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Plasma preheating technology for replicating planetary re-entry surface temperatures

Published online by Cambridge University Press:  19 August 2021

D.O. Iyinomen Open the ORCID record for D.O. Iyinomen [Opens in a new window]
D.O. Iyinomen*
Affiliation:
Mechanical and Aerospace Engineering, Aerospace Research and Innovations
*
E-mail: iyidaniel@yahoo.co.uk
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Abstract

Arc-jet facilities have been the norm for ablation experiments used to calibrate computational models to date. However, the arc jet has a few major limitations and challenges, including non-uniform enthalpy distribution, non-equilibrium state, change of surface quality during testing and the extent of oxidation, to name but a few. A novel plasma technique for preheating axisymmetric heatshield samples in hypersonic impulse facilities is presented herein. The major aim of this innovative work is to help reduce the large variations of ablation rate predictions, space vehicle materials and missile design/testing, obtain strongly coupled hypersonic boundary layers and achieve lower cost of aerothermodynamics experiments. This present work remains one of the most highly anticipated solutions to maximise payload success and replicate high surface temperatures identical to those experienced by real flight vehicles. This work makes a useful contribution to re-entry studies under conditions that replicate the characteristics of re-entry flights. Future applications for the technique are expected to be found in hypersonic impulse facilities that can simulate the true flow energy under re-entry conditions.

Keywords

HeatshieldPlasmaPreheatingInvestigatingAblation modelsHypersonicImpulse facilitiesPlanetaryRe-entrySurface temperatures
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1296 , February 2022 , pp. 297 - 315
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Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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References

