A 2- by 4-ft flightweight panel was subjected to thermal/structural tests representative of design flight conditions for a Mach 6.7 transport and to off-design conditions simulating flight maneuvers and cooling system failures. The panel utilized Rene 41 heat shields backed by a thin layer of insulation to radiate away most of the 12 Btu/ft2-sec incident heating. A solution of ethylene glycol in water circulating through tubes in an aluminum-honeycomb-sandwich panel absorbed the remainder of the incident heating (0.8 Btu/sq ft-sec). The panel successfully withstood (1) 46.7 hr of radiant heating which included 53 thermal cycles and 5000 cycles of uniaxial inplane loading of + or - 1200 lfb/in; (2) simulated 2g-maneuver heating conditions and simulated cooling system failures without excessive temperatures on the structural panel; and (3) the extensive thermal/structural tests and the aerothermal tests reported in NASA TP-1595 without significant damage to the structural panel, coolant leaks, or hot-gas ingress to the structural panel.


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    Titel :

    Flightweight Radiantly and Actively Cooled Panel: Thermal and Structural Performance


    Beteiligte:
    C. P. Shore (Autor:in) / R. J. Nowak (Autor:in) / H. N. Kelly (Autor:in)

    Erscheinungsdatum :

    1982


    Format / Umfang :

    53 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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