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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。
In order to improve long-term storage and high combustibility of ammonium perchlorate (AP) powder propellants, AP powders were coated and agglomerated to improve their surface properties by pretreatment. The Gibbs free energy method was used to calculate the energy characteristics of Al / AP powder rocket engine. Pretreatment experiments were used to analyze the effect of HTPB on the packing density, hygroscopicity and thermal decomposition properties of AP powder. The closed-burner ignition experiment was carried out to study the influence of oxygen-fuel ratio and loading on the energy characteristics of Al / AP powder propellants. The results showed that the best pretreatment material ratio of AP was adding 10% HTPB, and the theoretical specific impulse of Al / AP powder rocket engine reached 262.1s at the oxy-fuel ratio of 3:1. With the increase of oxygen Fuel ratio, the energy characteristics of the powder propellants have increased; under the same oxygen-fuel ratio, the unit mass of powder propellants into the gas is basically the same, with the increase of powder loading, the combustion temperature and the characteristic velocity are increased.