Schneider, S.P. Laminar-turbulent transition on reentry capsules and planetary probes. J. Spacecraft Rockets, 2006, 43, (6), pp 1153–1173.CrossRefGoogle Scholar
Liechty, D., Hollis, B. and Edquist, K. Control Surface and Afterbody Experimental Aeroheating for a Proposed Mars Smart Lander Aeroshell. In AIAA Atmospheric Flight Mechanics Conference and Exhibit (p. 4506), 2002.Google Scholar
Edquist, K.T., Liechty, D.S., Hollis, B.R., Alter, S.J. and Loomis, M.P. Aeroheating environments for a Mars smart lander. J. Spacecraft Rockets, 2006, 43, (2), pp 330–339.CrossRefGoogle Scholar
Wang, Z.H., Yu, Y.L. and Bao, L. Heat transfer in nonequilibrium flows with homogeneous and heterogeneous recombination reactions. AIAA J., 2018, 56, (9), pp 3593–3599.CrossRefGoogle Scholar
Gülhan, A., Esser, B., Koch, U., Fischer, M., Magens, E. and Hannemann, V. Characterization of high-enthalpy-flow environment for ablation material tests using advanced diagnostics. AIAA J., 2018, 56, (3), pp 1072–1084.CrossRefGoogle Scholar
Riccio, A., Raimondo, F., Sellitto, A., Carandente, V., Scigliano, R. and Tescione, D. Optimum design of ablative thermal protection systems for atmospheric entry vehicles. Appl. Therm. Eng., 2017, 119, pp 541–552.CrossRefGoogle Scholar
Gnoffo, P.A. Planetary-entry gas dynamics. Annu. Rev. Fluid Mech., 1999, 31, (1), pp 459–494.CrossRefGoogle Scholar
Collicott, H.E. and Bauer, P.E. Entry Vehicle Heating and Thermal Protection Systems: Space Shuttle, Solar Starprobe, Jupiter Galileo Probe, American Institute of Aeronautics and Astronautics, 1983.Google Scholar
Wang, Z.H., Yu, Y.L. and Bao, L. Heat transfer in nonequilibrium flows with homogeneous and heterogeneous recombination reactions. AIAA J., 2018, 56, (9), pp 3593–3599.CrossRefGoogle Scholar
Gülhan, A., Esser, B., Koch, U., Fischer, M., Magens, E. and Hannemann, V. Characterization of high-enthalpy-flow environment for ablation material tests using advanced diagnostics. AIAA J., 2018, 56, (3), pp 1072–1084.CrossRefGoogle Scholar
Mortensen, C.H. and Zhong, X. Real-gas and surface-ablation effects on hypersonic boundary-layer instability over a blunt cone. AIAA J., 2016, 54, (3), pp 980–998.CrossRefGoogle Scholar
Poovathingal, S., Schwartzentruber, T.E., Murray, V.J. and Minton, T.K. Molecular simulation of carbon ablation using beam experiments and resolved microstructure. AIAA J., 2016, 54, (3), pp 999–1010.CrossRefGoogle Scholar
Lei, L., Guangyue, D., Lei, Z., Zhenfeng, W. and Yewei, G. Experimental model design and preliminary numerical verification of fluid–thermal–structural coupling problem. AIAA J., 2019, 57, (4), pp 1715–1724.CrossRefGoogle Scholar
Sagnier, P. and Verant, J.L. Flow characterization in the ONERA F4 high-enthalpy wind tunnel. AIAA J., 1998, 36, (4), pp 522–531.CrossRefGoogle Scholar
Horvath, T.J., Berry, S.A. and Merski, N.R. Hypersonic boundary/shear layer transition for blunt to slender configurations-A NASA Langley experimental perspective, National Aeronautics and Space Administration Hampton Va Langley Research Centre, 2004.Google Scholar
Sheikh, U.A., Morgan, R.G. and McIntyre, T.J. Vacuum ultraviolet spectral measurements for superorbital earth entry in X2 expansion tube. AIAA J., 2015, 53, (12), pp 3589–3602.CrossRefGoogle Scholar
Davies, C. and Arcadi, M., 2006. Planetary mission entry vehicles quick reference guide. Version 3.0.Google Scholar
Hollis, B.R. and Borrelli, S. Aerothermodynamics of blunt body entry vehicles. Prog. Aerosp. Sci., 2012, 48, pp 42–56.CrossRefGoogle Scholar
Jiang, Z., Hu, Z., Wang, Y. and Han, G. Advances in critical technologies for hypersonic and high-enthalpy wind tunnel. Chin. J. Aeronaut., 2020, 33, (12), pp 3027–3038.CrossRefGoogle Scholar
Bugel, M., Reynier, P. and Smith, A. Survey of European and major ISC facilities for supporting Mars and sample return mission aerothermodynamics and tests required for thermal protection system and dynamic stability. Int. J. Aerosp. Eng., 2011, 2011. doi: 10.1155/2011/937629.CrossRefGoogle Scholar
Allen, H.J. Some problems of planetary atmosphere entry. Aeronaut. J., 1967, 71, (684), pp 813–820.CrossRefGoogle Scholar
Ostrom, C., Greene, B., Smith, A., Toledo-Burdett, R., Matney, M., Opiela, J., Marichalar, J., Bacon, J. and Sanchez, C., 2019. Operational and Technical Updates to the Object Reentry Survival Analysis Tool.Google Scholar
Asma, C.O., Tirtey, S. and Schloegel, F. Flow topology around gas, liquid and three-dimensional obstacles in hypersonic flow. AIAA J, 2012, 50, (1), pp 100–108.CrossRefGoogle Scholar
Glass, D. (2008), Ceramic matrix composite (CMC) thermal protection systems (TPS) and hot structures for hypersonic vehicles, in ‘15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference‘, pp 2682-2718.CrossRefGoogle Scholar
Dec, J. and Braun, R. (2006), An approximate ablative thermal protection system sizing tool for entry system design, in ‘44th AIAA Aerospace Sciences Meeting and Exhibit‘, pp 780-794.CrossRefGoogle Scholar
