Thermal insulation requirements of vehicles exposed for extended periods to solar space environment and heat flow paths pertaining to bipropellant liquid propulsion systems; comparison of several high energy propellant combinations is made in terms of payload capability in mission; results show that systems considered can sustain coast periods up to 15,000 hr (2 yr) without significant change in payload magnitudes.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    High energy propellant comparisons for space missions


    Additional title:

    ARS J


    Contributors:
    Burry, R.V. (author) / Jortner, J. (author) / Rosemary, J.K. (author)

    Published in:

    ARS Journal ; 31 , n 5 ; p 609-613


    Publication date :

    1961


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Manned Mars missions using propellant from space

    Zuppero, Anthony C. / Olson, Timothy S. / Redd, Lawrence R. | American Institute of Physics | 1993


    Manned Mars Missions using Propellant from Space

    Zuppero, A. C. / Olson, T. S. / Redd, L. R. et al. | British Library Conference Proceedings | 1993


    ADVANCED HIGH ENERGY MATERIALS FOR FUTURISTIC LIQUID PROPELLANT ROCKET ENGINES PROPELLED SPACE MISSIONS

    Malhotra, Vinayak / Ray, Triparna / Velmurugan, Priyadharshini | TIBKAT | 2021