TUFI Composite Surface

Name: TUFI Composite Surface
Database: NASA Ames Thermal Protection Materials
Category: Silicon-Based Reusable Composites: Rigid Ceramic Tiles
Composition: 2.5% SiB4, 77.5% (5.75% B2O3, 94.25% SiO2), 20% MoSi2
Manufacturer: Boeing, United Space Alliance (USA)
Technical Readiness Level: 8
Last Modified: 2001-10-01

Description:

  • TUFI, or Toughened Uni-piece Fibrous Insulation, is a functional gradient material possessing high emissivity, high temperature capability, toughness, and whose properties can be tailored, or adjusted to specific requirements.

Point of Contact:

  • Daniel Leiser
  • NASA Ames Research Center
  • dleiser@mail.arc.nasa.gov

Pictures:

Properties at Standard Conditions
SI Units (MKS)
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Property Value Units Uncertainty Source STP Reference Last Modified Additional Data
Density1 1.31e+03 kg/m^3 65.7 measured assumed/assumed 1 2006-01-05
Thermal Conductivity (Isotropic)2 8.43e-01 W/m-K 4.21e-02 predicted TRUE 1 2006-01-05
Specific Heat3 7.95e+02 J/kg-K 39.8 predicted TRUE 2006-01-05
Emissivity4 8.73e-01 - 4.36e-02 measured TRUE 2 2006-01-05
Multiple Use Temperature Limit5 1.59e+03 K 79.4 predicted assumed/assumed 2006-01-05
Single Use Temperature Limit6 1.87e+03 K 93.3 predicted assumed/assumed 2006-01-05
Oxygen Recombination Coefficient7 6.99e-04 - 3.50e-05 interpolated TRUE 3 2006-01-05
Nitrogen Recombination Coefficient8 8.59e-04 - 4.30e-05 interpolated TRUE 3 2006-01-05
Air Recombination Coefficient9 2.08e-01 - 1.04e-02 interpolated nonstp 3 2006-01-05

Notes:

  • 1. Represents the maximum composite density on AETB tile. Actual TUFI coating density varies through the coating layer.
  • 2. Dynamic values for transient environments. Thermal conductivity calculated using engineering function verified with arc-jet test data.
  • 3. Specific heat predicted using rule of mixtures and data from an ASTM handbook.
  • 4. Values for TUFI coated AETB-8. Room temperature value is measured. The higher temperature values are extrapolated
  • 5. Predicted based on arcjet and or flight test data
  • 6. Predicted based on arcjet and or flight test data
  • 7. Values based on Arrhenius curve fits [K exp(B/T)] of experimental data. T<685K: K=2.9E-4, B=264; 685K<T<1324K: K=10, B=-6900; T>1324K: K=1E-6, B=14400
  • 8. Values based on Arrhenius curve fits [K exp(B/T)] of experimental data. T<764K: K=7E-6, B=1443; T>764K: K=215, B=-11730
  • 9. Values based on Arrhenius curve fits [K exp(B/T)] of experimental data. 1255K<T<1644K: K=1e-4, B=9930

Property References:

  • 1. D.A. Stewart, D.B. Leiser: Characterization of the Thermal Conductivity for Advanced Toughened Uni-Piece Fibrous Insulations:AIAA Paper 93-2755:AIAA:Jul. 1993:TPSX Ref. #2.
  • 2. J. Ridge, J. Marschall: Estimation of Temperature Dependent Emissivities from Room Temperature Spectral Reflectance Measurements on Coated and Uncoated TPS Tiles:ELORET/Thermosciences Institute Report TSI-STM01-96-01:Sep. 1996:TPSX Ref. #10.
  • 3. D.A. Stewart: Surface Catalysis and Characterization of Proposed Candidate TPS for Access-to-Space Vehicles:NASA TM-112206:Jul. 1997:TPSX Ref. #19.

General References:

  • 1. J. Ridge, J. Marschall: Estimation of Temperature Dependent Emissivities from Room Temperature Spectral Reflectance Measurements on Coated and Uncoated TPS Tiles:ELORET/Thermosciences Institute Report TSI-STM01-96-01:Sep. 1996:TPSX Ref. #10.
  • 2. D.A. Stewart, J. Pallix, L. Esfahani: Surface Catalytic Efficiency of Candidate Ceramic Thermal Protection Materials for SSTO:NASA CDTM-20007:Mar. 1995:TPSX Ref. #18.
  • 3. D.B. Leiser, R. Churchward, V. Katvala, D.A. Stewart: Advanced Porous Coating for Low Density Ceramic Insulation Materials:J. Am. Ceram. Soc.:1989:TPSX Ref. #20.
  • 4. D.B. Leiser, M. Smith, R.A. Churchward, V.W. Katvala: Toughened Uni-Piece Fibrous Insulation:U.S. Patent No. 5,079,082:1992:TPSX Ref. #21.
  • 5. D.A. Stewart, D.B. Leiser: Characterization of the Thermal Conductivity for Advanced Toughened Uni-Piece Fibrous Insulation:AIAA Paper 93-2755:Jul. 6-9, 1993:TPSX Ref. #22.