激波诱导推力矢量喷管不同气体喷注时的性能分析

Aimed at the research status of the shock thrust vector control, which is limited to the mainstream and secondary flow gas as the same gas, the influence of different secondary flow gas molecular mass on thrust vector performance is investigated. First, a turbulence model described by two equations (AUSM+ scheme and k-ω SST) at two-order accuracy was utilized to solve the Favre averaged three-dimensional Navier-Stokes equations, which simulated the complex interference inner flow field of the nozzle, and the vectorial deflection angles and thrust coefficients were calculated under different gas injection angles, injection pressures and nozzle pressure ratios when the secondary flow gas of He, N₂ and CO₂ were selected. The calculation results show that the smaller the mean molecular mass of the secondary flow gas is, the larger the vectorial deflection angle is, the less the thrust loss is. Therefore, the gas with smaller mean molecular mass could be used as the gas source of the secondary flow, or the high temperature gas derived from the combustion chamber could be mixed with the gas with a smaller mean molecular mass.