The Space Storable Rocket Technology Program (SSRT) was conducted to establish a technology for a new class of high performance and long life bipropellant engines using space storable propellants. The results are described. Task 1 evaluated several characteristics for a number of fuels to determine the best space storable fuel for use with LO2. The results indicated that LO2-N2H4 is the best propellant combination and provides the maximum mission/system capability maximum payload into GEO of satellites. Task 2 developed two models, performance and thermal. The performance model indicated the performance goal of specific impulse greater than or = 340 seconds (sigma = 204) could be achieved. The thermal model was developed and anchored to hot fire test data. Task 3 consisted of design, fabrication, and testing of a 200 lbf thrust test engine operating at a chamber pressure of 200 psia using LO2-N2H4. A total of 76 hot fire tests were conducted demonstrating performance greater than 340 (sigma = 204) which is a 25 second specific impulse improvement over the existing highest performance flight apogee type engines.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Space Storable Rocket Technology (SSRT) Basic Program


    Contributors:
    M. L. Chazen (author) / T. Mueller (author) / A. R. Casillas (author) / D. Huang (author)

    Publication date :

    1992


    Size :

    100 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Space Storable Rocket Technology (SSRT) basic program

    Chazen, M. L. / Mueller, T. / Casillas, A. R. et al. | NTRS | 1992



    A summary of the Space Storable Rocket Technology Program

    Chazen, Melvin / Mueller, Thomas | AIAA | 1995


    Space Storable Hybrid Rocket Technology Development

    Vaughan, David / Nakazono, Barry / Karp, Ashley C. | NTRS | 2018