Aerodynamic and Aeroelastic Characteristics of a Tension Cone Inflatable Aerodynamic Decelerator
Author(s)
Clark, Ian G.
Cruz, Juan R.
Hughes, Monica F.
Ware, Joanne S.
Madlangbayan, Albert
Braun, Robert D.
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Abstract
The supersonic aerodynamic and aeroelastic characteristics of a tension cone inflatable
aerodynamic decelerator were investigated by wind tunnel testing. Two sets of tests were
conducted: one using rigid models and another using textile models. Tests using rigid
models were conducted over a Mach number range from 1.65 to 4.5 at angles of attack from
-12 to 20 degrees. The axial, normal, and pitching moment coefficients were found to be
insensitive to Mach number over the tested range. The axial force coefficient was nearly
constant (C^A = 1.45 +/- 0.05) with respect to angle of attack. Both the normal and pitching
moment coefficients were nearly linear with respect to angle of attack. The pitching moment
coefficient showed the model to be statically stable about the reference point. Schlieren
images and video showed a detached bow shock with no evidence of large regions of
separated flow and/or embedded shocks at all Mach numbers investigated. Qualitatively
similar static aerodynamic coefficient and flow visualization results were obtained using
textile models at a Mach number of 2.5. Using inflatable textile models the torus pressure
required to maintain the model in the fully-inflated configuration was determined. This
pressure was found to be sensitive to details in the structural configuration of the inflatable
models. Additional tests included surface pressure measurements on rigid models and
deployment and inflation tests with inflatable models.
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Date
2009-05
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