Journal Article10.1016/J.COMPOSITESB.2012.07.007
ZrB2/SiC as a protective coating for C/SiC composites: Effect of high temperature oxidation on mechanical properties and anti-ablation property
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TL;DR: In this paper, a new type of oxidation protective coating (ZrB 2 /SiC coating) was produced on C/SiC composites by precursor infiltration and pyrolysis (PIP), which is a simple and low cost method; the coating was ZrB2 2 mixed with SiC, which was fabricated by painting slurry on the surface of the composite followed by chemical vapor deposition (CVD) SiC on the top Mechanical tests were conducted before and after oxidation test Anti-ablation property was tested under oxy-acetylene torch Oxidation
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Abstract: C/SiC composites are raising great interest as a thermal shielding for aerospace applications, provided that they are protected from oxidation by suitable coatings Conversely, ultra high temperature ceramics, and in particular ZrB 2 , is among the best oxidation resistant materials as known A new type of oxidation protective coating (ZrB 2 /SiC coating) was produced on C/SiC composites The composites were produced by precursor infiltration and pyrolysis (PIP), which is a simple and low cost method; the coating was ZrB 2 mixed with SiC, which was fabricated by painting slurry on the surface of the composite followed by chemical vapor deposition (CVD) SiC on the top Mechanical tests were conducted before and after oxidation test Anti-ablation property was tested under oxy-acetylene torch Oxidation test shows that the uncoated samples are oxidized quickly and the weight loss reaches 292% and the reservation of original flexural strength is only 674%, while the weight loss of ZrB 2 /SiC coated samples is only 519%, and the reservation of original flexural strength is 374% ZrB 2 /SiC coating can provide longtime protection for C/SiC composites at 1973 K Compared with the uncoated composites, the linear and mass ablation rates of the coated composites decreased by 621% and 461%, respectively, after ablation for 30 s The formation of zirconia and silicon dioxide from the oxidation of ZrB 2 /SiC improved the ablation resistance of the composites, because of the evaporation at elevated temperature, which absorbed heat from the flame and reduced the erosive attack to carbon fibers and SiC matrix
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Citations
UHTC composites for hypersonic applications
Anish Paul,Jon Binner,Bala Vaidhyanathan +2 more
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TL;DR: In this paper, the authors propose a hypersonic vehicle that can take off from an airport, fly through the atmosphere, and travel to the other side of the earth at high speeds, and then return through the same or another airport.
Review of thermal stability of nanomaterials
TL;DR: In this paper, current developments in kinetic and thermodynamic stabilization of grains in nanostructured metals, alloys, and compounds are generalized and discussed in detail, along with experimental information about behavior of nanomaterials subjected to radiation or oxidation.
199
Preparation and properties of carbon fiber reinforced ZrC–ZrB2 based composites via reactive melt infiltration
TL;DR: In this paper, carbon fiber reinforced ZrC-ZrB 2 based composites, which were prepared by reactive infiltration of zirconium into a porous C/C-B 4 C preform, had the density of 3.07 kg/cm 3, the open porosity of 9.1% and the flexural strength of 147 MPa.
63
In-situ synthesis of SiC-ZrB2 coating by a novel pack cementation technique to protect graphite against oxidation
Jalil Pourasad,Naser Ehsani +1 more
TL;DR: In this article, a multiphase coating was prepared on a graphite substrate by a two-step technique to enhance the oxidation protection ability of graphite, where the first step was to obtain a functionally graded SiC layer and the second one was to develop a SiC-ZrB 2 coating by an in-situ reaction method with Zr, Si and B 4 C powders.
62
ZrB 2 particles reinforced glass coating for oxidation protection of carbon/carbon composites
TL;DR: In this article, a dense ZrB2/SiO2 coating was prepared on the SiC coated carbon/carbon composites by a facile sol-dipping approach, which could protect the composites from being oxidized for 160 h at 1773 K with a weight loss of 6.9 mg/cm2.
References
Oxidation-based materials selection for 2000°C + hypersonic aerosurfaces: Theoretical considerations and historical experience
TL;DR: In this article, a compositional approach was proposed to improve the oxidation resistance of ZrB2-SiC and other non-oxide materials to at least 1600°C by compositional modifications which promote immiscibility in the glass component of the scale.
937
Mechanical, Thermal, and Oxidation Properties of Refractory Hafnium and zirconium Compounds
TL;DR: In this paper, the thermal conductivity, thermal expansion, Youngs Modulus, flexural strength, and brittle-plastic deformation transition temperature of ZrB2, HfC 0·98 and HfN 0·92 ceramics were determined.
799
Evaluation of ultra-high temperature ceramics foraeropropulsion use
Stanley R. Levine,Elizabeth J. Opila,Michael C. Halbig,James D. Kiser,Mrityunjay Singh,Jonathan A. Salem +5 more
TL;DR: In this article, the authors examined three UHTC materials under conditions more representative of a propulsion environment, i.e., higher oxygen partial pressure and total pressure, and showed that these materials offer a good combination of properties that make them candidates for airframe leading edges on sharp-bodied reentry vehicles.
795
Thermodynamic Analysis of ZrB2–SiC Oxidation: Formation of a SiC-Depleted Region
TL;DR: In this article, a thermodynamic model was developed to explain the formation of a SiC-depleted layer during ZrB2-SiC oxidation in air at 1500°C.
458
Processing, properties and arc jet oxidation of hafnium diboride/silicon carbide ultra high temperature ceramics
TL;DR: In this article, the processing and properties of HfB2-20 vol%SiC ultra high temperature ceramics were examined and it was concluded that passive oxidation of SiC plays a role in determining the steady-state surface temperatures below 1700°C.
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