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In the present study, the mathematical prediction with the Paul‐Mukunda model is carried out for maximum pressure rise with erosive burning in multi‐grain solid rocket propellant. For this study, a cluster of 7 tubular solid double‐base propellant grains is selected. The erosive burning model has given a fair idea of the maximum pressure rise in rocket motors. The maximum pressure rise due to the erosive burning effect is quite a lot higher than without the erosive burning effect. The erosive burning model helps in studying maximum pressure rise for various configurations of propellant grains. It is found that lowering the outer diameter (OD) of propellant grains is giving low maximum pressure in rocket motor in comparison to increasing the inner diameter (ID) of propellant grains. Ap/At (port area to throat area) ratio is maintained same for both the cases. Although in both the cases predicted maximum flow velocity of propellant gases is almost same. It shows that keeping the same Ap/At ratio and erosive burning effect, the maximum pressure is reduced significantly by lowering OD of propellant grains than increasing the ID of the propellant grains in rocket motor. This study will help to reduce the maximum pressure rise in rocket motors for safe working.

Thermal insulation inside the rocket motor experience severe pressure and temperature conditions. Experimental determination of heat fl ux imparted to thermal insulator inside the rocket motor during the static fi ring is a challenging task. This paper reports experimental determination of heat fl ux for double base propellant (DBP) in small rocket motor. It includes development of experimental rocket motor, adaptation of water-cooled heat fl ux sensor on rocket motor, required instrumentation for heat fl ux time recording and analysis of data. Data are recorded in real time for double base propellant combustion up to the pressure level ~3.6 MPa. Average heat fl ux imparted to the rocket motor casing is found in the range of 230-300 × 10 4 W/m 2 . Heat fl ux inside the rocket motor varies nearly linear with pressure. A correlation between the heat fl ux and pressure is also established for measured pressure range.

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