固体火箭技术2024，Vol.47Issue(4)：485-492,8.DOI:10.7673/j.issn.1006-2793.2024.04.007
考虑热-化学耦合的NEPE推进剂固化过程数值模拟
Numerical simulation on curing process of NEPE propellant considering thermo-chemical coupling
陈国庆 1惠维维 2聂嘉良 3曹鹏 3王健儒4
作者信息
- 1. 东北电力大学 建筑工程学院,吉林 132012
- 2. 西安航天化学动力有限公司,西安 710025
- 3. 北京工业大学 城市建设学部,北京 100124
- 4. 航天动力技术研究院,西安 710025
- 折叠
摘要
Abstract
The thermal chemical coupling model was used to characterize the thermal conductivity and curing kinetic reaction,and the thermal parameters and density of nitrate plasticized polyether(NEPE)propellant were measured by physical tests.The dis-tribution and evolution of temperature field and curing degree of NEPE propellant during curing were studied.The results show that due to the difference between the heat generation rate of propellant curing reaction and the external heat transfer rate,the distribu-tion of internal temperature field and curing degree field is uneven in the curing process.When the curing time is 1～4 days,the temperature at the center is higher(max.57.6℃)and the temperature at the outer side is lower.When the curing time is greater than or equal to 5 days,the temperature slowly tends to be in equilibrium with the ambient temperature(50℃).The curing rate of propellant is slow when the curing time is less than 1 day and more than 4 days;When the curing time is 2～4 days,the curing rate is fast.The m number of solid rocket motor has a certain impact on the temperature and curing rate of propellant in the curing process.The greater the m number,the higher the maximum temperature of propellant,and the greater the temperature difference.The temperature difference will lead to the difference in the internal curing rate of propellant grain,which will cause a delay in the curing of propellant and increase the time it takes to reach the specified curing degree.关键词
NEPE推进剂/药柱/热-化学耦合模型/固化动力学反应/温度场/固化度场Key words
NEPE propellant/grain/thermo-chemical coupled model/curing kinetics reaction/temperature field/curing degree field分类
航空航天引用本文复制引用
陈国庆,惠维维,聂嘉良,曹鹏,王健儒..考虑热-化学耦合的NEPE推进剂固化过程数值模拟[J].固体火箭技术,2024,47(4):485-492,8.
