Coupled thermal-fluid analyses of microthruster flows

A. A. Alexeenko, D. A. Levin, D. A. Fedosov, S. F. Gimelshein, R. J. Collins

Research output: Chapter in Book/Report/Conference proceedingConference contribution


A coupled thermal and fluid analysis of a 2D and 3D micronozzle is presented. The material thermal response is modeled by the transient heat conduction equation which is solved by the finite element method. The gas flow solution is obtained by the direct simulation Monte Carlo (DSMC) method for Re=35 and 175. The DSMC calculated heat fluxes at the gas-solid interface are applied as a boundary condition to the heat conduction in the solid. The temporal variation of the material temperature and gas flowfields are calculated as well as the thruster operational time limits for two different thermal boundary conditions of a thermally insulated wall and convective cooling. The predicted thrust and mass discharge coefficient of both 2D and 3D micronozzle models decreases in time as the viscous losses increase for higher wall temperatures.

Original languageEnglish (US)
Title of host publication41st Aerospace Sciences Meeting and Exhibit
StatePublished - 2003
Externally publishedYes
Event41st Aerospace Sciences Meeting and Exhibit 2003 - Reno, NV, United States
Duration: Jan 6 2003Jan 9 2003

Publication series

Name41st Aerospace Sciences Meeting and Exhibit


Other41st Aerospace Sciences Meeting and Exhibit 2003
Country/TerritoryUnited States
CityReno, NV

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering


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