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 |
From inside the book
Results 1-3 of 81
Page 32
... shown in Fig . 5. There was no deviation between the empty container calibration strain and the strain in the walls during PCM testing . The scaled rate of addition and removal of heat is shown in Fig . 8 along with the melting and ...
... shown in Fig . 5. There was no deviation between the empty container calibration strain and the strain in the walls during PCM testing . The scaled rate of addition and removal of heat is shown in Fig . 8 along with the melting and ...
Page 66
... demonstrated performance shown in Fig . 5 was not as high as it could be . For purposes of com- parison , the performance of the extruded axially grooved heat pipe used on the ATS - 66 satellite is also shown in Fig . 5 . Acknowledgment ...
... demonstrated performance shown in Fig . 5 was not as high as it could be . For purposes of com- parison , the performance of the extruded axially grooved heat pipe used on the ATS - 66 satellite is also shown in Fig . 5 . Acknowledgment ...
Page 312
... shown in Figs . 4-6 , which correspond to a 50 ° entry into the cool model of the Uranus atmosphere . The raw stagnation - point heating environment for the entry is shown in the left half of Fig ... shown on the right side of Fig . 4 ...
... shown in Figs . 4-6 , which correspond to a 50 ° entry into the cool model of the Uranus atmosphere . The raw stagnation - point heating environment for the entry is shown in the left half of Fig ... shown on the right side of Fig . 4 ...
Contents
Development of PhaseChange Systems | 19 |
Analysis of Axially Grooved HeatPipe Condensers | 37 |
GradedPorosity HeatPipe Wicks 15 | 57 |
Copyright | |
19 other sections not shown
Common terms and phrases
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