Firing test of solid rocket motor with pintle-technology carried out and the measured pressure-time curve was compared with the values predicted by the internal ballistic and performance analysis.Without baffle, the measured combustion chamber pressure was similar with the predicted pressure at the beginning of combustion, but gradual increase in pressure, which was unexpected with the end-burning grain of which burning area is constant, was observed. A baffle was inserted to make uniform flow over the pintle. Unlike the thruster without baffle, the measured combustion chamber pressure was 1.4 times higher than the predicted value. Through the CFD simulation, 10% of total pressure loss of the flow was observed from combustion chamber to nozzle throat when the baffle was inserted. The measured pressure with baffle was predicted well by considering the total pressure loss in the internal ballistic modelling and performance analysis.
Abstract-In this study, rocket plume behavior at various altitudes and radiative heat transfer to the base surface is investigated by using DSMC and Finite-volume method for radiation. Rapidly expanded plume with increasing altitude cause the low density transient flow region in the plume. And, because of the decrease of plume temperature and density, the radiative heat transfer to the rocket base surface is also decrease.
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