The computational fluid dynamics of hybrid rocket internal ballistics is becoming a key tool for reducing the engine operation uncertainties and development cost as well as for improving experimental data analysis. Nevertheless, its application still presents numerous challenges for the complexity of modeling the phenomena involved in the fuel consumption mechanism and its coupling with the chemically reacting flowfield. This paper presents a review of the computational thermo-fluid-dynamic models developed for the internal ballistics of hybrid rockets burning gaseous oxygen with classical polymeric or paraffin-based fuels, with a special focus on the interaction between the fluid and the solid fuel surface. With the purpose of predicting the local fuel regression rate, which is the main parameter needed for the hybrid rocket design, the model is coupled with an improved gas/surface interface treatment based on local mass, energy and mean mixture-fraction balances, combined to either a pyrolysis-rate equation in the case of classical polymers, or to an additional equation for the liquid paraffin entrainment fraction of the total fuel consumption rate. A number of experimental test cases obtained from the static firing of two different laboratory-scale rockets are simulated to determine the models' capabilities, showing very good agreement between the calculated and measured fuel regression rates with both standard pyrolyzing and liquefying fuels. The prediction of the chamber pressure measured with paraffin fuel resulted in it being more cumbersome for the single-phase flow assumption. The advantages and limitations of the models are discussed.

The application of computational thermo-fluid-dynamics to the simulation of hybrid rocket internal ballistics with classical or liquefying fuels: A review / Di Martino, G. D.; Carmicino, Carmine; Mungiguerra, Stefano.; Savino, R.. - In: AEROSPACE. - ISSN 2226-4310. - 6:5(2019), p. 56. [10.3390/AEROSPACE6050056]

The application of computational thermo-fluid-dynamics to the simulation of hybrid rocket internal ballistics with classical or liquefying fuels: A review

Di Martino G. D.;Carmicino;Mungiguerra Stefano.;Savino R.
2019

Abstract

The computational fluid dynamics of hybrid rocket internal ballistics is becoming a key tool for reducing the engine operation uncertainties and development cost as well as for improving experimental data analysis. Nevertheless, its application still presents numerous challenges for the complexity of modeling the phenomena involved in the fuel consumption mechanism and its coupling with the chemically reacting flowfield. This paper presents a review of the computational thermo-fluid-dynamic models developed for the internal ballistics of hybrid rockets burning gaseous oxygen with classical polymeric or paraffin-based fuels, with a special focus on the interaction between the fluid and the solid fuel surface. With the purpose of predicting the local fuel regression rate, which is the main parameter needed for the hybrid rocket design, the model is coupled with an improved gas/surface interface treatment based on local mass, energy and mean mixture-fraction balances, combined to either a pyrolysis-rate equation in the case of classical polymers, or to an additional equation for the liquid paraffin entrainment fraction of the total fuel consumption rate. A number of experimental test cases obtained from the static firing of two different laboratory-scale rockets are simulated to determine the models' capabilities, showing very good agreement between the calculated and measured fuel regression rates with both standard pyrolyzing and liquefying fuels. The prediction of the chamber pressure measured with paraffin fuel resulted in it being more cumbersome for the single-phase flow assumption. The advantages and limitations of the models are discussed.
2019
The application of computational thermo-fluid-dynamics to the simulation of hybrid rocket internal ballistics with classical or liquefying fuels: A review / Di Martino, G. D.; Carmicino, Carmine; Mungiguerra, Stefano.; Savino, R.. - In: AEROSPACE. - ISSN 2226-4310. - 6:5(2019), p. 56. [10.3390/AEROSPACE6050056]
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11588/779716
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