Title:
Entry System Options for Human Return from the Moon and Mars

dc.contributor.author Putnam, Zachary R. en_US
dc.contributor.author Braun, Robert D. en_US
dc.contributor.author Rohrschneider, Reuben R. en_US
dc.contributor.author Dec, John A. en_US
dc.contributor.corporatename American Institute of Aeronautics and Astronautics
dc.date.accessioned 2006-03-17T16:00:02Z
dc.date.available 2006-03-17T16:00:02Z
dc.date.issued 2005-08
dc.description 2005 AIAA Atmospheric Flight Mechanics Conference August 2005, San Francisco, CA. en_US
dc.description.abstract Earth entry system options for human return missions from the Moon and Mars were analyzed and compared to identify trends among the configurations and trajectory options and to facilitate informed decision making at the exploration architecture level. Entry system options included ballistic, lifting capsule, biconic, and lifting body configurations with direct entry and aerocapture trajectories. For each configuration and trajectory option, the thermal environment, deceleration environment, crossrange and downrange performance, and entry corridor were assessed. In addition, the feasibility of a common vehicle for lunar and Mars return was investigated. The results show that a low lift-to-drag ratio (L/D = 0.3) vehicle provides sufficient performance for both lunar and Mars return missions while providing the following benefits: excellent packaging efficiency, low structural and TPS mass fraction, ease of launch vehicle integration, and system elegance and simplicity. Numerous configuration options exist that achieve this L/D.
dc.format.extent 368428 bytes
dc.format.mimetype application/pdf
dc.identifier.uri http://hdl.handle.net/1853/8434
dc.language.iso en_US
dc.publisher Georgia Institute of Technology en_US
dc.publisher.original American Institute of Aeronautics and Astronautics (AIAA)
dc.relation.ispartofseries SSDL ; AIAA 2005-5915 en_US
dc.subject Earth entry systems
dc.subject Trajectory analysis
dc.subject Direct entry trajectories
dc.subject Aerocapture trajectories
dc.title Entry System Options for Human Return from the Moon and Mars en_US
dc.type Text
dc.type.genre Paper
dspace.entity.type Publication
local.contributor.corporatename Space Systems Design Laboratory (SSDL)
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
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