Title:
Entry System Options for Human Return from the Moon and Mars
Entry System Options for Human Return from the Moon and Mars
Author(s)
Putnam, Zachary R.
Braun, Robert D.
Rohrschneider, Reuben R.
Dec, John A.
Braun, Robert D.
Rohrschneider, Reuben R.
Dec, John A.
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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.
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Date Issued
2005-08
Extent
368428 bytes
Resource Type
Text
Resource Subtype
Paper