Experiments on Solid Propellants Combustion: Experimental Apparatus and First Results
In solid propellant rocket combustion optical measurements at a fixed point of the gas phase thermal profile are very important, since they can be used to check the heterogeneous combustion theory briefly described in the first section of this paper.
An apparatus keeping the burning surface of the propellant sample fixed relative to the combustion chamber was realized by means of a stepping motor lifting the cylindrical propellant with a velocity equal to the burning-surface regression rate. The position of the burning surface is sensed by means of a laser system. A series of experimental runs were performed on an AP-based solid propellant at subatmospheric pressure. Under those conditions combustion of the propellant occurs with self-sustained burning oscillations. The signals of the feeding-motor velocity and of the light emitted by the gas phase at a distance of 5 mm from the burning surface were recorded. The system is capable of keeping the burning-surface position fixed, relative to the laboratory, within an error of a few tenths of a millimeter. The results show that the frequency of the burning oscillations and the mean burning rate agree with the data obtained with other experimental methods.
KeywordsCombustion Chamber Burning Rate Step Motor Burning Surface Solid Propellant
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