A novel Y₄Al₂O₉/Y₂O₃ composite exhibits substantial resistance to CMAS infiltration at both temperatures at 1300 ℃ and 1500 ℃, without notable grain-boundary penetration by CMAS glass. More importantly, the incorporation of reaction active compositions in the composite accelerated the consumption of molten CMAS constituents and reduced its corrosive activity, which is recognized as the crucial principle for composition design of anti-CMAS materials. This work provides valuable insights that guide the design of composition and advancement of superior CMAS-resistant materials.

Hypersonic vehicles face critical aerodynamic heating during flight, demanding advanced thermal protection systems (TPS). A team of Chinese researchers has developed a novel carbon-bonded carbon fiber (CBCF) composite modified with SiBCN ceramics (CBCF/SiBCN), enabling efficient in-plane heat dissipation while maintaining thermal insulation. The composite exhibits exceptional anisotropic thermal properties and mechanical strength, addressing long-standing limitations in traditional CBCF materials for aerospace TPS.

The combustion chamber temperature of the new generation aircraft engines can reach an ultra-high temperature of 1800 °C, making temperature monitoring of key components crucial. Thin-film thermocouples (TFTCs) are highly sensitive and have rapid response time; however, their upper temperature limit remains below 1800 °C. This study proposes an ultra-high temperature film thermocouple, enhanced by yttria-stabilized zirconia (YSZ) for positive film, indium oxide (In₂O₃) for negative film, aluminium oxide (Al₂O₃) for protect film. The thermocouple is designed based on temperature measurement principles, First-principles, and simulations, and it is manufactured via screen-printing. The results indicate that the maximum working temperature is 1850 ℃. In experiments with different doping ratios at 1800 ℃, the thermocouple achieves a maximum temperature electromotive force (TEMF) of 258.5 mV and a maximum Seebeck coefficient of 180.9 μV/°C, with an In₂O₃:YSZ92(ZrO2:Y₂O₃ = 92:8 wt%) ratio of 9:1 wt%. Using the lumped heat capacity method, the response time is measured at 2.8 ms, demonstrating good dynamic response characteristics. The film thermocouple is successfully utilized to measure the gas temperature of 1090 °C at the outlet of air turbine rocket engine, confirming its high-temperature operational capability. To improve the repeatability of the TFTCs without affecting their thermoelectric outputs, a CNN-LSTM-attention neural network is implemented to mitigate repeatability errors, achieving a high repeatability of 99.53%. Additionally, the compensated temperature data are compared with those obtained from a standard B-type thermocouple, showing a full-scale error of ±0.73% FS. This study provides a feasible solution for ultra-high temperature measurements.