DocumentCode
3091264
Title
Two pulse solid propellant rocket motor solution
Author
Konecny, Pavel
Author_Institution
Univ. of Defence, Brno, Czech Republic
fYear
2015
fDate
19-21 May 2015
Firstpage
1
Lastpage
5
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;
fLanguage
English
Publisher
ieee
Conference_Titel
Military Technologies (ICMT), 2015 International Conference on
Conference_Location
Brno
Print_ISBN
978-8-0723-1976-3
Type
conf
DOI
10.1109/MILTECHS.2015.7153747
Filename
7153747
Link To Document