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Aerothermal Design of a Common Probe for Multiple Planetary Destinations
- Publication Year :
- 2018
- Publisher :
- United States: NASA Center for Aerospace Information (CASI), 2018.
-
Abstract
- Estimate the mass of the Thermal Protection System (TPS) for a single design construct of an atmospheric entry probe with a rigid aeroshell, which could be used at five destinations, i.e. Venus, Saturn, Uranus, Neptune, and perhaps, Jupiter. The entry mass of the probe is 400 kg with a ballistic coefficient of 216 kg/m2. Process: The 3DoF trajectory simulation program Traj, coupled with the TPS response program FIAT was used for simulation and design. The assumed atmospheric models were VIRA (Venus-GRAM) for Venus, the Julianne Moses' model for Saturn, a NASA Ames engineering model for Uranus, Neptune-GRAM for Neptune, and Galileo Probe (Al Seiff's) result for Jupiter.
Details
- Language :
- English
- Database :
- NASA Technical Reports
- Notes :
- NNA15BB15C
- Publication Type :
- Report
- Accession number :
- edsnas.20180006998
- Document Type :
- Report