H2O2/HTPB固液火箭发动机燃料配方正交优化设计

采用随机轨道法计算了H₂O₂/HTPB固液火箭发动机的喷管两相流,并采用试验结果验证了数值计算的准确性.研究了不同凝相质量分数和粒子平均直径对喷管性能的影响,结果表明:随着凝相质量分数和粒子平均直径的增加,喷管效率逐渐降低.对固体燃料中的Al,Mg,AP和B等组分的质量分数进行了正交试验设计,研究分析了不同燃料组分对喷管两相流和发动机性能的影响,并对固体燃料配方进行了正交优化设计.结果表明:凝相组分质量分数随Al,Mg的质量分数增大而增加,AP和B的质量分数对凝相质量分数影响较小;添加Al,Mg,AP和B等物质对发动机的最佳理论比冲影响不大,但可以有效提高最佳理论密度比冲;添加Al和Mg等金属颗粒会增加喷管损失,降低实际比冲和实际密度比冲,添加AP和B对比冲效率影响不大. 

Orthogonal optimal design of solid fuel formulation for H2O2/HTPB hybrid rocket motor

Nozzle two-phase flow in H₂O₂/HTPB hybrid rocket motor was numerically simulated by the stochastic trajectory model.Accuracy of the simulation results was verified by comparison with experimental data.A parametric study of different condensed phase mass fractions and particle mean diameters was performed to investigate the influence of condensed phase parameters on nozzle performance,and the results show that the nozzle efficiency decreases with the increasing of condensed phase mass fraction and particle mean diameter.An orthogonal design of fuel formulation was conducted to investigate the effect of different fuel additives(Al,Mg,AP and B) on the motor performance,and an optimal formulation was obtained.The results indicate that the condensed phase mass fraction increases with the increasing of mass fractions of Al and Mg,and is low dependent on the mass fractions of AP and B;the addition of Al,Mg,AP and B has little effect on the maximum specific impulse,and can enhance the maximum density specific impulse effectively.Moreover,the addition of Al and Mg reduces the nozzle efficiency,the actual specific impulse and the actual density specific impulse,while the addition of AP and B has little effect on the nozzle performance.