
Fiber volume percent: 40-45%
Fiber volume percent hoop: 45% ± 5
Fiber volume percent axial: 36% ± 4
Fiber volume percent radial: 19% ± 4
Bulk density: ≥ 1.9 (g/cm )
Tensile strength (hoop): ≥ 100 MPa
Tensile strength (axial): not tested MPa
Compressive strength (hoop): ≥ 80 MPa
Compressive strength (axial): ≥ 71 MPa
Thermal conductivity (hoop): ≥ 40 W/m.K at 900 °C
Thermal conductivity (axial): ≥ 22 W/m.K at 900 °C
Thermal expansion: < 3.1 1/ºC*10 -6
Open porosity: < 5%
Carbon Content: 99.9%
Graphitization Temperature: @ 2500 °C
The carbon-carbon composite throat in missile technology is a critical component used in the nozzle section of rocket and missile engines. These throats are subjected to extremely harsh conditions, including high temperatures, corrosive gases, and intense pressures during rocket engine operation. The use of carbon-carbon composites in this application offers several distinct advantages:
High Temperature Resistance:
High Thermal Conductivity:
Erosion and Ablation Resistance:
Strength and Lightweight:
Fatigue Resistance:
Carbon-carbon composite throats are an example of advanced materials engineering providing substantial benefits in demanding aerospace applications, particularly in improving the performance and reliability of missile technology.
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