SIRCA-14A [virgin]

Name: SIRCA-14A [virgin]
Database: NASA Ames Thermal Protection Materials
Category: Silicon-Based Ablators
Composition: AIM-10 tile, infiltrated w/ silicone
Manufacturer: NASA Ames Research Center, Thermal Protection Materials and Systems Branch
Technical Readiness Level: 6
Last Modified: 2001-10-01

Description:

  • SIRCA-14A uses the Ames Insulation Material (AIM-10) substrate with 0.16 g/cc density and is impregnated with silicone to produce a final density of approximately 0.224 g/cc. SIRCA-14A can withstand a higher heating rate than SIRCA-15F due to its pure silica substrate, but has lower mechanical properties than the SIRCA-15F. The material is best suited for high heating rate, low heat load and low mechanical load conditions.

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 2.24e+02 kg/m^3 4.8 measured assumed/assumed 1 2006-01-05
Thermal Conductivity (Isotropic) 6.29e-02 W/m-K N/A unknown nonstp 2006-01-05
Specific Heat 1.20e+03 J/kg-K N/A unknown TRUE 2006-01-05
Emissivity 9.21e-01 - N/A measured assumed/assumed 1 2006-01-05
Tensile Strength (Thru-the-Thickness) 2.76e+05 Pa N/A measured assumed/assumed 1 2006-01-05
Tensile Strength (In-Plane) 5.17e+05 Pa N/A measured assumed/assumed 1 2006-01-05
Tensile Strain to Failure (Thru-the-Thickness) 9.80e-03 m/m N/A unknown assumed/assumed 2006-01-05
Tensile Strain to Failure (In-Plane) 6.60e-03 m/m N/A unknown assumed/assumed 2006-01-05
Tensile Modulus (Thru-the-Thickness) 7.03e+07 Pa N/A unknown assumed/assumed 2006-01-05
Tensile Modulus (In-Plane) 3.38e+08 Pa N/A unknown assumed/assumed 2006-01-05
Compressive Strength (Thru-the-Thickness) 9.65e+05 Pa N/A unknown assumed/assumed 2006-01-05
Compressive Strength (In-Plane) 1.93e+06 Pa N/A unknown assumed/assumed 2006-01-05
Compressive Strain to Failure (Thru-the-Thickness) 0.03 m/m N/A unknown assumed/assumed 2006-01-05
Compressive Strain to Failure (In-Plane) 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 3.74e+07 J/kg N/A unknown nonstp* 2006-01-05

Notes:

  • N/A

Property References:

  • 1. 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.: Mechanical Properties of SIRCA-15F for Mars/pathfinder:NASA internal memo report to JPL:TPSX Ref. #70.
  • 2. 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.
  • 3. 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.
  • 4. H.K. Tran: Light Weight Ceramic Ablators for Mars Follow-on Mission Vehicle TPS:NASA TM (to be published):TPSX Ref. #73.