A Unified Framework for Aerocapture Systems Analysis

Abstract

A unified framework for aerocapture systems analysis studies is presented, taking into account the interconnected nature of interplanetary trajectory design and vehicle design. One of the limitations of previous aerocapture systems studies is their focus on a single interplanetary trajectory for detailed subsystem level analysis. The proposed framework and aerocapture feasibility charts enable a mission designer to perform rapid trajectory and vehicle design trade-offs, and is illustrated with its application to a Neptune mission. The approach can be applied to other atmosphere-bearing Solar System destinations. The framework can be be implemented in an aerocapture software suite to enable rapid mission design studies.

Small Low-Cost Orbiters for Planetary Science using Photon and Aerocapture

“…Neptune aerocapture has been studied since 2003 using a mid-L/D vehicle to compensate for the large uncertainties [36]. However, since it has become clear such a vehicle would not be viable and recent studies have investigated using innovative techniques to leverage low-L/D aeroshells [37,38,39]. Two design reference missions are considered here.…”

“…The thermal protection system is a single-point-offailure for both entry probe and aerocapture missions, and hence must be qualified using ground tests to ensure mission success. The key variables for thermal protection system design are the maximum stagnation point heat rate, the stagnation pressure, and the integrated total heat load [6]. The heat rate and the stagnation pressure drives the TPS qualification, as it needs to be qualified for the combination of the heat rate and the stagnation pressure.…”