摘要
在自由基裂解模型和引入高氯酸铵(AP)和铝粉(Al)影响因子的基础上,讨论了催化剂对AP/Al/端羟基聚丁二烯(HTPB)推进剂热分解的影响,采用假说和因子归纳的方法得到了催化影响因子,结合一定数量燃速数据分析和计算机图形学拟合的方法建立了AP/Al/HTPB推进剂催化燃烧模型,该模型可从推进剂化学结构参数出发,定量计算AP/Al/HTPB推进剂的燃速和压强指数。计算结果表明:在一定条件范围内,燃速的理论预测与实验结果吻合较好,误差一般在7%以内,验证了催化燃烧模型在AP/Al/HTPB推进剂应用的可行性,对推进剂配方研制具有一定的指导意义。
The effects of the catalysts on the thermal decomposition of AP/Al/HTPB（hydroxyl-terminated polybutadiene） propellant were discussed based on the model of free-radical cracking and the impact factors of ammonium perchlorate（AP） and powered aluminum（Al）.The catalytic impact factor was regulated using a hypothesis and the factor inductive method.A computer graphics fitting method was used to establish a catalytic combustion model of AP/Al/HTPB propellant by analyzing a large number of burning rate data.The model could calculate quantitatively the burning rate and pressure index of AP/Al/HTPB propellant when the chemical structure parameters of solid propellant were given.The calculated results show that the theoretically predicted values are in agreement with the experimental results within given conditions,the error is less than 7 percent.The feasibility of the catalytic combustion model for AP/Al/HTPB propellant was verified,which provides a certain guide for the development of propellant formula.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2010年第10期1327-1332,共6页
Acta Armamentarii
关键词
热学
端羟基聚丁二烯
固体推进剂
燃烧模型
催化
thermology
hydroxyl-terminated polybutadiene
solid propellant
combustion model
catalysis
