Thermal, Structural, and Inflation Modeling of an Isotensoid Supersonic Inflatable Aerodynamic Decelerator

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IEEE-2011-1312.pdf (5.56 MB)
Author(s)
Smith, Brandon P.
Clark, Ian G.
Braun, Robert D.
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Daniel Guggenheim School of Aerospace Engineering
The Daniel Guggenheim School of Aeronautics was established in 1931, with a name change in 1962 to the School of Aerospace Engineering
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https://hdl.handle.net/1853/74120
Abstract
Near-term missions to Mars may not be possible with current deployable decelerator technology. This possibility becomes a certainty for the more distant human precursor missions. Inflatable Aerodynamic Decelerators (IADs) are a candidate technology that may provide the needed drag augmentation to enable these much heavier missions. The attached isotensoid is one of the IAD configurations favored for application at Mars. Assessing the isotensoid’s technical feasibility for Mars missions requires several performance models capable of providing reasonably accurate predictions of key design parameters. This paper describes engineering-level models derived from past isotensoid technology development efforts that have been modified or improved for the problem at hand. Easily implemented models of the isotensoid inflation history, aerothermodynamic environment, and thermostructural performance are described.1 2 Engineering models are presented for estimating internal pressure and drag during inflation, aerothermal heating on the fabric, stresses throughout the structure, and in-depth fabric temperatures. The models are applied to a reference mission similar to the Mars Science Laboratory (MSL) employing a Supersonic IAD (SIAD) at Mach 5. Thermostructural analysis is presented to show a method for selecting suitable materials capable of performing in the predicted aerothermal environment under the predicted load. The inflation model is validated with empirical data from Viking-era ground tests. Aerothermal analysis shows that a peak convective heat rate of 1.25 W/cm2 can be expected across the isotensoid fabric. Stresses are computed for minimum gauge materials, and the transient temperature response of the fabric and thermal coating is computed. Nomex, Kevlar, and Vectran materials are considered. Material tenacity retention at elevated temperatures is considered. Vectran is recommended for the isotensoid fabric due to its adequate thermostructural performance, favorable abrasive properties, and flight heritage as an inflatable structure.
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2011-03
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