2020
DOI: 10.1080/09243046.2020.1790124
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Effects of residual Si on the ablation properties of biomorphic C/SiC composites for reusable thermal protection systems

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Cited by 4 publications
(2 citation statements)
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“…The C/SiC composite have already been applied in hot-section components in spacecraft thermal protection systems and rocket engines, for example, nose cap, vanes, and nozzles. [4][5][6] Under cyclic-fatigue loading, multiple coupled damage mechanisms contributed to the fatigue degradation in C/SiC composites. [7][8][9][10]12 conducted experimental and theoretical investigations on the cyclic-fatigue behavior in unidirectional (UD) and cross-ply (CP) C/SiC composite at room temperature.…”
Section: Introductionmentioning
confidence: 99%
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“…The C/SiC composite have already been applied in hot-section components in spacecraft thermal protection systems and rocket engines, for example, nose cap, vanes, and nozzles. [4][5][6] Under cyclic-fatigue loading, multiple coupled damage mechanisms contributed to the fatigue degradation in C/SiC composites. [7][8][9][10]12 conducted experimental and theoretical investigations on the cyclic-fatigue behavior in unidirectional (UD) and cross-ply (CP) C/SiC composite at room temperature.…”
Section: Introductionmentioning
confidence: 99%
“…At 1000°C, the torque was 3758 ± 855 N m and the torsion shear strength was 38.1 ± 8.7 MPa; and the flexural moment was 3127 ± 588 N m and the flexural strength was 63.9 ± 12 MPa. The C/SiC composite have already been applied in hot‐section components in spacecraft thermal protection systems and rocket engines, for example, nose cap, vanes, and nozzles 4–6 …”
Section: Introductionmentioning
confidence: 99%