Entry System Options for Human Return from the Moon and Mars
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 thermal protection system mass fraction, ease of launch vehicle integration, and system elegance and simplicity. Numerous configuration options exist that achieve this lift-to-drag ratio.
Additional Information
© 2006 by Z. R. Putnam and R. D. Braun. This study was conducted under a partnership with the Charles Stark Draper Laboratory as part of the NASA Exploration Systems Mission Directorate Concept Exploration and Refinement study. The guidance and constructive comments of Gregg Barton (Charles Stark Draper Laboratory) and Paul Wooster (Massachusetts Institute of Technology) are appreciated.Attached Files
Published - 1.20351.pdf
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Additional details
- Eprint ID
- 119915
- Resolver ID
- CaltechAUTHORS:20230310-764511000.2
- NASA
- Created
-
2023-03-14Created from EPrint's datestamp field
- Updated
-
2023-03-15Created from EPrint's last_modified field
- Other Numbering System Name
- AIAA Paper
- Other Numbering System Identifier
- 5915