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The numerical method for the steady Navier-Stokes equations is studied to solve the inner flow field of the nozzle. The N-S computing technique with the slip-boundary theory is developed for the near-continuum slip flow near the nozzle exit. The DSMC method for the flow of axial symmetry is studied to simulate the core plume, the DSMC scheme for the simulation of three-dimensional far-field plume flow is developed, and the DSMC method is studied for multi-species mixture plume. Then, the multiregion decomposing and coupling technique is developed to solve the inside and outside flow of the thruster including the near-field, far-field, backflow and gas-surface infected regions. As a result, the numerical simulation method has been presented to compute the gas-fired mixture plume from the attitude-control thruster of the satellite and the impinging contamination on the surface of the solar array panel and satellite. To study the contamination effects produced by the five-species mixture plume from two representative attitude-control thrusters installed in different locations of the satellite in orbit, the present method is adopted to simulate the nozzle inflow, tremendous plume flowfield of five-species mixture including the impinging contamination of the particles from the gas-fired plume. The flowfield properties of the gas-fired plume from the attitude-control thrusters are obtained, the related computed results are compared and analyzed with the experimental measurement and other theoretical calculation, which validates the reliability of the present numerical method. [ABSTRACT FROM AUTHOR]