Mass Model Development for Conceptual Design of a Hypersonic Rigid Deployable Decelerator
Author(s)
Cruz-Ayoroa, Juan G.
Kazemba, Cole D.
Steinfeldt, Bradley A.
Kelly, Jenny R.
Clark, Ian G.
Braun, Robert D.
Advisor(s)
Editor(s)
Collections
Supplementary to:
Permanent Link
Abstract
As the required payload masses for planetary
entry systems increase, innovative entry vehicle
decelerator systems are becoming a topic of
interest. With this interest comes a growing need
for the capability to characterize the performance
of such decelerators. This work proposes a first-order
mass model for fully-rigid deployable
decelerator systems. The analytical methodology
that is presented can be applied to a wide range of
entry conditions and material properties for rapid
design space exploration. The tool is applied to a
case study of a C/SiC hot structure decelerator at
Mars for comparison to the performance of the
Hypersonic Inflatable Aerodynamic Decelerator
concepts presented in a recent EDL-SA study.
Results show that the performance of a rigid
deployable structure can be comparable to that of
a Hypersonic Inflatable Aerodynamic Decelerator
at high entry ballistic coefficients and small
decelerator diameters.
Sponsor
Date
2012-06
Extent
Resource Type
Text
Resource Subtype
Paper
Rights Statement
Unless otherwise noted, all materials are protected under U.S. Copyright Law and all rights are reserved