AETB-12 Rigid Tile

Name: AETB-12 Rigid Tile
Database: NASA Ames Thermal Protection Materials
Category: Silicon-Based Reusable Composites: Rigid Ceramic Tiles
Composition: 20% AL2O3, 12% (14% B2O3, 72% AL2O3, 14% SiO2-Nextel), 68% SiO2
Manufacturer: Boeing, Forrest Machining, United Space Alliance (USA)
Technical Readiness Level: 7
Last Modified: 2001-10-01

Description:

  • AETB-12 is a relatively low density (~12 lbs/cu.ft.), low thermal conductivity fibrous insulation material with higher temperature capability and better processing dimensional stability than the FRCI-12, LI-900 and LI-2200 insulation that are baselined on all of the shuttle orbiters. It was successfully flown on the shuttle at moderate temperatures as an experimental material on the top of the body flap.

Point of Contact:

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

Pictures:

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

Property Value Units Uncertainty Source STP Reference Last Modified Additional Data
Density1 1.92e+02 kg/m^3 9.61 measured assumed/assumed 4 2006-01-05
Thermal Conductivity (Thru-the-Thickness) 6.40e-02 W/m-K 3.20e-03 predicted TRUE 1 2006-01-05
Specific Heat2 6.28e+02 J/kg-K 31.4 predicted TRUE 1 2006-01-05
Emissivity3 0.88 - 4.40e-02 measured TRUE 3 2006-01-05
Multiple Use Temperature Limit 1.70e+03 K 85.0 predicted assumed/assumed 1 2006-01-05
Single Use Temperature Limit 1.87e+03 K 93.3 predicted assumed/assumed 1 2006-01-05
Tensile Strength (Thru-the-Thickness)4 6.86e+05 Pa 3.43e+04 measured TRUE 4 2006-01-05
Tensile Strength (In-Plane)5 1.44e+06 Pa 7.20e+04 measured TRUE 4 2006-01-05
Tensile Modulus (Thru-the-Thickness)6 1.10e+08 Pa 5.52e+06 measured TRUE 1 2006-01-05
Tensile Modulus (In-Plane)7 2.21e+08 Pa 1.10e+07 measured TRUE 1 2006-01-05
Coefficient of Thermal Expansion (Thru-the-Thickness) 2.60e-06 1/K 1.30e-07 measured assumed/assumed 4 2006-01-05
Coefficient of Thermal Expansion (In-Plane) 2.85e-06 1/K 1.43e-07 measured assumed/assumed 4 2006-01-05
Purchase Cost8 1.25e+04 $/m^2 6.24e+02 predicted assumed/assumed 2 2006-01-05
Installation Time9 8.53e+05 s/m^2 4.26e+04 predicted assumed/assumed 2 2006-01-05
Inspection/Repair Time per Flight10 2.48e+04 s/m^2 1.24e+03 predicted assumed/assumed 2 2006-01-05
Replacement Fraction per Flight11 1.40e-03 - 7.00e-05 predicted assumed/assumed 2 2006-01-05
Reuse Flight Limit (# of flights)12 1.00e+02 - 5.0 predicted assumed/assumed 2 2006-01-05

Notes:

  • 1. Value is for uncoated tile.
  • 2. Specific Heat predicted using rule of mixtures and data from an ASTM handbook.
  • 3. Value is for uncoated tile. Room temperature value is measured. The higher temperature values are extrapolated
  • 4. Linearly extrapolated from the softening point and do not appear in any published data (only restricted documents)
  • 5. Linearly extrapolated from the softening point and do not appear in any published data (only restricted documents)
  • 6. Linearly extrapolated from the softening point and do not appear in any published data (only restricted documents)
  • 7. Linearly extrapolated from the softening point and do not appear in any published data (only restricted documents)
  • 8. Cost for RCG coated tile.
  • 9. Predicted based on arcjet and or flight test data.
  • 10. Predicted based on arcjet and or flight test data.
  • 11. Predicted based on arcjet and or flight test data.
  • 12. 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. D.J. Rasky: Thermal Protection Systems for Future Reusable Launch Vehicles:25th International Conference on Environmemtal Systems, No. 951618:Jul. 1995:TPSX Ref. #7.
  • 3. 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.
  • 4. D.B. Leiser, M. Smith, D.A. Stewart: Options for Improving Rigidized Ceramic Heatshields:Ceram. Eng. Sci. Proc.:1985:TPSX Ref. #14.

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. D.B. Leiser, M. Smith, D.A. Stewart: Options for Improving Rigidized Ceramic Heatshields:Ceram. Eng. Sci. Proc.:1985:TPSX Ref. #14.
  • 10. M. Smith, D.B. Leiser, H.E. Goldstein: Alumina Enhanced Thermal Barrier:NASA Tech Brief:1989:TPSX Ref. #15.