| タイトル | Estimates of Heat Shielding Requirements for Saturn Probe Missions |
| 著者（英） | Tauber, M.; Patterson, J.; Papadopoulos, P.; Yang, L.; Cavolowsky, John A.; Wercinski, P. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1995-01-01 |
| 言語 | eng |
| 内容記述 | Entry trajectories, decelerations, heating and heat shielding requirements of probes entering the atmosphere of Saturn at relative entry velocities ranging from 26.5 - 33.0 km/sec were studied. Much of the Galileo Jupiter probe technology was applicable to these outer planet probes; therefore, the same configuration was used. A wide range entry flight path angles were used in the trajectory analysis in order to satisfy the complete range of arrival conditions and trajectory requirements. Various entry probe sizes and a range of entry masses from 32 - 258 kg were considered. The carbon phenolic heat shield material used on the Galileo and the successful Pioneer-Venus probes was selected. Turbulent boundary layer convection dominated the heating of the Saturn probes; radiative heating was negligible by comparison at the entry velocities considered. The peak heating rates were found to be about 4 kW per square centimeter, or approximately 17% of the Galileo probe's expected maximum value. The forebody heat shield mass fractions for the Saturn probes were found to vary from about 0.18 to 0.28. By comparison, the Pioneer-Venus probes' heat shield mass fractions ranged from 0.10 to 0.13 and the Galileo probe's forebody value is 0.43. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| 権利 | No Copyright |
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