FRCI-12 Rigid Tile

Name: FRCI-12 Rigid Tile
Database: NASA Ames Thermal Protection Materials
Category: Silicon-Based Reusable Composites: Rigid Ceramic Tiles
Composition: Approximately 78% wt. silica (SiO2), 22% wt. aluminoborosilicate (62% Al2O3, 24% SiO2, 14% B2O3)
Manufacturer: Boeing, Forrest Machining, United Space Alliance (USA)
Technical Readiness Level: 8
Last Modified: 2001-10-01

Description:

  • FRCI-12 is a relatively low density (~12 lbs/cu.ft.), low thermal conductivity fibrous insulation material that is substantially stronger than the original LI-900 and equivalent in strength to LI-2200 at a lower density. It was baselined for use on all of the shuttle orbiters. It has been flying successfully on the shuttle since its adoption shortly after the second orbiter Challenger was built.

Point of Contact:

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

Pictures:

Properties at Standard Conditions
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Property Value Units Uncertainty Source STP Reference Last Modified Additional Data
Density1 1.92e+02 kg/m^3 9.61 measured assumed/assumed 1 2006-01-05
Thermal Conductivity (Thru-the-Thickness)2 5.30e-02 W/m-K 9.53e-03 measured TRUE 2 2006-01-05
Thermal Conductivity (In-Plane)3 7.96e-02 W/m-K 1.43e-02 measured TRUE 2 2006-01-05
Specific Heat4 7.12e+02 J/kg-K 84.0 measured TRUE 5 2006-01-05
Emissivity5 9.17e-01 - 4.59e-02 measured TRUE 4 2006-01-05
Multiple Use Temperature Limit6 1.64e+03 K 82.2 predicted assumed/assumed 1 2006-01-05
Single Use Temperature Limit7 1.81e+03 K 90.6 predicted assumed/assumed 1 2006-01-05
Tensile Strength (Thru-the-Thickness)8 5.58e+05 Pa 6.90e+04 measured assumed/assumed 5 2006-01-05
Tensile Strength (In-Plane)9 1.77e+06 Pa 2.50e+05 measured assumed/assumed 5 2006-01-05
Tensile Modulus (Thru-the-Thickness)10 6.89e+07 Pa 3.45e+06 measured assumed/assumed 5 2006-01-05
Tensile Modulus (In-Plane)11 3.45e+08 Pa 1.72e+07 measured assumed/assumed 5 2006-01-05
Compressive Strength (Thru-the-Thickness)12 9.10e+05 Pa 4.55e+03 measured assumed/assumed 5 2006-01-05
Compressive Strength (In-Plane)13 1.83e+06 Pa 9.14e+03 measured assumed/assumed 5 2006-01-05
Coefficient of Thermal Expansion (In-Plane)14 1.30e-06 1/K 1.56e-07 measured nonstp 5 2006-01-05
Dielectric Constant15 1.2 - 6.00e-03 measured assumed/assumed 5 2006-01-05
Loss Tangent16 9.00e-04 - 4.50e-05 measured assumed/assumed 5 2006-01-05
Purchase Cost17 1.25e+04 $/m^2 6.24e+02 predicted assumed/assumed 3 2006-01-05
Installation Time18 3.53e+06 s/m^2 1.76e+05 predicted assumed/assumed 3 2006-01-05
Inspection/Repair Time per Flight19 8.14e+04 s/m^2 4.07e+03 predicted assumed/assumed 3 2006-01-05
Replacement Fraction per Flight20 2.50e-03 - 1.25e-04 predicted assumed/assumed 3 2006-01-05
Reuse Flight Limit (# of flights) 1.00e+02 - 5.0 predicted assumed/assumed 3 2006-01-05

Notes:

