Flow Computation of a Satellite Thruster

인공위성 추력기의 유동 해석

  • 권순덕 (순천대학교 대학원 기계공학과) ;
  • 김성초 (순천대학교 기계우주항공공학부) ;
  • 김정수 (순천대학교 기계우주항공공학부) ;
  • 최종욱 (순천대학교 기계우주항공공학부) ;
  • 박정 (순천대학교 기계우주항공공학부)
  • Published : 2006.12.01


In order to design a micro-thruster which controls the altitude of a space vehicle for a very long lifetime, the flow field should be analyzed considering the nozzle geometry and the difference between stagnation and environmental pressures and so on. This paper describes the axisymmetric non-reacted computational results which were carried out to understand the basic flow phenomena according to the high nozzle pressure ratio. The area ratio is about 56 and the diameter of a nozzle exit is about 0.46 inch. The Mach cell and waves are predicted well.