关键词: 火箭发动机喷管;高空仿真;二相流;分离流;数值仿真;性能预测

Abstract: Ground and altitude performances of the LM 2E perigee kick motor (EPKM) altitude nozzle were predicted. The explicit MacCormack difference scheme for gas phase and the characteristic method for particle phase were employed in the nozzle transonic flow region, and in the supersonic flow section the characteristic algorithm was employed, to numerically solve the two dimensional axis symmetrical non viscous two phase flow model. Based on the gas flow separation criterion, the nozzle ground performance was predicted,meanwhile, the nozzle altitude performance was also calculated extrapolatively by using the ground test data. The predicative average thrusts have relative errors of approximate 56% and 15%, respectively, when compared with the measured values. The average thrust from simulating directly the altitude nozzle with full flow status gives a relative error of 17% approximately when compared with the measured value. The current studies show that the employed two phase flow model, gas flow separation criterion and numerical method are effective to predict the performance of the altitude nozzle at different operating statuses in practice.

Key words: Rocket engine nozzle;Altitude simulation;Two phase flow;Separated flow;Numerical simulation;Performance prediction