Numerical Simulation of a Dual Pulse Solid Rocket Motor Flow Field

  • Afroz Javed Defence Research & Development Laboratory, Hyderabad
  • P Manna Defence Research & Development Laboratory, Hyderabad
  • Debasis Chakraborty Defence Research & Development Laboratory, Hyderabad
DOI: https://doi.org/10.14429/dsj.62.1418
Keywords: Numerical simulation, dual pulse solid rocket, pulse separation device

Abstract

Numerical simulations are carried out for the internal flow field of a dual pulse solid rocket motor port to understand the flow behaviour. Three dimensional Reynolds Averaged Navier Stokes equations are solved alongwith shear stress transport turbulence model using commercial code. The combustion gas is assumed as a mixture of alumina and gases and single phase flow calculations are done with the thermo chemical properties provided for the mixture. The simulation captures all the essential features of the flow field. The flow accelerates through the pulse separation device (PSD) port and high temperature and high velocity gas is seen to impinge the motor wall near the PSD port. The overall total pressure drop through motor port and through PSD is found to be moderate.

Defence Science Journal, 2012, 62(6), pp.369-374, DOI:http://dx.doi.org/10.14429/dsj.62.1418

Author Biographies

Afroz Javed, Defence Research & Development Laboratory, Hyderabad
Mr Afroz Javed did his MTech from Indian Institute of Technology (IIT) Madras, in 1996. Presently he is working in the Directorate of Computational Dynamics, Defence Research & Development Laboratory (DRDL), Hyderabad. He is pursuing his PhD from Indian Institute of Science (IISc), Bengaluru. He has published 2 journal papers and 3 conference papers. His research interests include: Computational fluid dynamics (CFD), propulsion, combustion instability, and turbulent compressible mixing.
P Manna, Defence Research & Development Laboratory, Hyderabad
Dr P Manna obtained his PhD (Thermal Science and Engineering) from IIT, Kharagpur. Presently he is working as a Scientist in the Directorate of Computational Dynamics, DRDL, Hyderabad. He has published 10 journal and 20 conference publications in the national and international level. His research interests include: CFD, propulsion, heat transfer, and high speed reacting flow.
Debasis Chakraborty, Defence Research & Development Laboratory, Hyderabad
Dr Debasis Chakraborty obtained his PhD (Aerospace Engineering) from IISc, Bengaluru. Presently, he is working as Technology Director, Computational Dynamics, DRDL, Hyderabad. He was the guest editor of special Issue of Defence Science Journal on computational fluid dynamics. He has about 46 journal and 58 conference publications to his credit. His research interests include: CFD, aero-dynamics, high-speed combustion, and propulsion.
Published
2012-11-12
How to Cite
Javed, A., Manna, P., & Chakraborty, D. (2012). Numerical Simulation of a Dual Pulse Solid Rocket Motor Flow Field. Defence Science Journal, 62(6), 369-374. https://doi.org/10.14429/dsj.62.1418
Issue
Vol 62 No 6
Section
Aeronautical Systems
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