Aerothermal Design of a Common Probe for Multiple Planetary DestinationsThe idea of a single design of a capsule, for atmospheric entry at Venus, Jupiter, Saturn, Uranus, and Neptune and delivery of payloads for in situ scientific experiments, is currently being pursued by a team of scientists and engineers drawn from four NASA centers - Ames, Langley, JPL, and Goddard. For notional suites of instruments (the selection depending on the destination), interplanetary trajectories have been developed by team members at JPL and Goddard. Using the entry states provided by these trajectories, 3DOF atmospheric flight trajectories have been developed by Langley [4] and Ames. The range of entry flight path angles for each destination is chosen such that the deceleration load lies between 50 g (shallow) and 150-200 g (steep) for a 1.5 m (diameter) rigid aeroshell based on a 45deg sphere-cone geometry and an entry mass of 400 kg.
Document ID
20180004316
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Allen Jr., G. A. (Analytical Mechanics Associates, Inc. Moffett Field, CA, United States)
Milos, F. S. (NASA Ames Research Center Moffett Field, CA, United States)
White, Todd R. (NASA Ames Research Center Moffett Field, CA, United States)
Prabhu, Dinesh K. (Analytical Mechanics Associates, Inc. Moffett Field, CA, United States)