SiC/SiC ceramic matrix composite (CMC) reinforced with Hi-Nicalon S silicon carbide fibers in a dense SiC matrix, produced via chemical vapor infiltration (CVI) combined with polymer infiltration and pyrolysis (PIP). This cross-ply laminate architecture ([0/90]₂) delivers excellent damage tolerance and thermal stability compared to monolithic ceramics. Used in extreme-temperature structural applications where thermal shock resistance, light weight, and retention of strength at elevated temperatures are critical, particularly in aerospace propulsion (engine hot sections) and next-generation power generation systems; offers a significant advantage over superalloy alternatives by operating at higher temperatures while maintaining lower density.
Compliance & Regulations
Fiber Direction
Ply Schedule
Laminate Code
[0/90/0/90]T
Fiber angles relative to the 0° reference direction (red arrow in 3D view). 0° = longitudinal, 90° = transverse, ±45° = shear paths.
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Ultimate Tensile Strength(σUTS) | 350.0 | MPa | — | ||
Young's Modulus(E) | 230.0 | GPa | — |
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Maximum Service Temperature(Tmax) | 1,573 | K | — | ||
Thermal Conductivity(k) | 12.00 | W/(m·K) | — | ||
Coefficient of Thermal Expansion(α (CTE)) | 0.00000450 | 1/K | — |
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Density(ρ) | 2.500 | kg/m³ | — |