Numerical Study of the AP/Al/HTPB Composite Solid Propellant based Combustion Process in a Small Retro Rocket Motor

Authors

  • Izzat Najmi Mohd Yaacob Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia, 43400 Serdang, Selangor, Darul Ehsan, Malaysia
  • Balbir Singh Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal Academy of Higher Education, Manipal 576104, Karnataka, India
  • Norkhairunnisa Mazlan Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia, 43400 Serdang, Selangor, Darul Ehsan, Malaysia
  • Ezanee Gires Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia, 43400 Serdang, Selangor, Darul Ehsan, Malaysia
  • Adi Azriff Basri Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia, 43400 Serdang, Selangor, Darul Ehsan, Malaysia
  • Osmera Ismail Science & Technology Research Institute For Defence (STRIDE), Government of Malaysia, 43000 Kajang, Selangor Darul Ehsan, Malaysia
  • Nor Afizah Salleh Science & Technology Research Institute For Defence (STRIDE), Government of Malaysia, 43000 Kajang, Selangor Darul Ehsan, Malaysia
  • Suraya Shahedi Science & Technology Research Institute For Defence (STRIDE), Government of Malaysia, 43000 Kajang, Selangor Darul Ehsan, Malaysia
  • Kamarul Arifin Ahmad Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia, 43400 Serdang, Selangor, Darul Ehsan, Malaysia

DOI:

https://doi.org/10.37934/arfmts.96.2.98114

Keywords:

Solid propellant, composite propellants, combustion, retro small rocket, binder, oxidizer, aluminum, nozzle

Abstract

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. The turbulent kinetic energy also plays a major role here.

Author Biographies

Izzat Najmi Mohd Yaacob, Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia, 43400 Serdang, Selangor, Darul Ehsan, Malaysia

izzatnajmiyaacob@gmail.com

Balbir Singh, Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal Academy of Higher Education, Manipal 576104, Karnataka, India

balbir.s@manipal.edu

Norkhairunnisa Mazlan, Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia, 43400 Serdang, Selangor, Darul Ehsan, Malaysia

norkhairunnisa@upm.edu.my

Ezanee Gires, Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia, 43400 Serdang, Selangor, Darul Ehsan, Malaysia

ezanee@upm.edu.my

Adi Azriff Basri , Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia, 43400 Serdang, Selangor, Darul Ehsan, Malaysia

adiazriff@upm.edu.my

Osmera Ismail, Science & Technology Research Institute For Defence (STRIDE), Government of Malaysia, 43000 Kajang, Selangor Darul Ehsan, Malaysia

osmera.ismail@stride.gov.my

Nor Afizah Salleh, Science & Technology Research Institute For Defence (STRIDE), Government of Malaysia, 43000 Kajang, Selangor Darul Ehsan, Malaysia

norafizah.salleh@stride.gov.my

Suraya Shahedi, Science & Technology Research Institute For Defence (STRIDE), Government of Malaysia, 43000 Kajang, Selangor Darul Ehsan, Malaysia

suraya.shahedi@stride.gov.my

Kamarul Arifin Ahmad, Department of Aerospace Engineering, Faculty of Engineering, Universiti Putra Malaysia, 43400 Serdang, Selangor, Darul Ehsan, Malaysia

aekamarul@upm.edu.my

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Published

2022-06-18

How to Cite

Mohd Yaacob, I. N., Singh, B., Mazlan, N., Gires, E. ., Basri , A. A. ., Ismail, O., Salleh, N. A., Shahedi, S., & Ahmad, K. A. . (2022). Numerical Study of the AP/Al/HTPB Composite Solid Propellant based Combustion Process in a Small Retro Rocket Motor. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 96(2), 98–114. https://doi.org/10.37934/arfmts.96.2.98114

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Articles