Abstract An attempt was made in this paper to determine the regression rate of a hybrid fuel by using combustion chamber pressure. In this method, the choked flow condition at the nozzle throat of the hybrid rocket was used to obtain the mass of fuel burnt and in turn the regression rate. The algorithm used here is better than those reported in the literature as the results obtained were compared with the results obtained using the weight loss method and was demonstrated to be in good agreement with the results obtained using the weight loss method using the same motor and the same fuel and oxidizer combination. In addition, the O/F ratio obtained was in good agreement with those obtained using the weight loss method. The combustion efficiencies obtained were in good agreement with the average values.
Highlights Regression rate measurement is an issue in hybrid rocket. Combustion chamber pressure was used to obtain the regression rate of the fuel. Chocked flow through the nozzle was used to obtain regression rate. The results obtained from pressure time data and weight loss method were in good agreement.
Measurement of regression rate in hybrid rocket using combustion chamber pressure
Acta Astronautica ; 103 ; 226-234
2014-06-28
9 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Measurement of regression rate in hybrid rocket using combustion chamber pressure
Online Contents | 2014
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NTIS | 1966
|Hybrid rocket combustion regression rate model.
AIAA | 1966
|Hybrid rocket fuel combustion and regression rate study
AIAA | 1992
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