballistic equations of ejection, the gas mass flow rate, the initial volume of the low-pressure chamber and the charge type were calculated and analyzed through combining theory with simulation. The accuracy of the model was verified through separation simulation and experiment. The results show that the increases of the burning area and burning speed increase with increasing gas mass flow rate, which results in the increases of both peak submunition acceleration and gas working efficiency and the decrease of separation time. On the other hand, the increase of the initial volume of the separation device results in the decrease of peak submunition acceleration, the increase of separation time and the decrease of gas working efficiency. The submunition velocity at the end of separation demonstrates the positive linear relationship with the gas mass flow rate, while the peak submunition acceleration exhibits the positive linear correlation with the mass-to-volume ratio of the separation device. The acceleration peak value of the increase area charge is smaller than that of the constant area charge and slower than the filling of the airbag, more satisfactorily satisfying the requirements for the low overload. The experimental results show that the error between the separation acceleration and the theoretical value is 10.35% and that the error between separation velocity and theoretical value is 6.67%. The theoretical model has good accuracy. This study provides a reference for the design of other gas-airbag separation devices with solid propellant as energy source.

摘要

为探究燃气囊式分离装置中子弹分离参数的影响因素, 建立了以固体推进剂为燃料, 燃气发生器为动力装置的燃气囊式分离装置模型。以经典弹射内弹道方程组作为理论基础, 通过理论与仿真相结合的方式对燃气流量、低压室初容以及装药药型进行了分析计算, 并通过分离模拟试验验证了计算模型的准确性。结果表明: 装药燃面越大、燃速越高, 燃气质量流量越大, 子弹过载峰值越大, 分离时间越短, 做功效率越高; 装置初容越大, 子弹过载峰值越小, 分离时间越长, 做功效率越低; 子弹分离末速度与燃气质量流量呈线性正相关; 子弹加速度峰值与装置质容比呈线性正相关; 增面型装药比恒面型装药的加速度峰值更小, 对气囊的填充过程更缓和, 作用时间更长, 更能满足低过载要求; 试验测得的子弹分离加速度与理论值误差为10.35%, 分离速度与理论值误差为6.67%, 理论预估模型具有良好的准确性。文中工作能够为以固体推进剂为能量源的燃气囊式分离装置提供设计思路和技术参考。