Post-Flight Evaluation of Stardust Sample Return Capsule Forebody Heatshield Material

Stackpoole, Mairead; Sepka, Steve; Cozmuta, Ioana; Kontinos, Dean

doi:10.2514/6.2008-1202

Cited by 74 publications

(57 citation statements)

References 3 publications

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“…Postflight analysis determined surface temperature and recession. The observed data suggested that the previous Stardust models were inaccurate; recession was overpredicted by 50% at some locations on the capsule [14].…”

Section: A Stardust Return Capsulementioning

confidence: 88%

Significance of Nonequilibrium Surface Interactions in Stardust Return Capsule Ablation Modeling

Beerman

Lewis

Starkey

et al. 2009

Journal of Thermophysics and Heat Transfer

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The gas-surface modeling of high-density materials exposed to high-pressure atmospheric reentry conditions was extended to include low-density materials interacting with low-pressure atmospheric conditions. The fully implicit ablation thermal response code and multicomponent ablation thermochemistry program were extended to include nonequilibrium surface conditions for the Stardust return capsule. The Stardust return capsule reentered Earth's atmosphere experiencing low pressure and had a low-density heat shield material. The material response of the Stardust return capsule was previously only modeled with surface equilibrium. Validation against Stardust reentry flight data showed that the equilibrium assumption led to an overprediction of recession and that the inclusion of nonequilibrium reduced the overprediction of this parameter. Incorporating the Park finite rate model nonequilibrium surface conditions led to a reduction in the calculated value of recession at the stagnation point from 1.12 to 0.72 cm in a nominal simulation of the Stardust return capsule. The nonequilibrium recession was closer to the measured recession of 0.65 cm. Incorporating nonequilibrium conditions also decreased the calculated total heat load from 28 to 19 kJ=cm 2 . The improved material response method is applicable to a range of reentries, including future missions such as the Orion crew exploration vehicle. NomenclatureB = preexponential factor, s 1 B 0 = dimensionless mass blowing rate, _ m= e u e C M C H = Stanton number for heat transfer C i = mass fraction for species i C M = Stanton number for mass transfer c p = specific heat, J=kg-K D i = diffusion coefficient for species i, m 2 =s E = activation temperature, K F = view factor H r = recovery enthalpy, J=kg h = enthalpy, J=kg h = partial heat of charring, J=kg k = Boltzmann constant, J=K M = molecular weight, kg=mole m = mass, kg _ m = mass flux, kg=m 2 s p = pressure, N=m 2 q c = conductive heat flux, W=m 2 q rad = radiative heat flux, W=m 2 T = temperature, K u = velocity, m=s v w = mass injection velocity, m=s x = moving coordinate system, y s, m Y = element mass fraction y = stationary coordinate, m = surface absorption = efficiency of gas-surface interaction = volume faction of resin " = surface emissivity = blowing reduction parameter = density, kg=m 3 = Stefan-Boltzmann constant, W=m 2 K 4 = decomposition reaction order Subscripts c = char d = density component e = boundary-layer edge g = pyrolysis gas i = surface species k = element or gaseous base species s = surface v = original w = wall

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Section: A Stardust Return Capsulementioning

confidence: 88%

Significance of Nonequilibrium Surface Interactions in Stardust Return Capsule Ablation Modeling

Beerman

Lewis

Starkey

et al. 2009

Journal of Thermophysics and Heat Transfer

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“…6 FIAT has been used in numerous TPS design and analysis activities since its development which most recently includes Stardust, Mars Science Laboratory, and Orion. [7][8][9] Blackwell, Hogan, and Cochran introduced the use of the control volume finite element method (CVFEM) and linear elastic mesh motion to solve one and two dimensional ablation problems. [10][11][12] Ahn and Suzuki et.…”

Section: Introductionmentioning

confidence: 99%

Development and Verification of the Charring Ablating Thermal Protection Implicit System Solver

Amar

Calvert

Kirk

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The development and verification of the Charring Ablating Thermal Protection Implicit System Solver is presented. This work concentrates on the derivation and verification of the stationary grid terms in the equations that govern three-dimensional heat and mass transfer for charring thermal protection systems including pyrolysis gas flow through the porous char layer. The governing equations are discretized according to the Galerkin finite element method with first and second order implicit time integrators. The governing equations are fully coupled and are solved in parallel via Newton's method, while the fully implicit linear system is solved with the Generalized Minimal Residual method. Verification results from exact solutions and the Method of Manufactured Solutions are presented to show spatial and temporal orders of accuracy as well as nonlinear convergence rates.

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“…Post-flight evaluation of the Stardust capsules forebody heat shield [1] as well as statistical modelling of TPS material microstructure [2] have recently confirmed the volumetric nature of ablation. In-depth oxidation leaves the carbon preform exposed to its extreme operating environment, where radiation becomes a significant (and eventually, dominant) mode of heat transfer [3].…”

Section: Introductionmentioning

confidence: 85%

“…The quasi-steady homogenised RTEs for a multi-phase medium comprising of two semi-transparent phases are given by Equation (1), where the spectral subscript has been omitted for brevity. This set of equations is derived from the discrete-scale RTEs valid in the individual phases and the corresponding inter-phase boundary conditions [14].…”

Section: Governing Equations and Implementationmentioning

confidence: 99%

Tomography-based radiative characterisation of decomposing carbonaceous heat shield materials

Banerji

Leyland

Haussener

2017

Carbon

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a b s t r a c tThis work evaluates the changes in radiative properties of two decomposing carbonaceous porous materials, each composed of two semi-transparent, homogeneous and isotropic phases. The understanding of the complex dependence of macroscopic optical behaviour on material microstructure, bulk phase properties and the wavelength of incoming radiation is paramount for modelling, design and optimisation of systems incorporating such media. Experimental and numerical techniques were combined to solve the homogenised radiative transfer equations using Monte Carlo ray tracing in the limit of geometrical optics. Effective radiative properties required by these equations were determined by Monte Carlo techniques using the exact 3D microstructures of the samples, obtained through high-resolution synchrotron computed tomography. This methodology is applied to a medium density carbon phenolic and a high density graphite reinforced polymer composite, each composed of semi-transparent solid and fluid phases. The extent of material decomposition is seen to affect the absorption behaviour of both samples. This effect is more obvious in the lower density carbon phenolic, where an 18% increase in absorptance is observed due to decomposition, compared to an increase of just 2% for the graphite. A library of absorption data is presented for use in continuum heat transfer modelling of similar chemically reacting macroporous carbon composites.

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Post-Flight Evaluation of Stardust Sample Return Capsule Forebody Heatshield Material

Cited by 74 publications

References 3 publications

Significance of Nonequilibrium Surface Interactions in Stardust Return Capsule Ablation Modeling

Significance of Nonequilibrium Surface Interactions in Stardust Return Capsule Ablation Modeling

Development and Verification of the Charring Ablating Thermal Protection Implicit System Solver

Tomography-based radiative characterisation of decomposing carbonaceous heat shield materials

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