FAST NUMERICAL CODE FOR PREDICTING PROPELLANTS PERFORMANCE

Abstract

The propulsive performance of several O-C-H propellants for space propulsion application is investigated through computational prediction and experimental proof, with focus on the effects of chemical equilibrium in water-gas reaction. The correct prediction of the propulsive efficiency of chemical propellants for space propulsion application is the key component of space launchers design and manufacturing. Previous observations of some deviations of this global reaction between the combustion products from chemical equilibrium at elevated temperatures suggest that this chemical equilibrium could have a visible impact on the propulsive efficiency of the propellants. A general computational method was developed and used to reveal possible deviations from the chemical equilibrium and the effect this could have over the specific impulse of rocket engines, powered by chemical propellants. The contribution is the proprietary numerical code that offers a reliable means of such prediction with a minimum amount of computer processing. Results are presented for a series of chemical propellants of immediate interest for the NERVA orbital launcher, developed under the CNMP contract 82076.