Title: ABLATION TESTING AND MATERIAL RESPONSE MODEL VALIDATION FOR MX 4926N MC CARBON/PHENOLIC

Authors: Colin Yee, Samantha Bernstein, Joseph H. Koo

DOI: 10.33599/nasampe/s.23.0072

Abstract: An ablative material response model for Solvay-Cytec's MX 4926N MC carbon/phenolic composite was constructed using NASA's 1D Fully Implicit Ablation and Thermal Analysis Program (1dFIAT). MX 4926N MC is a rayon carbon fiber, phenolic resin legacy ablative material which sees extensive usage in the aerospace and defense industries. The material model was developed using a combination of thermogravimetric analysis (TGA) in air and publicly available literature detailing thermal characteristics. Samples of MX 4926N MC were subjected to high heat fluxes ranging from 200 to 1,500 W/cm2 on an oxyacetylene testbed (OTB) in order to measure experimental mass loss, linear ablation, surface temperature, and back face temperature. The environmental model was built based on heat flux data from a Gardon gauge and flow characteristics from an Ansys Workbench computational fluid dynamics (CFD) model. The 1dFIAT material response (MR) model is compared to the OTB experimental data for back face and peak heat soak temperatures and mass loss. Discrepancies between the experimental data and 1dFIAT MR model are discussed.

References: 1. J. Schaefer and T. Dahm, Studies of Nozzle Ablative Material Performance for Large Solid Boosters. NASA CR-72080, 1966. 2. M. E. Ewing, T. S. Laker, and D. T. Walker, Numerical Modeling of Ablation Heat Transfer. Journal of Thermophysics and Heat Transfer, 2013. DOI: 10.2514/1.T4164. 3. H. Chung, et al., Carbon disulfide exposure estimate and prevalence of chronic diseases after carbon disulfide poisoning-related occupational diseases. Annals of Occupational and Environmental Medicine, 2017. DOI: 10.1186/s40557-017-0208-6. 4. L. You-xin and Q. De-zhen, Cost-benefit analysis of the recovery of carbon disulfide in the manufacturing of viscose rayon. Scandinavian Journal of Work, Environment & Health, 1985. 5. S. Zhang, et al., Regenerated Cellulose by the Lyocell Process, a Brief Review of the Process and Properties. BioResources, 2018. DOI: 10.15376/biores.13.2.Zhang. 6. W. A. Clayton, et al., Thermal Properties of Ablative Chars. AFRL Technical Report, 1969. 7. J. Schaefer, et al., Studies of Ablative Material Performance for Solid Rocket Nozzle Applications. NASA CR-72429, 1968. 8. J. Arnold, J. Dodson, and B. Laub, Scubscale Solid Motor Nozzle Tests -- Phase IV and Nozzle Materials Screening and Thermal Characterization -- Phase V. NASA CR-161254, 1979. 9. Y. K. Chen and F. S. Milos, Ablation and Thermal Response Program for Spacecraft Heatshield Analysis. Journal of Spacecraft and Rockets, 1999. 10. O. Atak, et al., Preliminary Analysis of the Experimental Study of Ablative Materials Exposed to Oxy-Acetylene Test Bed with Modeling. International Journal of Energetic Materials and Chemical Propulsion, 2020. DOI: 10.1615/IntJEnergeticMaterialsChemProp.2020030350. 11. T. Ozawa, A New Method of Analysing Thermogravimetric Data. Bulletin of the Chemical Society of Japan, 1965. DOI: 10.1246/bcsj.38.1881. 12. S. Sihn, et al., Identifying unified kinetic model parameters for thermal decomposition of polymer matrix composites. Journal of Composite Materials, 2018. DOI: 10.1177/0021998318805821. 13. R. A. Rindal, et al., Experimental and Theoretical Analysis of Ablative Material Response in a Liquid-Propellant Rocket Engine. NASA CR-72301, 1967. 14. A. Amar, Modeling of One-Dimensional Ablation with Porous Flow Using Finite Control Volume Procedure. 2006.

Conference: SAMPE 2023

Publication Date: 2023/04/17

SKU: TP23-0000000072

Pages: 11

Price: $22.00