Resolved CN Band Profile of Stardust Capsule Radiation at Peak Heating

Jenniskens, Peter; Wilson, Michael; Winter, Michael; Laux, Christophe O.

doi:10.2514/1.38074

Cited by 17 publications

(6 citation statements)

References 7 publications

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“…7 Incidentally, the presence of calcium in the fibers may explain why calcium spectra had been observed by emission spectroscopy in the trail of Stardust during its re-entry. 12 High-temperature treatment is known to remove impurities from carbon fibers and decrease their oxidation rate. 7 The open question is: should FiberForm be treated at high-temperature to remove possible catalysts and improve its moderate-temperature oxidation properties?…”

Section: Ivb Comments and Open Questionmentioning

confidence: 99%

Validation of a volume-averaged fiber-scale model for the oxidation of a carbon-fiber preform

Lachaud

Mansour

Ceballos

et al. 2011

42nd AIAA Thermophysics Conference

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The oxidation of FiberForm, an industrial carbon-fiber preform, has been studied in an oxidation reactor. The microscopic oxidation behavior of the fibers has been analyzed by scanning electron microscopy. The carbon fibers ablate showing progressive reduction of their diameter. The overall material recession occurs when the fibers are consumed. A reaction/diffusion-convection competition is shown to drive the oxidation process and control the depth of oxidation. A fiber-scale model is proposed for the prediction of carbonfiber preform oxidation. A macroscopic model is derived by volume-averaging the microscopic model and a porous-medium formulation is used to model mass transport in the preform. The proposed model has been implemented in a Carbon Oxidation Analysis Code based on OpenFOAM (COACO). Using inverse analysis, it was possible to estimate the intrinsic fiber reactivity and then validate the model. The reactivity obtained is surprisingly high compared to literature data. This is explained by the fact that the carbon fibers contain traces of calcium and potassium, which are known to be catalysts for oxidation. They progressively accumulate at the surface in the form of combustion residues. NomenclatureMean pore diameter f Rarefaction function J Molar oxidation flux, mol · m −2 · s −1 k f Reactivity constant, m · s −1 n Surface normal, m P ePéclet number r f Fiber radius, m SSurface function s f Fiber-preform specific surface, m 2 · m −3 V Averaging volume, m 3 vRecession velocity, m · s −1

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Section: Ivb Comments and Open Questionmentioning

confidence: 99%

Validation of a volume-averaged fiber-scale model for the oxidation of a carbon-fiber preform

Lachaud

Mansour

Ceballos

et al. 2011

42nd AIAA Thermophysics Conference

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“…The data were analyzed to reveal quantities of importance to atmospheric reentry aerothermodynamics: apparent temperatures, shock radiation spectra from high temperature gases, ablation species spectra (if present), and their temporal evolution during reentry. The first successful collaboration was for NASA's Stardust in 2006 [48][49][50][51][52][53][54][55][56][57][58][59][60] followed by JAXA's Hayabusa in 2010 [61,62]. These reentry observation campaigns used aerial based imaging systems.…”

Section: Emission Spectroscopy Imaging (Entry Vehicles)mentioning

confidence: 99%

“…The instrument was designed to capture emission from N2+ and CN at high resolution. When correlated to the reconstructed trajectory, these altitude-resolved measurements indicate the relative variations of shock radiation and ablation processes during reentry [48][49][50][51][52][53][54][55][56][57][58][59][60].…”

Section: Emission Spectroscopy Imaging (Entry Vehicles)mentioning

confidence: 99%

Remote observations of reentering spacecraft including the space shuttle orbiter

Horvath

Cagle

Grinstead

et al. 2013

2013 IEEE Aerospace Conference

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Abstract-Flight measurement is a critical phase in development, validation and certification processes of technologies destined for future civilian and military operational capabilities. This paper focuses on several recent NASA-sponsored remote observations that have provided unique engineering and scientific insights of reentry vehicle flight phenomenology and performance that could not necessarily be obtained with more traditional instrumentation methods such as onboard discrete surface sensors. The missions highlighted include multiple spatially-resolved infrared observations of the NASA Space Shuttle Orbiter during hypersonic reentry from 2009 to 2011, and emission spectroscopy of comparatively small-sized sample return capsules returning from exploration missions. Emphasis has been placed upon identifying the challenges associated with these remote sensing missions with focus on end-to-end aspects that include the initial science objective, selection of the appropriate imaging platform and instrumentation suite, target flight path analysis and acquisition strategy, pre-mission simulations to optimize sensor configuration, logistics and communications during the actual observation. Explored are collaborative opportunities and technology investments required to develop a next-generation quantitative imaging system (i.e., an intelligent sensor and platform) with greater capability, which could more affordably support cross cutting civilian and military flight test needs.

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“…Lower resolution near-UV data was obtained for about 30 s around the time of peak heating using intensified video-rate devices down to wavelengths around 320 nm in the case of the work by Rairden and Jenniskens, 8 and down to about 380 nm in the case of the work by Jenniskens et al 9 The ∆ν = 0 CN manifold was very well resolved by the upward-looking device of Jenniskens et al 10 but only around the time of peak heating.…”

Section: Introductionmentioning

confidence: 99%

Near Ultraviolet Emission Spectroscopy of the Hayabusa Re-entry

Buttswoth

Morgan

Jenniskens

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Quantitative time-resolved irradiance measurements were obtained of the Hayabusa Sample Return Capsule's entry on June 13, 2010, as measured from 12.6 km altitude with the Australian Ultraviolet Spectrograph instrument on board NASA's DC-8 Airborne Laboratory, which was stationed just outside of the landing site at the Woomera Test Range in Australia. The measurements were calibrated against NIST traceable standard calibration lamps on the tarmac at NASA Dryden Aircraft Operations Facility and at NASA Ames Research Center. The recorded spectra cover the wavelength range from 300 to 470 nm over the duration from 13:52:02.5 until 13:52:33.5 UTC. The spectra show shock emission from N + 2 , as well as several ablation products from the heat shield material (CN, Ca, and Al).In addition, the high-temperature tail of gray-body emission is observed to enter the wavelength range after 13:52:13 UTC. These data were evaluated in terms of the temporal evolution of the capsule's stagnation temperature and emissions within the CN and N + 2 manifolds. A peak in the irradiance within the wavelength band from 365 to 392 nm was registered at approxi-

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Resolved CN Band Profile of Stardust Capsule Radiation at Peak Heating

Cited by 17 publications

References 7 publications

Validation of a volume-averaged fiber-scale model for the oxidation of a carbon-fiber preform

Validation of a volume-averaged fiber-scale model for the oxidation of a carbon-fiber preform

Remote observations of reentering spacecraft including the space shuttle orbiter

Near Ultraviolet Emission Spectroscopy of the Hayabusa Re-entry

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