为评价新型高氮化合物3，5‐二硝氨基‐1，2，4‐三唑肼盐（HDNAT ）作为固体推进剂组分的应用潜力，采用NASA‐CEA软件，在标准条件下（pc ∶ p0＝70∶1），计算了含 HDNAT的丁羟推进剂（HTPB）、聚叠氮缩水甘油醚（GAP）推进剂和改性双基推进剂（CMDB）的能量特性。绘制了HTPB／Al／AP／HDNAT推进剂（金属Al的最大质量分数为20％）的标准理论比冲 Isp 、特征速度 C倡、燃烧温度 Tc 、燃气平均相对分子质量 Mw 的等性能三角图。结果表明，HDNAT单元推进剂的比冲为2533．0 N · s／kg ；在HTPB推进剂中，当HDNAT质量分数为50％时，Isp最大为2658．0N · s／kg ，较基础配方提高了326．6N · s／kg ；在GAP推进剂中，当HDNAT质量分数为30％时，Isp最大为2529．0N · s／kg ，较基础配方提高了252．7N · s／kg ；在CMDB推进剂中，当HDNAT质量分数为27％时，Isp最大为2593．1 N · s／kg ，较基础配方提高了57．3 N · s／kg。%To evaluate the application prospect of novel nitrogen‐rich compound hydrazinium 3 ,5‐diamino‐1 ,2 ,4‐triazole (HDNAT ) as composite solid propellant components ,the energy characteristics of hydroxy terminated polybutadiene (HT‐PB) propellant ,glycidyl azide polymer (GAP) propellant and composite modified double‐base(CMDB) propellant containing HDNAT were calculated by NASA‐CEA software under the standard condition (pc ∶ p0 =70∶1) .The iso‐property trigo‐nal figures of standard theory specific impulse Isp ,characteristic velocity C* ,combustion temperature Tc and average rela‐tive molecular weight of combustion gas Mw for HTPB/Al/AP/HDNAT propellant(the largest mass fraction of Al is 20% ) were drawn out .The results show that the Isp of HDNAT monopropellant is 2533 .0 N · s/kg .When the mass fraction of HDNAT in HTPB propellant is 50% ,the largest Isp is 2658 .0 N · s/kg ,improves by 326 .6 N · s/kg compared with the basic formulation .When the mass fraction of HDNAT in GAP propellant is 30% ,the largest Isp is 2529 .0 N · s/kg ,im‐proves by 252 .7 N · s/kg compared with the basic formulation .When the mass fraction of HDNAT in CMDB propellant is 27% ,the largest Isp is 2593 .1N · s/kg ,improves by 57 .3N · s/kg compared with the basic formulation .
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