高能单元推进剂TKX–50能量特性计算研究

在比较高能量密度化合物奥克托今(HMX)、六硝基六氮杂异伍兹烷(CL–20)和1,1′–二羟基–5,5′–联四唑二羟胺盐(TKX–50)性质的基础上,采用最小自由能法,计算不同压强下3种化合物作为单元推进剂的性能。在标准条件(pc:p a=70︰1)下计算了分别以CL–20和TKX–50替代HMX后所得推进剂配方CL–20–CMDB和TKX–50–CMDB的性能。结果表明,TKX–50具有较高的爆轰性能,在1～10 MPa下TKX–50具有较低的燃温、较高的特征速度和高于HMX的比冲,其燃烧产物平均相对分子质量较低;用于复合改性双基推进剂配方中,不仅提高了比冲,而且有效降低了火箭发动机排气羽流中的二次烟。

Calculation of Energy Characteristics of High Energy Monopropellant TKX-50

Based on comparison of properties of high energy density compounds such as cyclotetramethylene tetranitramine （HMX）, hexanitrohexaazaisowurtzitane （CL-20） and 1,1＇-dihydroxyl-5,5＇-bistetrazole hydroxy- lammonium salt （KTX-50）, the performance of three compounds as monopropellant under different pressures were calculated using minimum free energy method. The performance of propellant formulations CL-20-CMDB and TKX-50-CMDB obtained by replacing HMX with CL-20 and TKX-50 separately were calculated under the standard condition（,pc：pa=70 ： 1）. The results show that TKX-50 possesses higher detonation performance, and under 1～10 MPa, it has lower combustion temperature, higher characteristic velocity and specific impulse higher than HMX, and its combustion products have lower average relative formulations, it can not only increase specific impulse, rocket motor exhaust plume flow. molecular mass. Using TKX-50 in the CMDB propellant but also effectively decrease the secondary smoke in the