This paper presents the results of a program to describe the operational characteristics of an engineering model multipropellant resistojet for application as an auxiliary propulsion system for space station. Performance was measured on hydrogen, helium, methane, water (steam), nitrogen, air, argon, and carbon dioxide. Thrust levels ranged from 109 to 355 mN, power levels ranged from 167 to 506 W, and specific impulse impulse ranged from 93 to 385 sec, depending upon the propellant, chamber pressure, and heater current level selected. Detailed thermal maps of the heater and heat exchanger were also obtained for operation with carbon dioxide.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Preliminary performance characterizations of an engineering model multipropellant resistojet for space station application


    Additional title:

    Leistungseigenschaften des technischen Modells einer Multitreibstoff-Resistoduese fuer Raumstationen


    Contributors:
    Morren, W.E. (author) / Hay, S.S. (author) / Haag, T.W. (author) / Sovey, J.S. (author)

    Published in:

    AIAA-Papers ; Jul ; 1-22


    Publication date :

    1987


    Size :

    22 Seiten, 10 Bilder, 9 Tabellen, 16 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English