Ablation and Thermal Response Property Model Validation for Phenolic Impregnated Carbon Ablator

Phenolic Impregnated Carbon Ablator was the heatshield material for the Stardust probe and is also a candidate heatshield material for the Orion Crew Module. As part of the heatshield qualification for Orion, physical and thermal properties were measured for newly manufactured material, included emissivity, heat capacity, thermal conductivity, elemental composition, and thermal decomposition rates. Based on these properties, an ablation and thermal-response model was developed for temperatures up to 3500 K and pressures up to 100 kPa. The model includes transversely isotropic and pressure-dependent thermal conductivity. In this work, model validation is accomplished by comparison of predictions with data from many arcjet tests conducted over a range of stagnation heat flux and pressure from 107 W/cm 2 at 2.3 kPa to 1100 W/cm 2 at 84 kPa. Over the entire range of test

[1]  W. Winovich,et al.  The 60-MW Shuttle interaction heating facility , 1979 .

[2]  Frank S. Milos,et al.  Ablation and Thermal Response Program for Spacecraft Heatshield Analysis , 1999 .

[3]  Dean Kontinos,et al.  Post-Flight Evaluation of Stardust Sample Return Capsule Forebody Heatshield Material , 2008 .

[4]  William Willcockson.  Stardust Sample Return Capsule Design Experience , 1999 .

[5]  F. S. Milos,et al.  Two-Dimensional Implicit Thermal Response and Ablation Program for Charring Materials , 2001 .

[6]  H. Tran,et al.  Phenolic Impregnated Carbon Ablators (PICA) for Discovery class missions , 1996 .

[7]  Frank S. Milos,et al.  Loosely Coupled Simulation for Two-Dimensional Ablation and Shape Change , 2010 .

[8]  J. Olejniczak,et al.  Erratum on "Performance of a Low Density Ablative Heat Shield Material" , 2008 .

[9]  F. Milos,et al.  Comprehensive model for multicomponent ablation thermochemistry , 1997 .

[10]  Aliza Balter-Peterson,et al.  Arc jet testing in NASA Ames Research Center thermophysics facilities , 1992 .

[11]  G. Candler,et al.  Data-Parallel Line Relaxation Method for the Navier -Stokes Equations , 1998 .

[12]  J. Olejniczak,et al.  Erratum on "Erratum on 'Performance of a Low Density Ablative Heat Shield Material'" , 2004 .

[13]  Karl T. Edquist,et al.  Development of the Mars Science Laboratory Heatshield Thermal Protection System , 2009 .

[14]  Karl T. Edquist,et al.  Two-Dimensional Ablation and Thermal Response Analyses for Mars Science Laboratory Heat Shield , 2009 .

[15]  Frank Milos,et al.  Two-Dimensional Ablation, Thermal Response, and Sizing Program for Pyrolyzing Ablators , 2009 .

[16]  Frank S. Milos,et al.  Non-Equilibrium Ablation of Phenolic Impregnated Carbon Ablator , 2010 .