Performance analysis of microthrusters based on coupled thermal-fluid modeling and simulation

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

Research output: Contribution to journalArticlepeer-review

Abstract

Gas flow and performance characteristics of a high-temperature micro-electronically machined systems (MEMS)-based thruster are studied using a coupled thermal-fluid analysis. The material thermal response governed by the transient-heat-conduction equation is obtained by the finite element method. The low-Reynolds number gas flow in the microthruster is modeled by the direct simulation Monte Carlo approach. The effects of Reynolds number, thermal boundary conditions, and micronozzle height are considered in detail. The predicted thrust and mass-discharge coefficient of the three-dimensional microthruster under different flow conditions decrease with time as the viscous losses increase for higher wall temperatures.

Original languageEnglish (US)
Pages (from-to)95-101
Number of pages7
JournalJournal of Propulsion and Power
Volume21
Issue number1
DOIs
StatePublished - 2005
Externally publishedYes

ASJC Scopus subject areas

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science

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