PICA [virgin]

Name: PICA [virgin]
Database: NASA Ames Thermal Protection Materials
Category: Carbon-Based Ablators
Composition: Low density fibrous carbon substrate, infiltrated w/ phenolic
Manufacturer: Fiber Materials, Inc.
Technical Readiness Level: 5
Last Modified: 2001-10-01

Description:

  • The fibrous carbon substrate is manufactured by Fiber Materials Inc. (FMI) and is known as FiberForm(R), which is sold commercially for furnace liners. The FiberForm(R) is impregnated with phenolic to a final density of approximately 0.24 g/cc. The ablator PICA shows a particularly high effective heat of ablation at heat fluxes between approximately 300 - 1500 W/sqcm. PICA was selected as the forebody heatshield for the Stardust Discovery Class Mission which launched in February 1999. After collecting samples from the tail of the Wild-2 comet, Stardust will return to earth in 2006 and re-enter at 16 Km/sec; the fastest re-entry into earth's atmosphere, to date, for a man-made vehicle.

Point of Contact:

  • Frank S. Milos
  • NASA Ames Research Center
  • fmilos@mail.arc.nasa.gov

Pictures:

Properties at Standard Conditions
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Property Value Units Uncertainty Source STP Reference Last Modified Additional Data
Density 2.36e+02 kg/m^3 12.0 measured assumed/assumed 1 2006-01-05 N/A
Thermal Conductivity (Isotropic) 3.05e-01 W/m-K N/A measured nonstp 2 2006-01-05 N/A
Specific Heat 1.20e+03 J/kg-K N/A unknown TRUE 2006-01-05 N/A
Emissivity 0.8 - N/A measured assumed/assumed 2 2006-01-05 N/A
Tensile Strength (Thru-the-Thickness) 2.41e+05 Pa N/A unknown assumed/assumed 2006-01-05 N/A
Tensile Strength (In-Plane) 1.34e+06 Pa N/A unknown assumed/assumed 2006-01-05 N/A
Tensile Strain to Failure (Thru-the-Thickness) 8.50e-03 m/m N/A unknown assumed/assumed 2006-01-05 N/A
Tensile Strain to Failure (In-Plane) 1.20e-03 m/m N/A unknown assumed/assumed 2006-01-05 N/A
Tensile Modulus (Thru-the-Thickness) 2.36e+07 Pa N/A unknown assumed/assumed 2006-01-05 N/A
Tensile Modulus (In-Plane) 1.10e+08 Pa N/A unknown assumed/assumed 2006-01-05 N/A
Effective Heat of Ablation 1.15e+08 J/kg 5.77e+06 measured nonstp* 2006-01-05 N/A
Volume Fraction of Resin 6.46e-02 - N/A unknown assumed/assumed 2006-01-05 N/A
Pyrolysis Gas Enthalpy -9.02e+06 J/kg N/A unknown nonstp 2006-01-05 N/A

Notes:

  • N/A

Property References:

  • 1. 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.
  • 2. H.K. Tran, et al.: Phenolic Impregnated Carbon Ablators for Discovery Missions:AIAA Paper 96-1911:TPSX Ref. #74.

General References:

  • 1. 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.
  • 2. H.K. Tran: Evaluation of Novel Light-Weight Ceramic Ablators by Arc Jet Testing:NASA TM-108798:Jan.1994:TPSX Ref. #69.
  • 3. H.K. Tran, et al.: Phenolic Impregnated Carbon Ablators for Discovery Missions:AIAA Paper 96-1911:TPSX Ref. #74.
  • 4. anon: Some Comments on the Thermal Conductivity of Fiberform(R) Insulation:Fiber Materials, Inc., Biddeford Industrial Park, Biddeford, MA 04005:TPSX Ref. #75.
  • 5. anon: Light Weight Ceramic Ablators, Final Report:Contract No. NAS2-13982:Fiber Materials, Inc., Biddeford, MA 04005:TPSX Ref. #76.