Combustion modeling of solid propellant base on ammonium perchlorate and polybutadiene in a hypothetical rocket engine


Аuthors

Shaydullin R. A.*, Sabirzyanov A. N.**

Kazan National Research Technical University named after A.N. Tupolev, Kazan, Russia

*e-mail: samsankimanki@bk.ru
**e-mail: ansabirzyanov@kai.ru

Abstract

The article presents a brief review of models for the numerical simulation of solid fuel combustion processes. The options of the combustion process description of ammonium perchlorate and polybutadiene with hydroxyl end groups with application of ideal mixing reactor and at numerical modeling in the combustion chamber of the rocket engine with joint solution of the gas dynamics equations are thrashed out. The article presents the results of the numerical analysis of mixed solid fuels combustion as a part of a hypothetical engine. A supposition for numerical modeling of the mixed solid rocket fuel combustion in the axisymmetric setting was substantiated. The Damkeler number distribution in the combustion chamber volume was demonstrated.

Keywords:

solid rocket propellant, combustion of a mixed metal-free solid rocket propellant, combustion modeling in a rocket engine, chemical kinetics

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