Conceptual Modeling of Supersonic Retropropulsion Flow Interactions and the Relationship to System Performance
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Author(s)
Korzun, Ashley M.
Braun, Robert D.
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Abstract
Supersonic retropropulsion is an entry, descent, and landing
technology applicable to and potentially enabling the
high-mass missions to the surface required for advanced
robotic and human exploration at Mars. For conceptual
design, an initial understanding of the significance
of retropropulsion configuration on the vehicle’s static
aerodynamic characteristics and the relation of this configuration
to other vehicle performance metrics that traditionally
determine vehicle configuration is necessary.
This work develops an approximate model for the aerodynamic
- propulsive flow interaction based on momentum
transfer within the flowfield and the geometry of relevant
flow structures. This model is used to explore the impact
of operating conditions, required propulsion system performance,
propulsion system composition, and vehicle
configuration on the integrated aerodynamic drag characteristics
of full-scale vehicles for Mars entry, descent,
and landing. Conclusions are then drawn on the fidelity
and effort required to support specific design trades for
supersonic retropropulsion.
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Date
2012-06
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Paper
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