Experimental determination of rocket motor internal ballistic coefficients and performance parameters

Abstract

In solid propellant rocket motor internal ballistic calculation, next coefficients, performance parameters and characteristics are required: specific impulse, discharge coefficient, thrust coefficient and propellant burning rate law. All those RM working parameters can be theoretically or semi-empirically predicted, but depends from rocket motor design and combustion products flow losses; theoretical values can be very unreliable. Correction of theoretical working parameters can be provided using experimental data, although this approach is expensive and requires necessary experimental equipment. By using corrected working parameters in internal ballistic calculation highly precise results can be achieved, and accuracy of this approach is demonstrated in two different examples.