35v/o SCS-9a-(20v/oRBSiC/ZrB2)

Name: 35v/o SCS-9a-(20v/oRBSiC/ZrB2)
Database: NASA Ames Thermal Protection Materials
Category: Ultra-High Temperature Ceramics
Composition: N/A
Manufacturer: Advanced Ceramics Research, Tucson, Arizona.
Technical Readiness Level: N/A
Last Modified: 1998-11-17

Description:

  • The 35v/o SCS-9a-(20v/oRBSiC/ZrB2) CFCC is one of a family of ultra-high temperature, multi-use ceramic matrix composites developed in a NASA ARC funded SBIR. It, like other UHTC materials, is intended to be used in TPS applications. It was specifically developed as a ultra high temperature structural material to facilitate attaching other UHTC materials in TPS. Because of its large strain-to- failure, low modulus, and failure characteristics it may be suitable for many other applications including large panel TPS. Orthotropic mechanical properties for a unidirectional lay-up (nominally 10 plies) were computed with COSTAR. These computation were optimized so that good agreement was obtained with measured tensile properties. Thermal properties are from measured values except for the specific heat. The material is fabricated ply by ply and so other composite architecture are possible are, i.e., [0/90]s. Consolidation is achieved by uni- axial hot pressing. This material is fabricated exclusively by Advanced Ceramics Research of Tucson, Arizona. Because of the planarity and large volume fraction of SiC fibers in this material a oxidation protection coating is recommended for TPS applications. Such a coating has been optimized for this material by Ultramet of Pacoima, CA in a separate NASA ARC funded SBIR program The coating, called Ultra-2000, is a CVD codeposited HfC/SiC with a nominal thickness of 5 mils. Maximum single use temperature is based on observed performance of the oxidation protection coating (ULTRA-2000). Parallel, longitudinal or axial properties are in the fiber direction and normal properties are perpendicular or transverse to the fiber. Thin plates of this material can be considered transversely isotropic.

Point of Contact:

  • Donald T. Ellerby
  • NASA Ames Research Center
  • dellerby@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 3.60e+03 kg/m^3 N/A unknown assumed/assumed 2006-01-05
Thermal Conductivity (Thru-the-Thickness)1 2.63e+01 W/m-K N/A unknown TRUE 2006-01-05
Thermal Conductivity (In-Plane)2 3.25e+01 W/m-K N/A unknown TRUE 2006-01-05
Emissivity3 0.7 - N/A unknown TRUE 2006-01-05
Multiple Use Temperature Limit4 1.98e+03 K N/A unknown assumed/assumed 2006-01-05
Single Use Temperature Limit5 2.20e+03 K N/A unknown assumed/assumed 2006-01-05
Eutectic Temperature Limit6 2.48e+03 K N/A unknown assumed/assumed 2006-01-05
Melt Temperature7 3.02e+03 K N/A unknown assumed/assumed 2006-01-05
Tensile Strength (Thru-the-Thickness)8 2.76e+07 Pa N/A unknown TRUE 2 2006-01-05
Tensile Strength (In-Plane)9 3.28e+08 Pa N/A unknown TRUE 2 2006-01-05
Tensile Modulus (Thru-the-Thickness)10 1.19e+11 Pa N/A unknown TRUE 2006-01-05
Tensile Modulus (In-Plane)11 9.31e+10 Pa N/A unknown TRUE 2006-01-05
Compressive Strength (In-Plane) 7.45e+08 Pa N/A unknown TRUE 1 2006-01-05
Shear Strength (Isotropic)12 1.78e+07 Pa N/A unknown TRUE 2 2006-01-05
Poisson's Ratio (Isotropic)13 0.14 - N/A unknown TRUE 2006-01-05
Coefficient of Thermal Expansion (Thru-the-Thickness)14 5.40e-06 1/K N/A unknown TRUE 2 2006-01-05
Coefficient of Thermal Expansion (In-Plane)15 3.96e-06 1/K N/A unknown TRUE 2 2006-01-05

Notes:

  • 1. Values were calculated from thermal diffusivity (flash method) measurements, specific heat, and density data.
  • 2. Values were calculated from thermal diffusivity (flash method) measurements, specific heat, and density data.
  • 3. Total normal emittance of the unoxidized surface. Emissivity for an adherent oxide scale is typically 0.60. With the Ultra-2000 coating emittance is 0.9 and fairly independent of temperature.
  • 4. Based on recrystallization temperature of the SiC fibers.
  • 5. Based on measured thermal mechanical behavior in the normal direction (Ref 2).
  • 6. Property value for the matrix.
  • 7. Property value for the matrix.
  • 8. Measurements at high temperatures were conducted in an inert atmosphere. (Ref. 2)
  • 9. Measurements at high temperatures were conducted in an inert atmosphere. (Ref. 2)
  • 10. Measurements at high temperatures were conducted in an inert atmosphere.
  • 11. Measurements at high temperatures were conducted in an inert atmosphere.
  • 12. Interlaminar.
  • 13. Based on matrix.
  • 14. CTE measurements are from push-rod dilatometry in an inert atmmosphere.
  • 15. CTE measurements are from push-rod dilatometry in an inert atmmosphere.

Property References:

  • 1. K. Stuffle: Continuous Fiber Reinforced Composites for Heat Shield Applications:NASA ARC Contract NAS2-13896:Jan. 4, 1996:TPSX Ref. #49.
  • 2. S. Causey, K. Stuffle: Further Characterization of SCS-9afiber-(RBSiC-ZrB2)m Composites for Design of Aerospace Structures:Proceedings of 21st Conference on Composites, Materilas, and Structures, Cocoa Beach, Florida:Jan. 29, 1997:TPSX Ref. #50.

General References:

  • N/A