Iyinomen, D.O. Numerical and experimental analyses of ablation measurements in expansion wind tunnel facilities using a new plasma pre-heating technique. Int. J. Thermofluids, 2020, 3, p 100019.CrossRefGoogle Scholar
Iyinomen, D.O. Numerical approach to ablation measurements using a new plasma pre-heating technique. Int. J. Thermofluids, 2020, 1, p 100014.CrossRefGoogle Scholar
Iyinomen, DO, Malpress, R and Buttsworth, D., Technique development for investigating axisymmetric ablation models in hypersonic impulse facilities. AIAA J., 2021, 59(6), pp 1899–1913. doi: 10.2514/1.J059629.CrossRefGoogle Scholar
Iyinomen, D.O. Technique development for investigation of axisymmetric graphite sample oxidation in hypersonic flow (Doctoral dissertation Institute for Advanced Engineering and Space Sciences, University of Southern Queensland), 2019.Google Scholar
Chazot, O. Experimental studies on hypersonic stagnation point chemical environment, Technical report, Von Karman Institute for Fluid Dynamics Rhode-Saint-Genese (Belgium), 2006.Google Scholar
Loehle, S., Fasoulas, S., Herdrich, G.H., Hermann, T.A., Massuti-Ballester, B., Meindl, A., Pagan, A.S. and Zander, F., 2016. The plasma wind tunnels at the institute of space systems: current status and challenges. In 32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference (p. 3201).CrossRefGoogle Scholar
Moradi, M., Ghoreishi, M. and Khorram, A., 2018. Process and Outcome Comparison Between Laser, Tungsten Inert Gas (TIG) and Laser-TIG Hybrid Welding. Lasers in Engineering (Old City Publishing), 39.Google Scholar
Wang, X., Luo, Y. and Fan, D. Investigation of heat transfer and fluid flow in high current GTA welding by a unified model. Int. J. Therm. Sci., 2019, 142, pp 20–29.CrossRefGoogle Scholar
Traidia, A. (2011), Multi-physics modelling and numerical simulation of GTA weld pools, PhD thesis, Ecole Polytechnique.Google Scholar
Siewert, E., Baeva, M. and Uhrlandt, D. The electric field and voltage of dc tungsten-inert gas arcs and their role in the bidirectional plasma-electrode interaction. J. Phys. D Appl. Phys., 2019, 52, (32), p 324006.CrossRefGoogle Scholar
Anand, K.R. and Mittal, V. Review on the parametric optimization of tig welding. Int. Res. J. Eng. Technol. (IRJET), 2017, 2017(4), pp e-ISSN: 2395-0056, p-ISSN: 2395-0072.Google Scholar
Fadda, G., Colombo, L. and Zanzotto, G. First-principles study of the structural and elastic properties of zirconia. Phys. Rev. B, 2009, 79, (21), p 214102.CrossRefGoogle Scholar
Ishigame, M. and Sakurai, T. Temperature dependence of the Raman spectra of ZrO2. J. Am. Ceram. Soc., 1977, 60, (7-8), pp 367–369.CrossRefGoogle Scholar
Xiang, M., Song, M., Zhu, Q., Hu, C., Yang, Y., Lv, P., Zhao, H. and Yun, F. Facile synthesis of high-melting point spherical TiC and TiN powders at low temperature. J. Am. Ceram. Soc., 2020, 103, (2), pp 889–898.CrossRefGoogle Scholar
Shackelford, J.F. and Alexander, W. CRC materials science and engineering handbook, Boca Raton, FL: CRC press, 2000.CrossRefGoogle Scholar
Lachaud, J., Aspa, Y. and Vignoles, G.L. Analytical modelling of the steady state ablation of a 3D C/C composite. Int J. Heat Mass Transfer, 2008, 51, (9), pp 2614–2627.CrossRefGoogle Scholar
Graves, R. and Gosse, R., Reduced-Order Sensitivity Analysis of an Ablating Graphite Reentry Body. In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition (p. 957).Google Scholar
Lewis, S.W., James, C.M., Ravichandran, R., Morgan, R.G. and McIntyre, T.J. Carbon ablation in hypervelocity air and nitrogen shock layers. J. Thermophys. Heat Transfer, 2018, 32, (2), pp 449–468.CrossRefGoogle Scholar
Zeng, M., Liu, J., Xu, D. and Zhang, W.. Numerical study of the transient characteristics of ablative hypersonic flow fields. International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics, 2014.Google Scholar
Bag, S. and De, A. Development of a three-dimensional heat-transfer model for the gas tungsten arc welding process using the finite element method coupled with a genetic algorithm–based identification of uncertain input parameters. Metall. Mater. Trans. A, 2008, 39, (11), pp 2698–2710.CrossRefGoogle Scholar
Tsai, N.S. and Eagar, T.W. Distribution of the heat and current fluxes in gas tungsten arcs. Metall. Trans. B, 1985, 16, (4), pp 841–846.CrossRefGoogle Scholar
Goldak, J., Chakravarti, A. and Bibby, M. A new finite element model for welding heat sources. Metall. Trans. B, 1984, 15, (2), pp 299–305.CrossRefGoogle Scholar
Arul, S. and Sellamuthu, R. Application of a simplified simulation method to the determination of arc efficiency of gas tungsten arc welding (GTAW) and experimental validation. Int. J. Comput. Mater. Sci. Surf. Eng., 2011, 4, (3), pp 265–280.Google Scholar
Scala, S.M. The Ablation of Graphite in Dissociated Air: Theory, Missile and Space Division, General Electric, 1962, pp 1-94.Google Scholar