TY - JOUR
T1 - Numerical Study of the AP/Al/HTPB Composite Solid Propellant based Combustion Process in a Small Retro Rocket Motor
AU - Yaacob, Izzat Nazmi Mohd
AU - Singh, Balbir
AU - Mazlan, Norkhairunnisa
AU - Gires, Ezanee
AU - Basri, Adi Azriff
AU - Ismail, Osmera
AU - Salleh, Nor Afizah
AU - Shahedi, Suraya
AU - Ahmad, Kamarul Arifin
N1 - Funding Information:
The authors gratefully acknowledge the contributions of FAAS ENGINEERING AND CONSULTANCY SDN. BHD in providing opportunities to flourish and make engineering and energy related research a reality through the grant no: 6300248. The authors would also like to convey their gratitude to UPM for providing the necessary facilities required for this research work
Funding Information:
The authors gratefully acknowledge the contributions of FAAS ENGINEERING AND CONSULTANCY SDN. BHD in providing opportunities to flourish and make engineering and energy related research a reality through the grant no: 6300248. The authors would also like to convey their gratitude to UPM for providing the necessary facilities required for this research work.
Publisher Copyright:
© 2022. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences.All Rights Reserved.
PY - 2022
Y1 - 2022
N2 - A numerical investigation of the composite solid propellant-based Combustion Process is performed to characterize the combustion behavior of ammonium perchlorate and Hydroxyl-terminated polybutadiene (HTPB) propellants in a small retro rocket motor. In this analysis, the combustion process is carried out inside the chamber with 71% oxidizer, 15% aluminum, and 14% binder. The effects of using 15% aluminum, particularly focusing on the substantially increased burning rate and composition and sizes of combustion residues are studied. A small solid-propellant-based retro rocket motor with a C-D Nozzle is studied computationally. Consistency is maintained in the boundary conditions and dimensions of the nozzle. The results clearly show a decrease in the temperature, as there is a drop in pressure along the length of the nozzle. On the other hand, due to the energy conservation, the fluid velocity marks a significant increase along the length of the nozzle. This analysis provides an outline of the combustion for small solid rocket internal flow predictions. The computation results show that the combustor carries sustained combustion throughout the process, with a steep rise in temperature near the nozzle exit. There is also a significant decrease in density near the nozzle exit due to the temperature rise.
AB - A numerical investigation of the composite solid propellant-based Combustion Process is performed to characterize the combustion behavior of ammonium perchlorate and Hydroxyl-terminated polybutadiene (HTPB) propellants in a small retro rocket motor. In this analysis, the combustion process is carried out inside the chamber with 71% oxidizer, 15% aluminum, and 14% binder. The effects of using 15% aluminum, particularly focusing on the substantially increased burning rate and composition and sizes of combustion residues are studied. A small solid-propellant-based retro rocket motor with a C-D Nozzle is studied computationally. Consistency is maintained in the boundary conditions and dimensions of the nozzle. The results clearly show a decrease in the temperature, as there is a drop in pressure along the length of the nozzle. On the other hand, due to the energy conservation, the fluid velocity marks a significant increase along the length of the nozzle. This analysis provides an outline of the combustion for small solid rocket internal flow predictions. The computation results show that the combustor carries sustained combustion throughout the process, with a steep rise in temperature near the nozzle exit. There is also a significant decrease in density near the nozzle exit due to the temperature rise.
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U2 - 10.37934/arfmts.96.2.98114
DO - 10.37934/arfmts.96.2.98114
M3 - Article
AN - SCOPUS:85135272403
SN - 2289-7879
VL - 96
SP - 98
EP - 114
JO - Journal of Advanced Research in Fluid Mechanics and Thermal Sciences
JF - Journal of Advanced Research in Fluid Mechanics and Thermal Sciences
IS - 2
ER -
