Optimization and performance evaluation of environmentally friendly rocket composite propellant
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Date
2018
Journal Title
Journal ISSN
Volume Title
Publisher
Taylor and Francis
Abstract
This 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.
Description
Keywords
Design, environment, factors, propellant, optimisation