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.