Aspects are examined of an investigation by the Marshall Space Flight Center into the conceptual feasibility of increasing the thrust performance of the Space Shuttle Main Engine (SSME) by using a conical nozzle extension fitted with an ablative insert in order to achieve a low-cost, near-term gain in payload. The ablating insert would provide a controlled increase in nozzle expansion ratio during launch and early climbout (first 30-60 seconds) so as to reduce thrust loss from nozzle over-expansion in the lower atmosphere. Summaries are given of JPL studies in the area of: defining the near-wall flow environment in the extended nozzle insert region; selecting potential insert materials; conceptualizing an extension/insert geometrical configuration; and identifying future experimental efforts necessary to verify the feasibility of the concepts.


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    Titel :

    Thrust improvement with ablative insert nozzle extension


    Beteiligte:
    Clayton, R. M. (Autor:in) / Back, L. H. (Autor:in)


    Erscheinungsdatum :

    01.02.1986



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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