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为进一步研发新型特种推进剂品种,向推进技术应用领域发展和延伸,开展了NM(硝基甲烷)/RDX/Nano-Al膏体推进剂配方研究,并对其能量、流变以及燃烧性能进行了分析。结果表明:采用最小自由能法估算膏体推进剂配方比冲为2674.2 N·s/kg;膏体推进剂流变行为遵循Herschel-Bulkley本构方程,在0~30℃范围内,假塑性指数n小于1,属于非牛顿假塑性流体,同时膏体推进剂具有明显的触变性以及蠕变-回复特性,在角频率为1Hz且低应力下(≤50Pa),膏体推进剂储能模量(G′)大于损耗模量(G′′),此时具有较稳定的三维网络结构;与含纳米铝热剂Nano-Al/Pb O双基系推进剂相比,膏体推进剂在10~15MPa压强范围内燃速较快,但在低压下未燃。
In order to further research and develop new special propellant varieties and to develop and extend the application fields of propulsion technology, the formulation research of NM (nitromethane) / RDX / Nano-Al paste propellant was carried out, and its energy, rheological and combustion properties Analysis. The results show that the specific impulse of the paste propellant is estimated to be 2674.2 N · s / kg using the minimum free energy method. The rheological behavior of the paste propellant follows the Herschel-Bulkley constitutive equation. Within the range of 0 ~ 30 ℃, the pseudoplasticity index n is less than 1, belong to the non-Newtonian pseudoplastic fluid, while the paste propellant has obvious thixotropy and creep-recovery characteristics. Under the condition of the angular frequency of 1Hz and low stress (≤50Pa), the storage modulus of paste propellant (G ’) is larger than the loss modulus (G "), at this time, it has a more stable three-dimensional network structure. Compared with Nano-Al / PbO bismuth- ~ 15MPa pressure range faster burning rate, but unburned at low pressure.