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Thermal protection systems are a critical component of planetary exploration,enabling probes to enter the atmosphere and perform in-situ measurements. Theaero-thermal conditions encountered during entry are destination and vehicledependent, ranging from relatively benign conditions at Mars and Titan, toextreme conditions at Venus and Jupiter. The thermal protection system is asingle-point-of-failure for both entry probe and aerocapture missions, andhence must be qualified using ground tests to ensure mission success. The highdensity Carbon-Phenolic which was used in the Galileo and the Pioneer Venusmissions is no longer available due to the lack of the manufacturing base forits raw materials. To address the need for Venus and outer planet missions,NASA has developed the Heatshield for Extreme Environment Entry Technology(HEEET). The present study uses the Aerocapture Mission Analysis Tool (AMAT) toperform a comparative study of the thermal protection system requirements forvarious planetary destinations and the applicability of HEEET for future entryand aerocapture missions. The heat rate and stagnation pressure for aerocaptureis significantly less compared to probe entry. The large heat loads duringaerocapture present a challenge, but HEEET is capable of sustaining large heatloads within a reasonable TPS mass fraction.

Thermal Protection System Requirements for Future Planetary Entry and Aerocapture Missions