Combined Analysis of Thruster Plume Behavior in Rarefied Region by Preconditioned Navier-Stokes and DSMC Methods

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  • LEE Kyun Ho
    Satellite Thermal & Propulsion Department, Korea Aerospace Research Institute
  • LEE Sung Nam
    Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology
  • YU Myoung Jong
    Satellite Thermal & Propulsion Department, Korea Aerospace Research Institute
  • KIM Su Kyum
    Satellite Thermal & Propulsion Department, Korea Aerospace Research Institute
  • BAEK Seung Wook
    Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology

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Satellite attitude is usually controlled by plume exhaust from thrusters into the vacuum of space. To study the plume effects in the highly rarefied region, the Direct Simulation Monte Carlo (DSMC) method is usually used, because the plume flow field contains the entire range of flow regime from the near-continuum near the nozzle exit through the transitional state to free molecular state at the far field region from the nozzle. The purpose of this study is to investigate the behavior of a small monopropellant thruster plume in the vacuum region numerically by using the DSMC method. To obtain more accurate results, the preconditioned Navier-Stokes algorithm is introduced to calculate continuum flow fields inside the thruster to predict nozzle exit properties, which are used for inlet conditions of DSMC method. As a result, the plume characteristics in the highly rarefied flow, such as strong nonequilibrium near nozzle exit, large back flow region, etc., are investigated.

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