This paper appears in: Aerospace Conference Proceedings, 2000 IEEE
Publication Date: 2000
Volume: 7,
On page(s): 421-427 vol.7
Meeting Date: 03/18/2000 - 03/25/2000
Location: Big Sky, MT, USA
ISBN: 0-7803-5846-5
References Cited: 6
INSPEC Accession Number: 6805592
Digital Object Identifier: 10.1109/AERO.2000.879309
Current Version Published: 2002-08-06
Abstract
An innovative, lightweight method, using an inflatable ballute, to
increase aerobraking drag and potentially reduce the size of spacecraft
(S/C) payloads, is presented. Computational fluid dynamics (CFD)
calculations (using the entry environment and trajectory for a Mars 03
entry vehicle) were performed for a generic torroidal-shaped ballute,
attached to a baseline S/C configuration. Results from the CFD analysis
indicate a maximum heating intensity of 35 W/cm2 occurred at
the aeroshell-ballute joint interface. A thermal model was developed,
incoporating the CFD results, which was used to design a tailored
thermal protection system (TPS). The TPS consisted of a multilayered
configuration for the higher heat flux area and a fewer-layer
configuration for areas with lower heat flux. The total mass of the
tailored TPS for the entire ballute surface was about 43% lighter than a
more traditional monolithic heat shield design. Lockheed Martin, along
with L'Garde, Inc., designed and fabricated a subscale model of an
inflatable ballute attached to a rigid aeroshell, to demonstrate ballute
bladder stowage and inflation mechanics
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