Journal of computational fluids engineering (한국전산유체공학회지)

Korean Society of Computational Fluids Engineering (한국전산유체공학회)
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MULTI-PHYSICAL SIMULATION FOR THE DESIGN OF AN ELECTRIC RESISTOJET GAS THRUSTER IN THE NEXTSAT-1

차세대 인공위성 전기저항제트 가스추력기의 다물리 수치모사

  • Chang, S.M. (School of Mechanical, Automotive, Naval Architecture, and Ocean Engineering, Kunsan National University) ;
  • Choi, J.C. (Research Institute, Space Solution, Inc.) ;
  • Han, C.Y. (Satellite R&D Head Office, Korea Aerospace Research Institute) ;
  • Shin, G.H. (SaTReC, Korea Advanced Institute of Science and Technology)
  • 장세명 (군산대학교 기계자동차조선해양공학부) ;
  • 최진철 (스페이스솔루션(주) 연구소) ;
  • 한조영 (한국항공우주연구원 위성연구본부) ;
  • 신구환 (한국과학기술원 인공위성연구센터)
  • Received : 2016.03.31
  • Accepted : 2016.06.23
  • Published : 2016.06.30
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Abstract

NEXTSat-1 is the next-generation small-size artificial satellite system planed by the Satellite Technology Research Center(SatTReC) in Korea Advanced Institute of Science and Technology(KAIST). For the control of attitude and transition of the orbit, the system has adopted a RHM(Resisto-jet Head Module), which has a very simple geometry with a reasonable efficiency. An axisymmetric model is devised with two coil-resistance heaters using xenon(Xe) gas, and the minimum required specific impulse is 60 seconds under the thrust more than 30 milli-Newton. To design the module, seven basic parameters should be decided: the nozzle shape, the power distribution of heater, the pressure drop of filter, the diameter of nozzle throat, the slant length and the angle of nozzle, and the size of reservoir, etc. After quasi one-dimensional analysis, a theoretical value of specific impulse is calculated, and the optima of parameters are found out from the baseline with a series of multi-physical numerical simulations based on the compressible Navier-Stokes equations for gas and the heat conduction energy equation for solid. A commercial code, COMSOL Multiphysics is used for the computation with a FEM (finite element method) based numerical scheme. The final values of design parameters indicate 5.8% better performance than those of baseline design after the verification with all the tuned parameters. The present method should be effective to reduce the time cost of trial and error in the development of RHM, the thruster of NEXTSat-1.

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References

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