Thermophysics of Spacecraft and Outer Planet Entry Probes: Technical Papers Selected from AIAA 14th Aerospace Sciences Meeting, January 1976, and the AIAA 11th Thermophysics Conference, July 1976 (with One Exception), Subsequently Revised for this VolumeAllie M. Smith, American Institute of Aeronautics and Astronautics |
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Results 1-3 of 41
Page xiv
... thermal control system which attenuated the in - flight warming trend of a passively cooled satellite and thus extended its period of thermal performance by almost one year . Analyses of the three basic elements of a heat pipe , the ...
... thermal control system which attenuated the in - flight warming trend of a passively cooled satellite and thus extended its period of thermal performance by almost one year . Analyses of the three basic elements of a heat pipe , the ...
Page 38
... thermal behavior of the heat - pipe con- denser under 0 g condition . Although the effects of gravity on heat - pipe performance such as " puddling " are known to be GROOVE LAND 2a áž” PIPE WALL GROOVED HEAT PIPE CROSS 38 Y. KAMOTANI.
... thermal behavior of the heat - pipe con- denser under 0 g condition . Although the effects of gravity on heat - pipe performance such as " puddling " are known to be GROOVE LAND 2a áž” PIPE WALL GROOVED HEAT PIPE CROSS 38 Y. KAMOTANI.
Page 81
... heat - transfer coefficient has been intro- duced in this investigation in a manner that allows utiliza- tion of the results of groove heat ... heat - pipe experiments available in THERMAL ANALYSIS OF HEAT - PIPE EVAPORATOR WALLS 81.
... heat - transfer coefficient has been intro- duced in this investigation in a manner that allows utiliza- tion of the results of groove heat ... heat - pipe experiments available in THERMAL ANALYSIS OF HEAT - PIPE EVAPORATOR WALLS 81.
Contents
Development of PhaseChange Systems | 19 |
Analysis of Axially Grooved HeatPipe Condensers | 37 |
GradedPorosity HeatPipe Wicks 15 | 57 |
Copyright | |
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ablation absorption AIAA analysis angle application approximately assumed atmosphere axial body boundary calculated carbon coating coefficient conductivity cone configuration considered constant convective heating cool coupled crystal decrease determined developed distance distribution effect energy engine entry environment equation experiment experimental flow flux FRSI function given groove heat shield heating rates incidence included increase initial integral intensity layer liquid louver mass material maximum measured melting method nose obtained occurs optical outgassing parameter peak performance pipe Planet plume predicted present pressure probe problem properties radiation radiative heating range ratio reflectance region relative resistance respectively sample shape shock shown shown in Fig silica solar solid solution Space species spectral sphere surface Table temperature thermal thickness tion transfer vapor variation wall