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对少烟 HTPB/ AP/ RDX/ Al推进剂能量性能进行了理论计算 ,通过 BSFФ 16 5和Ф315试验发动机试验 ,考察了试验发动机类型、工作压力对比冲效率的影响 ,而且与高铝含量 HTPB/ AP/ RDX/ Al推进剂的比冲效率进行了比较。结果表明 :铝含量对推进剂的比冲效率有显著的影响 ,低铝配方的比冲效率比高铝配方的比冲效率相对要高些 ;对于推进剂组分确定的配方 ,合适选择发动机的工作压力 ,可以不同程度地提高比冲效率 ;对于同一类型推进剂配方 ,通过计算理论比冲 ,结合比冲效率水平 ,可以对实际比冲进行有效的预估。
The energy performance of the less smoke HTPB / AP / RDX / Al propellant was theoretically calculated. The engine tests of BSFФ165 and Ф315 were carried out to investigate the influence of engine type and working pressure on the efficiency of the test. Moreover, The specific impulse efficiencies of AP / RDX / Al propellants were compared. The results show that the aluminum content has a significant impact on the specific impulse efficiency of the propellant, and the specific impulse efficiency of the low aluminum formulation is relatively higher than the specific impulse efficiency of the high aluminum formulation. For the formula of the propellant component, the choice of the engine Working pressure can improve the specific impulse efficiency to a certain extent; for the same type of propellant formulation, the actual impulse can be effectively estimated by calculating the theoretical impulse and combining the specific impulse efficiency level.