For the requirements of a missile engine power starting test object

the technique index of the simulation test rid was decided by static pyrotechnic test data. Both the high pressure cold-air blowing test and the real powder hot-air blowing test were accomplished to get the starting characteristics of the simulator rotor. The test results showed that: the relational expression could be fitted by the air flux and rotation speed under different pressures measured in the static pyrotechnic test and high pressure cold-air blowing test. With the relational expression

the possible maximum rotation speed of the gas generator rotor using hot air with specific powder quantity could be forecasted. At last

the maximum rotation speed was obtained in the hot-air blowing test using 0.8kg real powder.Compared with the maximum rotation speed obtained in the cold-air blowing test under reduced pressure

the difference was only 116r/min. This further proved the validity and accuracy of the forecasting method. It will decrease or cancel the blowing tests of the simulator rotor using powder of different quantities and reduce the test safety risk. The experimental research will lay a foundation for the application on real engine.