(Georgia Institute of Technology, 2006-05-07)
Clark, Ian G.
A study was undertaken to assess the advantages and feasibility of using ballutes for
Earth entry at lunar return velocities. Using analysis methods suitable for conceptual
design, multiple entry strategies were investigated. Entries that jettison the ballute after
achieving orbit were shown to reduce heating rates to within reusable thermal protection
system limits and deceleration was mitigated to approximately four g’s when a moderate
amount of lift was applied post-jettison. Ballute size drivers were demonstrated to be the
thermal limitations and areal densities of the ballute material. Performance requirements
for both of those metrics were generated over a range of total ballute system masses.