Title :
Two pulse solid propellant rocket motor solution
Author_Institution :
Univ. of Defence, Brno, Czech Republic
Abstract :
The paper deals with mathematic simulation of dynamic processes in two pulse solid propellant rocket motor. The dynamic approach to the solution is formed by the differential equations of the mass and energy conservation laws in gas flow. Pressure and thrust courses are used for demonstration of the solution results.
Keywords :
energy conservation; fuel; propellants; rocket engines; differential equations; dynamic approach; dynamic processes; energy conservation laws; gas flow; mass conservation laws; mathematic simulation; pressure course; thrust course; two-pulse solid propellant rocket motor solution; Combustion; Limiting; Mathematical model; Orifices; Rockets; Solids; divided combustion chamber; gas flow through orifice; two pulse solid propellant rocket motor;
Conference_Titel :
Military Technologies (ICMT), 2015 International Conference on
Conference_Location :
Brno
Print_ISBN :
978-8-0723-1976-3
DOI :
10.1109/MILTECHS.2015.7153747
