ESA Ablative Radiation Project

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FIRST RESULTS ON ABLATION RADIATION COUPLING THROUGH OPTICAL EMISSION SPECTROSCOPY FROM THE VACUUM ULTRAVIOLET TO THE VISIBLE Tobias Hermann1 , Stefan L¨ohle1 , P´en´elope Leyland2 , Lionel Marraffa3 , Jean-Marc Bouilly4 , and Stefanos Fasoulas5 1

High Enthalpy Flow Diagnostics Group, Institute of Space Systems (IRS), University of Stuttgart, Stuttgart, Germany 2 Ecole Polytechnique F´ed´erale de Lausanne, Interdisciplinary Aerodynamics Group 3 ESA/ESTEC, Aerothermodynamics Section 4 Astrium SAS 5 Institute of Space Systems (IRS), University of Stuttgart, Stuttgart, Germany

ABSTRACT

Plasma wind tunnel experiments simulating a Hayabusa re-entry trajectory point at 78.8 km with a local mass– specific enthalpy of 68.4 MJ/kg and a stagnation pressure of 24.4 hPa have been performed. Three materials, a carbon preform, a lightweight carbon phenolic ablator and cooled copper, have been tested in order to investigate radiation and ablation and its interaction. Optical emission spectroscopic measurements in the vacuum ultraviolet (VUV) regime (116–197 nm) have been conducted through a bore hole in the stagnation point of the material samples. Optical emission spectroscopic measurements in the UV/VIS spectral range (320–810 nm) have been conducted viewing the plasma from the side 5 mm in front of the sample surface. The radiation transport to the boundary layer has been analysed from these measurements combined with theoretical modeling. The resulting radiation heat flux to the surface has been compared: The stagnation point VUV radiation for the carbon sample is 1.81 times stronger compared to copper. For the carbon phenolic material the stagnation VUV radiation is over a magnitude weaker compared to copper. In the UV/VIS however both carbon based material samples exhibit stronger radiation than copper. On the stagnation streamline molecular rotational and vibrational temperatures are lower for both the carbon based materials compared to copper while the electronic excitation temperature increases slightly in front of a carbon based material. Atom number densities are largest for the carbon preform sample and lowest for the phenolic carbon sample. In conclusion there is a strong coupling of ablation and radiation surface heat flux. The measurements using the real ablation material, i.e. carbon phenolic, appear to perform best in this test campaign with respect to radiative heat flux mitigation.

Key words: Vacuum ultraviolet spectroscopy, plasma wind tunnel, re-entry, Boltzmann plot, ablation, radiation.

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INTRODUCTION

Re-entry vehicles entering the earth atmosphere on hyperbolic trajectories are exposed to very high thermal loads, a convective and a radiative component. As the reentry speed increases, the radiative part of the heat flux becomes more and more dominant [LHM12, GJC+ 11, Gno99]. In order to protect the vehicle from these thermal loads, ablative heat shields are used. Within the flow field, energy transfer is conducted by radiative transport in addition to convective and diffusive mechanisms [And06]. The introduction of carbonaceous and phenolic species originating from the ablative heat shield can have an effect on all energy transport mechanisms [Gup00, RRM72, HL67, JGM13].For high radiative heat fluxes the coupling of ablation and radiation needs to be investigated in order to set useful design margins. New radiating species are introduced, e. g. atomic carbon and cyanogen (CN) increasing the radiative heat flux. However, these species originating from the heat shield can act also as strong absorbers thus reducing the radiative heat flux. Absorbed radiation is either re-emitted or transported downstream becoming an additional convective heat flux to the wall [NPBM08]. Both increase and decrease in radiative heating through ablation have been reported in numerical analyses [Gup00, Par07, JGS09]. In terms of total radiative heat flux encountered by the vehicle the vacuum ultraviolet (VUV) regime, i. e. 100–200 nm, is considered the main source [NPBM08, JMG+ 11, Par04, LWM+ 09, PAI98, JGM13]. However, experimental investigations of this wavelength regime are sparse [CMGO09, McC72, SMZ+ 12, WHAW69, Sut84, PCWP97]. Considering the fact that ablation-radiation coupling is still not sufficiently understood, the need for experimental data on the subject is clear. In this study the ablation and radiation processes have been investigated in a plasma wind tunnel since they provide steady-state high enthalpy flow environments representative of re-entry flows [LBHP12, AKKL96, AKW99, DHAK94, LAKW+ 98]. Several material sample tests


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