Numerical study on ignition process of a solid propellant microthruster

Teng Li*, Shu Zhou Fang, Xu Hui Liu, Hong Peng Ma

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

1 Citation (Scopus)

Abstract

In order to investigate the local ignition process of a solid propellant microthruster with restricted ignition device heating surface, by numerical simulation, a local ignition model based on solid-fluid coupled heat transfer model and local remeshing technique was proposed, and the solid propellant microthruster ignition process under normal pressure was studied. The flow and heat transfer property of gas inside the microthruster was analyzed. Based on the thrust-time curve, the proposed model was compared with the whole surface ignition model, as well as the local ignition model proposed by Jongkwang Lee. Simulation results clearly show that the burning surface expands due to the heat feedback of the gas to unburned propellant surface. The gas velocity is under local sound speed at the nozzle throat, which generates adverse pressure gradient in the divergent nozzle, hence causes boundary layer split. As the adverse pressure gradient at the backward of the divergent nozzle increases, the backflow becomes more significant, and enhances heat transfer and kinetic energy dissipation of the gas. The thrust increasing tendency agrees better with experimental results.

Original languageEnglish
Pages (from-to)1290-1296
Number of pages7
JournalTuijin Jishu/Journal of Propulsion Technology
Volume35
Issue number9
DOIs
Publication statusPublished - 1 Sept 2014

Keywords

  • Adverse pressure gradient
  • Backflow
  • Heat feedback
  • Local ignition model
  • Solid propellant microthruster

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Li, T., Fang, S. Z., Liu, X. H., & Ma, H. P. (2014). Numerical study on ignition process of a solid propellant microthruster. Tuijin Jishu/Journal of Propulsion Technology, 35(9), 1290-1296. https://doi.org/10.13675/j.cnki.tjjs.2014.09.021