SIRCA-15F [virgin]

Name: SIRCA-15F [virgin]
Database: NASA Ames Thermal Protection Materials
Category: Silicon-Based Ablators
Composition: FRCI-12 tile, infiltrated w/ silicone
Manufacturer: NASA Ames Research Center, Thermal Protection Materials and Systems Branch
Technical Readiness Level: 9
Last Modified: 2001-10-01

Description:

  • SIRCA-15F uses the Fibrous Refractory Ceramic Insulation, with 0.192 g/cc density (FRCI-12) tile substrate and is impregnated with silicone to produce a material with a final density of approximately 0.25 g/cc. SIRCA-15F was used for the aft plate heat shield and a portion of the conical aft section of the Mars/Pathfinder probe, which successfully landed on the Martian surface in July 1997. SIRCA-15F was designed, tested, and manufactured for the X-34 Program as a re-usable TPS for the nosecap and wing and rudder leading edges. SIRCA-15F is also being manufactured to support the Backshell Interface Plate (BIP) for the Mars 2003 Mission.

Point of Contact:

  • Frank S. Milos
  • NASA Ames Research Center
  • fmilos@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
Density 2.40e+02 kg/m^3 3.2 measured assumed/assumed 2 2006-01-05
Thermal Conductivity (Isotropic) 5.90e-02 W/m-K N/A measured nonstp 1 2006-01-05
Specific Heat 1.12e+03 J/kg-K N/A unknown TRUE 2006-01-05
Emissivity 9.21e-01 - 4.61e-02 measured assumed/assumed 1 2006-01-05
Tensile Strength (Thru-the-Thickness)1 7.45e+05 Pa N/A measured assumed/assumed 2 2006-01-05
Tensile Strength (In-Plane)2 1.99e+06 Pa N/A measured assumed/assumed 2 2006-01-05
Tensile Strain to Failure (Thru-the-Thickness)3 9.30e-03 m/m N/A measured assumed/assumed 2 2006-01-05
Tensile Strain to Failure (In-Plane)4 6.60e-03 m/m N/A measured assumed/assumed 2006-01-05
Tensile Modulus (Thru-the-Thickness)5 7.03e+07 Pa N/A predicted assumed/assumed 2006-01-05
Tensile Modulus (In-Plane)6 3.38e+08 Pa N/A predicted assumed/assumed 2006-01-05
Compressive Strength (Thru-the-Thickness)7 9.65e+05 Pa N/A unknown assumed/assumed 2006-01-05
Compressive Strength (In-Plane)8 1.93e+06 Pa N/A unknown assumed/assumed 2006-01-05
Compressive Strain to Failure (Thru-the-Thickness)9 0.03 m/m N/A unknown assumed/assumed 2006-01-05
Compressive Strain to Failure (In-Plane)10 2.20e-02 m/m N/A unknown assumed/assumed 2006-01-05
Compressive Modulus (Thru-the-Thickness) 3.72e+07 Pa N/A unknown assumed/assumed 2006-01-05
Compressive Modulus (In-Plane) 1.00e+08 Pa N/A unknown assumed/assumed 2006-01-05
Coefficient of Thermal Expansion (Isotropic) 1.42e-06 1/K N/A unknown interpolated(T) 2006-01-05
Effective Heat of Ablation 4.02e+07 J/kg N/A measured nonstp* 1 2006-01-05
Volume Fraction of Resin 4.06e-02 - N/A unknown assumed/assumed 2006-01-05

Notes:

  • 1. Values are for room-temperature material.
  • 2. Values are for room-temperature material.
  • 3. Values are for room-temperature material.
  • 4. Values are for room-temperature material.
  • 5. Values are for room-temperature material.
  • 6. Values are for room-temperature material.
  • 7. Values are for room-temperature material.
  • 8. Values are for room-temperature material.
  • 9. Values are for room-temperature material.
  • 10. Values are for room-temperature material.

Property References:

  • 1. H.K. Tran, et al.: Silicone Impregnated Reusable Ceramic Ablators for Mars Follow-on Missions:AIAA Paper 96-1819:TPSX Ref. #67.
  • 2. H.K. Tran, et al.: Mechanical Properties of SIRCA-15F for Mars/pathfinder:NASA internal memo report to JPL:TPSX Ref. #70.

General References:

  • 1. H.K. Tran, et al.: Silicone Impregnated Reusable Ceramic Ablators for Mars Follow-on Missions:AIAA Paper 96-1819:TPSX Ref. #67.
  • 2. H.K. Tran, D.J. Rasky, L. Esfahani: Thermal Response and Ablation Characteristics of Light Weight Ceramic Ablators:A-9766, Journal of Spacecraft and Rockets:Jul. 1994:TPSX Ref. #68.
  • 3. H.K. Tran: Evaluation of Novel Light-Weight Ceramic Ablators by Arc Jet Testing:NASA TM-108798:Jan.1994:TPSX Ref. #69.
  • 4. H.K. Tran, et al.: Mechanical Properties of SIRCA-15F for Mars/pathfinder:NASA internal memo report to JPL:TPSX Ref. #70.
  • 5. H.K. Tran, et al.: Mars/Pathfinder Back Interface Plate Heat Shield and Designs Verification Tests in the Ames 20MW Panel Test Facility:NASA Internal Report to JPL:TPSX Ref. #71.
  • 6. H.K. Tran, et al.: Advanced Ablative Heat Shield Materials for Leading Edge Applications for the Reusable Launch Vehicle:NASA TM (to be published):TPSX Ref. #72.