关键词: 固体火箭发动机;比冲;推进剂试验

Abstract: The vacuum specific impulse efficiencies for SRM-1,SRM-2 and SRM-3 are predicted separately in the paper.The predicted values of specific impulse efficiencies are coordinated with the measured ones well and the their relative deviations are not more than 0.3% .Simultaneously,un-simulated three principal parameters (L,d1, tb) for the small-scale motor were found by analysing of the simulated parameters in the mathematical modle of vacuum specific impulse.As a result,the alternated method for predicting the vacuum specific impulse efficiencies of the small-scale motor was implemented.On the basis of this,the proposal to use the full-scale motor with the simulated small-scale motor for the high-altitude simulation test is presented.

Key words: Solid rocket engine;Specific impulse;Propellant test