LI-2200 Rigid Tile

Name: LI-2200 Rigid Tile
Database: NASA Ames Thermal Protection Materials
Category: Silicon-Based Reusable Composites: Rigid Ceramic Tiles
Composition: 100% SiO2
Manufacturer: United Space Alliance (USA)
Technical Readiness Level: 9
Last Modified: 2001-10-01

Description:

  • LI-2200 is a relatively high density (~22 lbs/cu.ft.) and thermal conductivity fibrous insulation material with higher strength than the LI-900 baselined for use on all the shuttle orbiters. It is currently flying on all orbiters, but to a very limited extent due to itsÕ weight. It was originally developed to provide an enhanced strength RSI tile relative to LI-900.

Point of Contact:

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

Pictures:

Properties at Standard Conditions
Eng
Switch to SI Units (MKS)
Export Data (Coming Soon!)

Property Value Units Uncertainty Source STP Reference Last Modified Additional Data
Density1 2.20e+01 lbm/ft^3 1.10e+00 measured assumed/assumed 5 2006-01-05
Thermal Conductivity (Thru-the-Thickness)2 1.19e-05 Btu/ft-s-R 2.15e-06 measured TRUE 3 2006-01-05
Thermal Conductivity (In-Plane)3 1.67e-05 Btu/ft-s-R 3.00e-06 measured TRUE 3 2006-01-05
Specific Heat4 1.50e-01 Btu/lbm-R 2.01e-02 measured TRUE 3 2006-01-05
Emissivity5 8.99e-01 - 4.50e-02 measured TRUE 2 2006-01-05
Multiple Use Temperature Limit6 2.96e+03 R 1.48e+02 predicted assumed/assumed 4 2006-01-05
Single Use Temperature Limit7 3.26e+03 R 1.63e+02 predicted assumed/assumed 4 2006-01-05
Tensile Strength (Thru-the-Thickness)8 1.05e+04 psf 1.73e+03 measured assumed/assumed 5 2006-01-05
Tensile Strength (In-Plane)9 2.61e+04 psf 4.18e+03 measured assumed/assumed 5 2006-01-05
Tensile Modulus (Thru-the-Thickness)10 3.89e+06 psf 1.94e+05 measured assumed/assumed 5 2006-01-05
Tensile Modulus (In-Plane)11 1.15e+07 psf 5.76e+05 measured assumed/assumed 5 2006-01-05
Compressive Strength (Thru-the-Thickness)12 1.87e+04 psf 9.36e+02 measured assumed/assumed 5 2006-01-05
Compressive Strength (In-Plane)13 3.31e+04 psf 1.66e+03 measured assumed/assumed 5 2006-01-05
Coefficient of Thermal Expansion (Isotropic)14 2.68e-07 1/R 3.68e-08 measured interpolated(T) 5 2006-01-05
Dielectric Constant15 1.3 - 6.50e-03 measured assumed/assumed 5 2006-01-05
Loss Tangent16 1.60e-03 - 8.00e-05 measured assumed/assumed 5 2006-01-05
Purchase Cost17 1.16e+03 $/ft^2 5.80e+01 predicted assumed/assumed 1 2006-01-05
Installation Time18 3.28e+05 s/ft^2 1.64e+04 predicted assumed/assumed 1 2006-01-05
Inspection/Repair Time per Flight19 7.56e+03 s/ft^2 3.78e+02 predicted assumed/assumed 1 2006-01-05
Replacement Fraction per Flight20 2.50e-03 - 1.25e-04 predicted assumed/assumed 1 2006-01-05
Reuse Flight Limit (# of flights)21 1.00e+02 - 5.0 predicted assumed/assumed 1 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 shuttle flight test data.
  • 7. Predicted based on arcjet and/or shuttle 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 several hundred room-temperature tests.
  • 9. Mechanical properties remain relatively constant up to 1144K (1600F), where a gradual reduction in strength begins. Standard deviation value based on several hundred room-temperature tests.
  • 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 measurement limit, whichever is greater. Directional dependence not specified, so isotropic is assumed.
  • 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.
  • 21. Predicted based on arcjet and or flight test data.

Property References:

  • 1. D.J. Rasky: Thermal Protection Systems for Future Reusable Launch Vehicles:25th International Conference on Environmemtal Systems, No. 951618:Jul. 1995:TPSX Ref. #7.
  • 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. anon: Space Shuttle Program Thermodynamic Design Data Book. Penetrations.:SD73-SH-0226:Rockwell International, Downey, CA:Jan. 1981:TPSX Ref. #23.
  • 4. anon: Shuttle Operational Data Book:Boeing Document:Boeing:TPSX Ref. #28.
  • 5. anon: LI-2200: A 22-PCF, All Silica Insulation Material:Lockheed Missiles and Space Co.:Apr-83:TPSX Ref. #126.

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. H.E. Goldstein, M. Smith, D.B. Leiser: Silica Reusable Surface Insulation:U.S. Patent No. 3,952,083:1976:TPSX Ref. #11.