Fully-Propulsive Mars Atmospheric Transit Strategies for
High-Mass Missions
Author(s)
Marsh, Christopher L.
Advisor(s)
Braun, Robert D.
Editor(s)
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Abstract
A systems analysis focused on the use of propulsion during the EDL sequence at Mars for
high-payload missions is presented. Trajectory simulation and mass sizing are performed to
analyze the feasibility of a fully-propulsive descent. A heat rate boundary and associated
control law are developed in an effort to limit the heating loads placed on the vehicle.
Analysis is performed to explore the full-propulsive EDL strategy’s sensitivity to the
vehicle’s propulsive capabilities and aero-propulsive and vehicle models. The EDL strategy
is examined for ranges of initial masses and heat rate constraints, outlining an envelope of
feasibility. The proposed architecture is compared against EDL systems in which significant
aeroassist technology is employed. With this information, an overview of the impact of a
fully-propulsive EDL system on spacecraft design and functionality is offered
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Date
2009-04-29
Extent
Resource Type
Text
Resource Subtype
Masters Project
Rights Statement
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