Title:
Computational Aerodynamic Analysis of a Tension Cone Supersonic Inflatable Aerodynamic Decelerator
Computational Aerodynamic Analysis of a Tension Cone Supersonic Inflatable Aerodynamic Decelerator
Author(s)
Clark, Ian G.
Braun, Robert D.
Braun, Robert D.
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Abstract
The 2009 Mars Science Laboratory mission has
brought renewed awareness to the difficulty of landing large
payloads on the surface of Mars. As a result, a new suite of
decelerator technologies is being investigated for future
robotic and human-precursor missions. One such
technology is the supersonic inflatable aerodynamic
decelerator (IAD). Previous studies have shown that a
supersonic IAD can provide sizable increases in landed
mass versus traditional parachute based systems,
particularly for near-term robotic mission. This is due to the
ability of an IAD to deploy at higher Mach numbers and
dynamic pressures than a parachute, thus allowing for
greater deceleration earlier in the entry sequence. 1 2
As part of the Program to Advance Inflatable Decelerators
for Atmospheric Entry, one particular configuration, the
tension cone, has undergone a series of wind tunnel
experiments designed to acquire a full characterization of
the aerodynamic performance of a particular tension cone
geometry. One test objective entailed the acquisition of a
data set useful for validating computational tools for later
IAD analysis efforts.
This paper presents a summary of the work performed in
investigating two separate computational fluid dynamics
codes for their suitability in predicting tension cone
performance. The first code, NASCART-GT, is a solution adaptive,
Cartesian grid code that is used for rapid inviscid
analysis of axisymmetric geometries. The second code,
Overflow was used for Navier-Stokes analysis of three-dimensional
geometries. These codes were evaluated for
their ability to match measured pressure distributions, static
force and moment coefficients, and observed flowfield
characteristics. Overflow is also used to investigate flow
features that were not observed during testing, such as the
aft body recirculation region.
Additional investigation into the aerodynamic performance
of a tension cone was performed through a parametric
analysis of multiple tension cone geometries. Three primary
shape parameters were varied with the goal of identifying
undesirable flowfield characteristics such as shocks attached
to the surface of the tension shell and to provide insight into
the sensitivity of drag to tension cone geometry.
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Date Issued
2009-03
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