  • 1. Value is for uncoated tile.
  • 2. Dynamic values for transient environments. Uncertainty (tolerance) is +/- 18% or +/- 5.8e-3 W/mK (0.04 BTU-in/ft2-hr-F), whichever is greater
  • 3. Dynamic values for transient environments. Uncertainty (tolerance) is +/- 18% or +/- 5.8e-3 W/mK (0.04 BTU-in/ft2-hr-F), whichever is greater
  • 4. Uncertainty (tolerance) is +/- 10% or +/- 4.8e-6 W/mK (0.02 BTU/lb-F), whichever is greater
  • 5. Value is for uncoated tile. Room temperature value is measured. The higher temperature values are extrapolated.
  • 6. Predicted based on arcjet and or flight test data.
  • 7. Predicted based on arcjet and or flight test data.
  • 8. Mechanical properties remain relatively constant up to 1144K (1600F), where a gradual reduction in strength begins. Standard deviation value based on 1200 tensile tests at room temperature.
  • 9. Mechanical properties remain relatively constant up to 1144K (1600F), where a gradual reduction in strength begins. Standard deviation value based on 1200 tensile tests at room temperature.
  • 10. Only room temperature values are available from the reference.
  • 11. Only room temperature values are available from the reference.
  • 12. Only room temperature values are available from the reference.
  • 13. Only room temperature values are available from the reference.
  • 14. Uncertainty (tolerance) is +/- 12% or +/- 1.7e-5/T ( deg C) (0.3e-4/T (deg F), whichever is greater. Reference gives values of thermal expansion at specific temperatures, not the coefficients.
  • 15. RF characteristics at 10GHz (room temperature)
  • 16. RF characteristics at 10GHz (room temperature)
  • 17. Cost for RCG coated tile. Predicted based on arcjet and or flight test data.
  • 18. Predicted based on arcjet and or flight test data.
  • 19. Predicted based on arcjet and or flight test data.
  • 20. Predicted based on arcjet and or flight test data.

Property References:

  • 1. S. Amanda Chiu, William C. Pitts: Reusable Surface Insulations for Reentry Spacecraft:AIAA Paper 91-0695:Jan. 1991:TPSX Ref. #3.
  • 2. Smith, J.A., and Curry, D.M: Aeroassist Flight Experiment Aerobrake Thermal Design Data Book:NASA JSC-23571:NASA JSC, Houston, TX:May-89:TPSX Ref. #5.
  • 3. D.J. Rasky: Thermal Protection Systems for Future Reusable Launch Vehicles:25th International Conference on Environmemtal Systems, No. 951618:Jul. 1995:TPSX Ref. #7.
  • 4. 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.
  • 5. anon: FRCI-12: Fibrous Refractory Composite Insulation Material:Lockheed Missiles & Space Co. Data Sheet:Jan. 1987:TPSX Ref. #115.

General References:

  • 1. D.A. Stewart, D.B. Leiser: Characterization of the Thermal Conductivity for Fibrous Refractory Composite Insulations:Ceramic Engineering and Science Proceedings:1985:TPSX Ref. #1.
  • 2. 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.
  • 3. S. Amanda Chiu, William C. Pitts: Reusable Surface Insulations for Reentry Spacecraft:AIAA Paper 91-0695:Jan. 1991:TPSX Ref. #3.
  • 4. D.B. Leiser, M. Smith, D.A. Stewart, H.E. Goldstein: Thermal and Mechanical Properties of Advanced High Temperature Ceramic-Composite Insulation:Ceram. Eng. Sci. Proc.:1983:TPSX Ref. #4.
  • 5. Smith, J.A., and Curry, D.M: Aeroassist Flight Experiment Aerobrake Thermal Design Data Book:NASA JSC-23571:NASA JSC, Houston, TX:May-89:TPSX Ref. #5.
  • 6. D.J. Rasky: Thermal Protection Systems for Future Reusable Launch Vehicles:25th International Conference on Environmemtal Systems, No. 951618:Jul. 1995:TPSX Ref. #7.
  • 7. C. Ehrlich, et al.: Advanced Manned Launch System Study (AMLS); Reusable Cyrogenic Tank Design:Contract NAS1-18975 DRD-9:Rockwell International, Space Systems Division, Downey, CA:Jul.-Sep. 1993:TPSX Ref. #8.
  • 8. anon: Current Technology for Thermal Protection Systems:NASA Conf. Pub. 3157:Feb. 1992:TPSX Ref. #9.
  • 9. 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.
  • 10. D.B. Leiser, H.E. Goldstein, M. Smith: Fibrous Refractory Composite Insulation:U.S. Patent No. 4,148,962:1979:TPSX Ref. #12.
  • 11. D.B. Leiser, M. Smith, H.E. Goldstein: Developments in Fibrous Refractory Composite Insulation:Bull. Amer. Ceram. Soc.:1981:TPSX Ref. #13.