Composites of carbon fiber-reinforced silicon carbide (Cf/SiC) with ultra-high temperature ceramics (UHTCs) exhibit superior resistance to oxidation and ablation under high temperatures. Components in large-scale applications often have complex geometries, making it crucial to understand the oxidation and ablation behaviors of curved and non-uniform surfaces. In this study, a Cf/SiC-ZrB2 composite was fabricated into a 300 mm cylindrical shape using filament winding and liquid silicon infiltration processes. The resulting specimens exhibited a uniform microstructure, with SiC and ZrB2 crystals evenly distributed across the top and bottom surfaces, demonstrating the feasibility of producing large-scale composites. The specimens underwent an oxyacetylene torch test at 2,100 K for 5 min to assess their ablation and oxidation performance. The results revealed significant variation in the oxide layer due to the non-flat surface, with the layer thickness gradually decreasing as the oblique angle was reduced. Additionally, the presence of high-melting-point ZrO2 in the oxide layer near the torch center was attributed to the migration and solidification of molten SiO2. This suggests that large and complex Cf/SiC incorporating UHTCs can effectively form a protective oxide layer, even under conditions where SiO2 displacement occurs. The findings underscore the importance of integrating geometric considerations into the design of ultra-high temperature ceramic composites to achieve the thermal and ablation resistance required for advanced high-temperature applications.

Since electric energy is used in industry, mass production and various conveniences are provided. To provide convenience for the construction and operation of such electric energy transmission and distribution facilities, it is increasing that the demand for special purpose vehicles, that is, telescopic aerial work platform vehicles. When working active electric work using the telescopic aerial work platform vehicles, due to active electric work is inevitable, it is essential to ensure insulation performance for the safety of the operator. In this paper, we study the design and development of mechanical properties for filament winding process of glassfiber/epoxy composite, it is required to boom of telescopic aerial work platform vehicles. The glass fiber/epoxy composite filament winding process and its mechanical properties were evaluated to replace the existing ATOS80 boom. By filament winding process it was obtained the mechanical properties required for the design analysis of the glass fiber/epoxy composite boom. Using this, the insulated boom for the 30m class aerial work vehicle was designed and was manufactured by applying the filament winding process. The fabricated composite boom was evaluated by the static strength test to meet the required strength. The maximum displacement was 84mm and the crack occurred at the maximum load of 8981N. It satisfied the maximum lifting load of 4900N and 210mm the maximum displacement required for the boom.