RCC (Reinforced Carbon-Carbon Composite)

Name: RCC (Reinforced Carbon-Carbon Composite)
Database: NASA Ames Thermal Protection Materials
Category: Carbon-Based Reusable Composites: Carbon-Carbons
Composition: N/A
Manufacturer: N/A
Technical Readiness Level: N/A
Last Modified: 1996-04-24

Description:

  • Reinforced Carbon-Carbon (RCC) Composite was developed for use on the Shuttle leading edges and nosecap by LTV Corporation. It is comprised of a silicon-carbide coated carbon-carbon composite, fabricated from a low modulus rayon precursor-based fabric with a filled phenolic resin. RCC is currently outdated for many applications by the more recent Advanced Carbon-Carbon material (ACC). Manufactured by Vought Corporation, Systems Division. Properties are for RCC/Coated/TEOS/Type A.

Point of Contact:

  • dcurry@ems.jsc.nasa.gov

Pictures:

Properties at Standard Conditions
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Property Value Units Uncertainty Source STP Reference Last Modified Additional Data
Density 9.85e+01 lbm/ft^3 N/A unknown assumed/assumed 2006-01-05
Thermal Conductivity (Thru-the-Thickness) 6.25e-04 Btu/ft-s-R N/A unknown TRUE 2006-01-05
Thermal Conductivity (In-Plane) 9.75e-04 Btu/ft-s-R N/A unknown TRUE 2006-01-05
Specific Heat 1.70e-01 Btu/lbm-R N/A unknown TRUE 2006-01-05
Emissivity 0.78 - N/A unknown TRUE 2006-01-05
Multiple Use Temperature Limit 3.46e+03 R N/A unknown assumed/assumed 2006-01-05
Single Use Temperature Limit 3.66e+03 R N/A unknown assumed/assumed 2006-01-05
Coefficient of Thermal Expansion (Isotropic)1 7.30e-07 1/R N/A unknown TRUE 2006-01-05
Purchase Cost 1.20e+04 $/ft^2 N/A unknown assumed/assumed 2006-01-05
Installation Time 3.46e+04 s/ft^2 N/A unknown assumed/assumed 2006-01-05
Inspection/Repair Time per Flight 5.04e+02 s/ft^2 N/A unknown assumed/assumed 2006-01-05
Replacement Fraction per Flight 1.30e-03 - N/A unknown assumed/assumed 2006-01-05
Reuse Flight Limit (# of flights)2 33.0 - N/A unknown assumed/assumed 2006-01-05

Notes:

  • 1. Values are for 19-ply thick RCC.
  • 2. Typical value. Actual number of flight reuses depends on flight environment.

Property References:

  • N/A

General 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. 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.
  • 3. anon: Current Technology for Thermal Protection Systems:NASA Conf. Pub. 3157:Feb. 1992:TPSX Ref. #9.
  • 4. anon: Space Shuttle Program Thermodynamic Design Data Book. Penetrations.:SD73-SH-0226:Rockwell International, Downey, CA:Jan. 1981:TPSX Ref. #23.
  • 5. D.M. Curry, C.N. Webster: Material Characteristics of Space Shuttle Reinforced Carbon-Carbon:24th National SAMPE Symposium, San Francisco, CA:1979:TPSX Ref. #37.
  • 6. Don A. Beckley, George Kania: Carbon/Carbon Prepreg Characterization and Development:Hitco Materials Division, U.S. Polymeric:TPSX Ref. #38.
  • 7. anon: Revised Design Values for RCC Thermal Conductivity, Revision A:Vought Dir 2-53020/RCC/1-0013:Feb. 12, 1982:TPSX Ref. #39.