Title: Methodology for Validation of Material Response Models Using In-Situ Ablation Sensing Methods
Authors: Colin Yee, Jon Langston, Hao Wu and Joseph H. Koo
Abstract: A complete and efficient methodology for characterizing the pyrolysis response of ablative Thermal Protection Systems (TPS) materials is developed. The end goal of acquiring the inputs necessary for material response (MR) modeling in extreme hyperthermal environments is to permit rapid down-selection of TPS materials. The example case in this study focuses on the characterization of the MXB-360 glass/phenolic ablative for use in the Insulation Thermal Response and Ablation Code (ITRAC) developed by Northrop Grumman Innovation Systems. Aerothermal ablation testing was conducted on an oxyacetylene test bed with the use of small test models. Emphasis is placed on determining pyrolysis kinetic modeling constants by use of TGA, pyrolysis gas composition and enthalpy tables by energy dispersive x-ray (EDX) spectroscopy, and in-depth temperature profile matching by in-situ ablation sensing methods. Sensor construction methods, oxidizing versus non-oxidizing environment considerations, data analysis of in-situ ablation sensing methods, and validation criteria for MR modeling are briefly discussed.
References: 1. Starkey, R.P. and M.J. Lewis, Critical Design Issues for Airbreathing Hypersonic Waverider Missiles. Journal of Spacecraft and Rockets, 2001. 38(4): p. 510-519. 2. Szczepanowska, H. and T.G. Mathia, Space Heritage: The Apollo Heat Shield; Atmospheric Reentry Imprint on Materials’ Surface. MRS Proceedings, 2011. 1319. 3. Suzuki, T., et al., Postflight Thermal Protection System Analysis of Hayabusa Reentry Capsule. Journal of Spacecraft and Rockets, 2014. 51(1): p. 96-105. 4. Knight, D., et al., Assessment of predictive capabilities for aerodynamic heating in hypersonic flow. Progress in Aerospace Sciences, 2017. 90: p. 39-53. 5. Paglia, L., et al., Carbon-phenolic ablative materials for re-entry space vehicles: plasma wind tunnel test and finite element modeling. Materials & Design, 2016. 90: p. 1170-1180. 6. MacDonald, M.E., C.M. Jacobs, and C.O. Laux, Interaction of Air Plasma With Ablating Heat Shield Material. IEEE Transactions on Plasma Science, 2014. 42(10): p. 2658-2659. 7. Natali, M., et al., An in-situ ablation recession sensor for carbon/carbon ablatives based on commercial ultra-miniature thermocouples. Sensors and Actuators B: Chemical, 2014. 196: p. 46-56. 8. Koo, J.H., et al., In Situ Ablation Recession and Thermal Sensor for Thermal Protection Systems. Journal of Spacecraft and Rockets, 2018. 55(4): p. 783-796. 9. Ewing, M.E. and B. Pincock, Heat Transfer Modeling of a Charring Material Using Isoconversional Kinetics. Heat Transfer Engineering, 2016. 38(13): p. 1189-1197. 10. Ewing, M.E., T.S. Laker, and D.T. Walker, Numerical Modeling of Ablation Heat Transfer. Journal of Thermophysics and Heat Transfer, 2013. 27(4): p. 615-632. 11. Sihn, S., et al., Identifying unified kinetic model parameters for thermal decomposition of polymer matrix composites. Journal of Composite Materials, 2018. 53(20): p. 2875-2890. 12. Ozawa, T., A New Method of Analysing Thermogravimetric Data. Bulletin of the Chemical Society of Japan, 1965. 38. 13. Yee, C., et al., In Situ Ablation Recession Sensor for Ablative Materials Based on Ultraminiature Thermocouples. Journal of Spacecraft and Rockets, 2014. 51(6): p. 1789-1796. 14. Ewing, M.E. and D.A. Isaac, Thermodynamic Property Calculations for Equilibrium Mixtures. Journal of Thermophysics and Heat Transfer, 2018. 32(1): p. 118-128.
Conference: SAMPE 2020 | Virtual Series
Publication Date: 2020/06/01
Price: FREEGet This Paper