Title:
Sizing of an Entry, Descent, and Landing System for Human Mars Exploration
Sizing of an Entry, Descent, and Landing System for Human Mars Exploration
Author(s)
Christian, John A., III
Wells, Grant William
Lafleur, Jarret M.
Manyapu, Kavya
Verges, Amanda
Lewis, Charity
Braun, Robert D.
Wells, Grant William
Lafleur, Jarret M.
Manyapu, Kavya
Verges, Amanda
Lewis, Charity
Braun, Robert D.
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Abstract
The human exploration of Mars presents many challenges, not least of which is the task
of entry, descent, and landing (EDL). Because human-class missions are expected to have
landed masses on the order of 40 to 80 metric tons, significant challenges arise that have not
been seen to date in robotic missions. This study provides insight into the challenges
encountered as well as potential solutions through parametric trade studies on vehicle size
and mass. Aerocapture and entry-from-orbit analyses of 10 and 15 m diameter aeroshells
with a lift-to-drag ratio of 0.3 or 0.5 were investigated. Results indicate that in the limit, a
crew capsule used only for descent could have an initial mass as low as 20 t. For larger
landed payloads, such as a 20 t surface power system, a vehicle with an initial mass on the
order of 80 t may be required. In addition, no feasible EDL systems were obtained with the
capability to deliver more than approximately 25 t of landed payload to the Mars surface for
initial masses less than 100 t. This suggests that an aeroshell diameter of 15 m may not be
sufficient for human Mars exploration.
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Date Issued
2006-09
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Text
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Paper