한국가시화정보학회:학술대회논문집
- 한국가시화정보학회 2006년도 추계학술대회 논문집
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- Pages.145-148
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- 2006
인공위성 추력기의 유동 해석
Flow Computation of a Satellite Thruster
초록
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.
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