摘要
采用数值计算方法对发射动力系统主装药随环境温度的变化规律进行了研究,分析了接触热阻和自然对流对计算模型的影响,并与试验结果进行了对比分析。结果表明:当动力系统置于温差20℃的环境中时,经过5h传热,主装药与环境温度相差约9%,而经过10h传热后,主装药与环境温度相差不到0.5%。该研究结论为分析环境温度对发射动力系统内弹道的影响提供了依据。
The research is carded out on the temperature varying laws of main propellant of launch power system by using numerical calculating methods, the effect of contact heat resistance and natural convection on computing model is analyzed, and the comparative analysis is made with test results. It shows that when the launch power system is in the environment of 20℃ temperature difference, the temperature difference between main charge and environment is about 9% after 5 hours heat transfer, while after 10 hours heat transfer, the temperature difference isn＇t reach up to 0.5%.The research conclusion provides dependence for the analysis of the environmental ternperatttre effecting on the inner trajectory of launch power system.
出处
《火工品》
CAS
CSCD
北大核心
2008年第3期1-3,共3页
Initiators & Pyrotechnics
关键词
燃气发生器
瞬态传热
接触热阻
内弹道
Gas generator
Instantaneous heatconduction
Heat resistance
Interior ballistic
