Design and Execution of the Hypersonic Inflatable Aerodynamic Decelerator Large-Article Wind Tunnel Experiment

Cassell, Alan M.; Swanson, Gregory T.; Quach, Bill; Kushner, Laura K.; Brown, Jeffrey D.; Kazemba, Cole; Kruger, Carl; Johnson, R. Keith; Hughes, Stephen J.; Littell, Justin D.; Calomino, Anthony M.; Cheatwood, F. McNeil

doi:10.2514/6.2013-1304

Cited by 15 publications

(10 citation statements)

References 6 publications

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“…NASA's HIAD technology development project recently tested a 6-m stacked-torus inflatable article. Multiple aerodynamic wind-tunnel and static pressure load tests [6][7][8] were conducted to characterize the inflatable structure response under relevant mission loading. Accurate prediction of the structural response of the HIAD inflatable structure under aerothermal and mechanical loads presents a challenge in the presence of uncertainties associated with the complex high-fidelity models.…”

Section: Dmentioning

confidence: 99%

“…The Kevlar webbing straps distribute flight loads from torus to torus and to the centerbody. The network of straps include 4000-lb (4-K) load radial and centerbody attachment straps attached to T5 and 3000-lb (3-K) load pairing and chevron straps attached to T6 and T7 [6,7]. Figure 3 depicts the strap and Technora axial cord components.…”

Section: B Baseline Reference Geometry and Freestream Conditionsmentioning

confidence: 99%

“…6 [18]. The adapted grid is derived from an initial grid that was used for NFAC wind-tunnel test cases [6,7]. The HIAD in this grid has a cylindrical centerbody, which represents the sting attachment.…”

Section: Baseline Reference Case For Lifting Entrymentioning

confidence: 99%

“…The HIAD in this grid has a cylindrical centerbody, which represents the sting attachment. The length of the centerbody is equivalent to the length of the sting attachment from NFAC windtunnel testing [6,7]. A flight HIAD would have a rigid centerbody that might be similar in diameter to the sting.…”

Section: Baseline Reference Case For Lifting Entrymentioning

confidence: 99%

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Uncertainty Analysis of Fluid-Structure Interaction of a Deformable Hypersonic Inflatable Aerodynamic Decelerator

Brune

Hosder

Edquist

2016

Journal of Spacecraft and Rockets

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The objective of this paper is to present the results of a detailed uncertainty analysis for high-fidelity fluid-structure interaction modeling of a deformable hypersonic inflatable aerodynamic decelerator at peak heating conditions for lifting Mars entry with a turbulent flow assumption. Uncertainty results are presented for the structural deformation response and surface conditions (pressure, shear stress, and convective heat transfer) of the inflatable decelerator with an efficient polynomial chaos expansion approach. The uncertainty results are compared with results obtained in a previous study for ballistic Mars entry. Approximately half of the flowfield and structural modeling uncertainties show at least 90% combined contribution to the inflatable decelerator deflection and resulting surface condition uncertainties. For lifting Mars entry, global nonlinear sensitivity analysis shows that the tensile stiffness of the inflatable structure's axial cords and radial straps and the torus torsional and tensile stiffnesses are the main contributors to the inflatable decelerator deflection uncertainty. As a result of these structural uncertainty contributions, the shape deformation contributes up to 10% of the uncertainty in the surface conditions. However, the freestream density dominates the uncertainty in the surface conditions experienced by the inflatable decelerator. In addition, the CO 2 −CO 2 binary collision interaction is a significant contributor to aerodynamic heating and shear stress uncertainty. Nomenclature= lift-to-drag ratio N s = number of samples N t = number of terms in a total-order polynomial chaos expansion n = number of random dimensions P = surface pressure, Pa p = order of polynomial expansion q = dynamic pressure, Pa Re = Reynolds number per unit length, /m S e = percent absolute error S T = total Sobol index T = static temperature, K V = velocity, m∕s x = deterministic variable vector α = deterministic coefficient in the polynomial chaos expansion α = generic uncertain response function β = ballistic coefficient, kg=m 2 γ FPA;i = initial entry flight path angle, deg δ = truncation error or deflection angle, deg μ e = mean error ξ = standard input random variable ρ = static density, kg=m 3 Ψ = random basis function Ω 1;1 = diffusion collision integral Ω 2;2 = viscosity collision integral ∞ = freestream condition

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Section: Dmentioning

confidence: 99%

Section: B Baseline Reference Geometry and Freestream Conditionsmentioning

confidence: 99%

Section: Baseline Reference Case For Lifting Entrymentioning

confidence: 99%

Section: Baseline Reference Case For Lifting Entrymentioning

confidence: 99%

See 2 more Smart Citations

Uncertainty Analysis of Fluid-Structure Interaction of a Deformable Hypersonic Inflatable Aerodynamic Decelerator

Brune

Hosder

Edquist

2016

Journal of Spacecraft and Rockets

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show abstract

“…This unique material is a self-assembled free-standing electrically conductive elastomer that can be used on a high stretch substrate or as a coating on other materials. 6 The Metal Rubber™ material can be cut into sensor shapes and has been used in multiple applications for structural strain sensing, including on high-tension Kevlar straps of NASAs Hypersonic Inflatable Aerodynamic Decelerator (HIAD), 1 and on small diameter Zilon cords on NASAs Ultra-Long Duration Scientific Balloons. 3 These tests have shown that the Metal Rubber sensor has high-strain capabilities and a unique ability to be sized for a specific application and loading regime.…”

Section: B Instrumentation Optionsmentioning

confidence: 99%