Manufacturing ZrB₂-SiC-TaC Composite: Potential Application for Aircraft Wing Assessed by Frequency Analysis through...

Aerospace engineering requires materials that can withstand extreme conditions while maintaining structural integrity. Traditional materials like aluminum alloys have limitations in high-temperature environments. Composite materials offer potential improvements in thermal and mechanical performance. However, the behavior of ultra-high-temperature composites under vibrational loads remains unclear. Prior research has shown that zirconium diboride (ZrB2) and silicon carbide (SiC) composites exhibit high thermal resistance. No prior work had resolved how these materials perform in aircraft wing designs. This gap motivated the investigation of ZrB2-SiC-TaC composites. The study aimed to assess the feasibility of using such composites in aircraft wings. Understanding the vibrational response is key to evaluating structural behavior. The research focused on frequency analysis using finite element modeling. The goal was to compare the composite with conventional materials like aluminum 2024-T3.

The study aimed to evaluate the potential of a ZrB2-SiC-TaC composite for use in aircraft wings. The researchers focused on the composite's mechanical and thermal properties. They sought to determine how the material would perform under vibrational loads. The specific problem addressed was the lack of data on the composite's application in aerospace structures. The motivation came from the need for materials that can endure high temperatures and mechanical stress. The team used a finite element model to simulate the vibrational behavior of aircraft wings. They compared the composite with traditional materials like aluminum 2024-T3. The goal was to assess whether the composite could improve wing performance.

The composite was fabricated using spark plasma sintering with ZrB2, SiC, and TaC in 70%, 20%, and 10% volume ratios. The sintering was conducted at 2000 °C under 30 MPa pressure for 5 minutes. The resulting material was analyzed using X-ray diffraction and field-emission scanning electron microscopy. Nano-indentation tests were performed to evaluate mechanical properties. X-ray fluorescence and X-ray photoelectron spectroscopy confirmed the composition. The composite was tested for rigidity, elastic modulus, and thermal resistance. A finite element model in ABAQUS simulated the vibrational behavior of aircraft wings. Three material cases were considered: leading edge, full wing, and aluminum 2024-T3. Static analysis verified the model's accuracy by measuring deformation and stress.

The composite achieved a rigidity of 23,356 MPa, an elastic modulus of 403.5 GPa, and a thermal resistance of 3100 °C. The microstructure was fully dense with minimal oxide contamination. The finite element model showed improved vibrational responses in the ZrB2-SiC-TaC wing. The natural frequency of the composite wing was higher than that of aluminum 2024-T3. The leading edge made of the composite also showed better performance. The static analysis confirmed the model's accuracy in predicting deformation and stress. The results were compared to published literature to validate the FEM approach. The composite significantly enhanced the structural behavior of the aircraft wing.

The study demonstrated that the ZrB2-SiC-TaC composite can improve the vibrational and structural behavior of aircraft wings. The material's high rigidity and thermal resistance make it suitable for aerospace applications. The finite element model accurately predicted the composite's performance. The results suggest that the composite outperforms traditional materials like aluminum 2024-T3. The researchers propose that the composite could be used in high-temperature environments. The study supports the use of the composite in leading edge and full wing designs. The findings align with the literature, confirming the model's validity. The composite shows potential for future aerospace material applications.