基于AP预处理技术的粉末推进剂性能

为了提高高氯酸铵(AP)粉末推进剂的长期贮存性和高效燃烧性,利用预处理技术对AP粉末进行包覆团聚,改善其表面特性。采用吉布斯最小自由能法计算Al/AP粉末火箭发动机的能量特性,利用预处理实验分析端羟基聚丁二烯(HTPB)对AP粉末的装填密度、吸湿性能和热分解特性的影响,并进行密闭燃烧器点火实验,研究氧燃比和装填量对Al/AP粉末推进剂能量特性参数的影响规律。结果表明:AP的最佳预处理材料配比为添加10%HTPB,且在氧燃比为3∶1时,Al/AP粉末火箭发动机的理论比冲最高达262.1s;一定范围内,随着氧燃比的增加,粉末推进剂的能量特性参数均有所增加;在氧燃比相同条件下,单位质量粉末推进剂成气量基本相同,随着粉末装填量的增加,燃温和特征速度均有所提高。

Performance of Powder Propellant Based on AP Pretreatment Technology

The ammonium perchlorate (AP) powder was coated and agglomerated to improve the powder propellant surface properties,which provided the conditions for Al/AP propellant long-term storage and high efficiency combustion.The energy characteristics of Al/AP powder rocket motor were calculated by Gibbs minimum free energy method,and the effects of the hydroxylterminated polybutadiene(HTPB) to AP powder on the loading density,hygroscopicity,and thermal decomposition were analyzed by pretreatment experiments.The ignition tests were conducted in the closed burner to study the effect laws of O/F and packing quality to the energy characteristic parameters of Al/AP powder propellant.The results show that,the optimal material ratio of AP pretreatment is 10％ HTPB,and in this circumstance,the theoretical specific impulse of Al/AP powder rocket engine can be up to a maximum of 262.1 s at 3 ∶ 1 of O/F.The energy characteristic parameters of powder propellant will increase with the growth of O/F in a certain rage;the gas generating quality of powder propellant per unit mass is basically equal at the same O/F,and both combustion temperature and velocity characteristics will increase with the growth of packing quality.