Optimisation and performance evaluation of an environmentally friendly rocket composite propellant

Abstract

ABSTRACTThis paper investigated the effects of laboratory synthesised rocket composite propellants’ formulations on propellant performance parameters using response surface methodology (RSM). For the sake of a safe environment, the propellant is made of chemical constituents that have less severe effects on air quality. Experimental measurements of propellant performance parameters were carried out using the ballistic evaluation method. The thrust generated during combustion, the burn time and the propellant combustion temperature were measured using a data acquisition facility equipped with a button load cell and a thermocouple. Specific impulse, density, temperature, characteristic velocity, molecular weight and heat ratio were computed from the measured parameters. The resulting optimum rocket composite propellant formulations were 65.1%, 18.1%, 9.1%, 3.6%, 2.2% and 1.9% for the oxidiser, binder, fuel, opacifier, burning rate enhancer and catalysts, respectively. The corresponding performance indices including specific impulse, propellant density, propellant temperature, propellant characteristic velocity, molecular weight and heat ratio were 122.03 s, 1697.08 kg m−3, 2025.07 K, 987.65 m s−1, 31.50 kg mol−1 and 1.02, respectively. Findings revealed the accuracy and the adequacy of RSM in analysing and optimising the effects of composite rocket propellant formulation on its performance parameters and also a step towards producing an environmentally friendly rocket composite propellant.