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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Thrust improvement with ablative insert nozzle extension


    Contributors:


    Publication date :

    1986-02-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    Thrust improvement with ablative insert nozzle extension

    CLAYTON, R. M. / BACK, L. H. | AIAA | 1986



    Shuttle subscale ablative nozzle tests

    POWERS, L. / BAILEY, R. | AIAA | 1980


    Shuttle subscale ablative nozzle tests

    Powers, L. B. / Bailey, R. L. | NTRS | 1980


    Shuttle Subscale Ablative Nozzle Tests

    L.B. Powers / R.L. Balley | AIAA | 1982