The work performed during the implementation phase of an integrated set of computer codes developed to study plume flows generated from satellite main engines and thrusters is described. The major aim of the work was to achieve the capability to cover the complete cycle of gasdynamics analyses required to assess the impact that plume impingement effects may have on the satellite and on its sensitive payload or instrumentation. A simplified configuration of the European Space Agency's satellite for the X-Ray Multi-Mirror Mission was considered as a test case for the purpose of implementing and testing the computer codes. In this regard, the issue of major concern consisted of the estimation of the thrust loss produced by plume impingement during the injection maneuver of the satellite into a higher perigee orbit. Results obtained by Navier-Stokes, direct simulation Monte Carlo, and test particle Monte Carlo calculations are described, and the flow patterns settling in during thruster firing in the regions of interest are discussed. The major finding of the study was the detection of a serious incompatibility between the preliminary assumed design orientation of the satellite thrusters and the flight dynamics requirements imposed by the satellite mission. In conclusion, the study fully provides evidence of the critical role and usefulness of this kind of numerical analyses in providing answers contributing to the optimization of successful satellite design.
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