The third phase of a program to develop understanding of and tolerance-level criteria for the deleterious effects of electrostatic rocket exhaust (Cs, Cs(+), Hg, Hg(+)) and materials of rocket construction impinging on typical classes of spacecraft (S/C) surfaces was completed. Models of ion engine effluents and models describing the degradation of S/C surfaces by these effluents are presented. Experimental data from previous phases are summarized and Phase 2 data and analysis are presented in detail. The spacecraft design implications of ion engine contaminants are discussed.


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    Title :

    Electrostatic propulsion beam divergence effects on spacecraft surfaces, volume 2


    Contributors:
    Hall, D. F. (author)

    Publication date :

    1973-01-17


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English