A design study of pumped two-phase and capillary-pumped thermal control systems (TCS) was conducted on a typical, advanced earth-orbiting spacecraft (AEOS). NASA's Upper Atmosphere Research Satellite (UARS) size and baseline design were chosen as the configuration for AEOS; however, the power requirements were increased and the allowable temperature range was decreased to represent the requirements of a more advanced spacecraft.For peak-power dissipations of 1 or 2 kW, the capillary-pumped system was lightest. At these power dissipations, the line sizes were the smallest available: therefore, there was no net advantage to having a pump. The 91kg weight saving over the 173kg conventional system was due primarily to reduced heater power. However, more convenient component locations also reduced the structural weight significantly. In addition to the weight advantage, the more nearly isothermal spacecraft obtainable with the two-phase system permits less compensation for thermal distortion; a simpler, less costly structure results.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Advanced Thermal-Control Systems as Applied to Future NASA Spacecraft


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Intersociety Conference on Environmental Systems ; 1985



    Publication date :

    1985-07-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Advanced thermal-control systems as applied to future NASA spacecraft

    Bravo, C. L. / Costello, F. A. / Ripple, J. W., Jr. | NTRS | 1985



    NASA Thermal Control Technologies for Robotic Spacecraft

    T. D. Swanson / G. C. Birur | NTIS | 2003


    NASA thermal control technologies for robotic spacecraft

    Swanson, T.D. / Birur, G.C. | Tema Archive | 2003


    NASA thermal control technologies for robotic spacecraft

    Swanson, T. / Birur, G. C. | NTRS | 2001