2020
DOI: 10.1007/s42405-020-00267-6
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Ablation Experiments of Ultra-High-Temperature Ceramic Coating on Carbon–Carbon Composite Using ICP Plasma Wind Tunnel

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Cited by 17 publications
(10 citation statements)
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“…The main reason is that the volume content of axial fiber rod and radial fiber bundle in RVE decreases while the volume fraction of matrix increases with the increase of braiding distance. Since the modulus and CTE of the matrix are lower than that of the fiber rod and fiber bundle, the increase of the volume fraction will inevitably lead to the overall decrease of the modulus and CTE [ 28 , 29 , 30 , 31 , 32 , 33 ].…”
Section: Calculation Results and Analysismentioning
confidence: 99%
See 3 more Smart Citations
“…The main reason is that the volume content of axial fiber rod and radial fiber bundle in RVE decreases while the volume fraction of matrix increases with the increase of braiding distance. Since the modulus and CTE of the matrix are lower than that of the fiber rod and fiber bundle, the increase of the volume fraction will inevitably lead to the overall decrease of the modulus and CTE [ 28 , 29 , 30 , 31 , 32 , 33 ].…”
Section: Calculation Results and Analysismentioning
confidence: 99%
“…The pores and cracks in the matrix and interface of the axial braided C/C composite were regarded as inclusions with different shapes and sizes and introduced into the pure carbon matrix. In this paper, the random geometric models meeting objective distribution law of microstructure characteristics were generated by a subroutine coded by python and its mechanical properties were calculated by FEM, which can consider the interaction between various microstructures [28][29][30][31][32].…”
Section: Mechanical Properties Of Matrix and Interfacementioning
confidence: 99%
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“…However, the surface of the new aircraft will cause serious aerodynamic heating problems due to the shock wave and viscous effect during the reentry process. Under the coupling effect of high temperature and complex aerodynamic loads, the probability of failure of TPS covering the surface of the aircraft is much higher than that of general structures [3][4] . Once the TPS is destroyed and high thermal airflow enters the interior of the aircraft, it is possible to cause the overall failure of the reusable launch vehicle during the reentry process.…”
Section: Introductionmentioning
confidence: 99%