A 10,000 lbf thrust chamber was developed for the Upper Stage Flight Experiment (USFE). This thrust chamber uses hydrogen peroxide/JP-8 oxidizer/fuel combination. The thrust chamber comprises an oxidizer dome and manifold, catalyst bed assembly, fuel injector, and chamber/nozzle assembly. Testing of the engine was done at NASA's Stennis Space Center (SSC) to verify its performance and life for future upper stage or Reusable Launch Vehicle applications. Various combinations of silver screen catalyst beds, fuel injectors, and combustion chambers were tested. Results of the tests showed high C* efficiencies (97% - 100%) and vacuum specific impulses of 275 - 298 seconds. With fuel film cooling, heating rates were low enough that the silica/quartz phenolic throat experienced minimal erosion. Mission derived requirements were met, along with a perfect safety record.


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    Titel :

    Upper Stage Flight Experiment 10K Engine Design and Test Results


    Beteiligte:
    R. Ross (Autor:in) / D. Morgan (Autor:in) / D. Crockett (Autor:in) / L. Martinez (Autor:in) / W. Anderson (Autor:in)

    Erscheinungsdatum :

    2000


    Format / Umfang :

    11 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Upper Stage Flight Experiment 10K Engine Design and Test Results

    Ross, R. / Morgan, D. / Crockett, D. et al. | NTRS | 2000


    Upper Stage Flight Experiment 10K engine design and test results

    Ross, R. / Morgan, D. / Crockett, D. et al. | AIAA | 2000


    Upper Stage Flight Experiment

    Anderson, W. E. / Boxwell, R. / Crockett, D. V. et al. | British Library Conference Proceedings | 1999


    Upper-Stage Flight Experiment

    Anderson, W. E. / Boxwell, R. / Crockett, D. V. et al. | NTRS | 1999


    Upper-Stage Flight Experiment

    W. E. Anderson / R. Boxwell / D. V. Crockett et al. | NTIS | 1999