摘要
利用NASA-CEA2软件,在标准条件下,分别计算了含DAP-4((C6H14N2)[NH4(ClO4)3])的HTPB(端羟基聚丁二烯)推进剂、GAP(聚叠氮缩水甘油醚)推进剂、CMDB(复合改性双基)推进剂和NEPE(硝酸酯增塑聚醚)推进剂的能量性能;重点研究了以DAP-4分别替代RDX(黑索今)、HMX(奥克托今)、CL-20(六硝基六氮杂异伍兹烷)、TKX-50(5,5'-联四唑-1,1'-二氧二羟胺)后推进剂能量的变化趋势;对比了 4种含DAP-4推进剂的能量性能.结果表明,当推进剂配方中添加DAP-4后,其标准比冲(Isp)和特征速度(C*)呈线性趋势增加.特别是当配方中只含DAP-4高能填料时,HTPB、GAP、CMDB、NEPE 推进剂的Isp 分别达到了 2 617.5、2 688.4、2 679.4、2 708.7 N·s/kg,C*分别达到了1 604.1、1 634.7、1 639.1、1 654.7 m/s,高于目前已知固体推进剂的比冲和特征速度.同时给出了推进剂燃烧温度和燃烧产物平均分子量的数据,通过分析这2个参数的变化,部分解释了添加DAP-4后推进剂Isp和C*的变化机制,为DAP-4在固体推进剂中的应用提供参考.
Abstract
Using NASA-CEA2 software,the energetic performance of HTPB(hydroxyl-terminated polybutadiene)propellant,GAP(glycidyl azide polyether)propellant,CMDB(composite modified double base)propellant and NEPE(nitrate ester plasticized polyether)propellant containing DAP-4((C6H14N2)[NH4(ClO4)3])was calculated separately under standard conditions.The energy change trends of the propellants after replacing RDX(hexogen),HMX(octogen),CL-20(hexanitro hexaaza isowurtzitane),TKX-50(5,5'-bitetrazol-1,1'-dihydroxylammonium)with DAP-4 were emphatically investigated.The energetic performance of four types of propellants containing DAP-4 was compared.The results showed that when DAP-4 was added to the propellant formulation,the standard specific impulse(Isp)and characteristic velocity(C*)increased in a linear trend.Especially,when only DAP-4 energetic filler was included in the formulation,the Isp of HTPB,GAP,CMDB and NEPE propellants reached 2 617.5,2 688.4,2 679.4 and 2 708.7 N·s/kg,respectively,and the C*reached 1 604.1,1 634.7,1 639.1 and 1 654.7 m/s,respectively,which were higher than the specific impulses and characteristic velocities of currently known solid propellants.At the same time,the data of propellant combustion temperature and average molecular weight of combustion products were provided.By analyzing the changes of these two parameters,the change mechanism of Isp and C*of the propellants after the addition of DAP-4 was partially explained,which provided a reference for the application of DAP-4 in solid propellants.
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