摘要
采用热-化学耦合模型表征热传导和固化动力学反应,利用物理试验测定硝酸酯增塑聚醚(NEPE)推进剂在不同固化度下的热参数和密度,研究了NEPE推进剂药柱在固化过程中温度场和固化度的分布和演变规律。结果表明,因推进剂固化反应的生热速率与外界热量传递速率存在差异,导致固化过程中出现内部温度场和固化度场分布不均匀的现象。固化时间为1~4 d时,药柱中心位置的温度较高(最高57.6℃),外侧较低;固化时间大于等于5 d时,药柱温度场慢慢与环境温度(50℃)趋向于平衡。推进剂固化度-时间曲线近似为“S”型,固化时间小于1 d时和大于4 d时,固化速率缓慢;固化时间2~4 d时,固化速率快。固体发动机的m数对推进剂固化温度和固化速率有一定影响,m数越大,推进剂的最高温度越高,同时温差也越大,温度差会导致推进剂药柱内部固化速率产生差异,造成推进剂达到指定固化度的时间变长。
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.
作者
陈国庆
惠维维
聂嘉良
曹鹏
王健儒
CHEN Guoqing;HUI Weiwei;NIE Jialiang;CAO Peng;WANG Jianru(School of Engineering and Architecture,Northeast Electric Power University,Jilin132012,China;Xi'an Aerospace Chemical Propulsion Co.Ltd.,Xian710025,China;College of Architecture and Civil Engineering,Beijing University of Technology,Beijing100124,China;Academy of Aerospace Solid Propulsion Technology,Xi'an710025,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2024年第4期485-492,共8页
Journal of Solid Rocket Technology
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
NEPE propellant
grain
thermo⁃chemical coupled model
curing kinetics reaction
temperature field
curing degree field
