High-performance structural microwave absorbing ceramic matrix composites represent an ideal candidate for achieving the integration of broadband wave absorption and high load-bearing capacity in aerospace high-temperature components. Taking the multi-scale collaborative design of macro-meso-micro levels as the core research approach, this paper systematically summarizes the fundamental design principles of high-performance structural microwave absorbing composites. From the perspective of material design, it comprehensively considers the optimal balance between impedance matching and electromagnetic loss to achieve broadband and efficient absorption of electromagnetic waves. The study deeply investigates the influence mechanisms of micro-component materials (such as SiC, Si3N4, ceramic matrices, and carbon nanotubes, metal oxides as absorbers) on the microwave absorbing performance of composites. It also analyzes the key roles of typical macro-mesoscopic configurations (such as layered structures, porous structures, and fiber-reinforced structures) in regulating electromagnetic wave absorption. By establishing correlation models between multi-scale structures and performance, a series of optimized design methods for high-performance SACMCs are summarized, covering material composition selection, structural parameter optimization, and other dimensions. This research provides critical theoretical foundations and practical guidance for the integrated design and performance evaluation of high-temperature broadband microwave absorbing systems in the new generation of aerospace vehicles. It holds significant implications for promoting the collaborative development of stealth technology and structural materials in the aerospace industry.

Due to their excellent high-temperature performance and lightweight properties, SiC/SiC composites are widely used in high-temperature components of aerospace engines. However, defects like porosity and delamination can occur during their fabrication, affecting material performance and necessitating efficient non-destructive testing methods. Extensive research indicates that CT inspection is one of the most effective methods for detecting defects in SiC/SiC composites. Traditional CT scanning often requires several hours, leading to high time consumption and costs. In contrast, the fast scan mode continuously exposes the sample during rotation, significantly reducing scanning time. While fast scanning may introduce issues like image trailing and noise, this study compares image resolution, noise distribution, and defect detection capabilities across different scanning modes. It proposes methods to optimize scanning parameters, aiming to enhance detection efficiency without compromising image quality. Experimental results indicate that fast scan technology can substantially increase scanning speed without significant loss in spatial resolution. Although image noise increases as the number of projections decreases, adjusting parameters such as current can effectively mitigate noise effects. The study concludes by proposing strategies to balance image resolution, noise, and scanning time, providing technical support for fast scan of industrial CT testing for SiC/SiC composites.

In this paper, the damage forms and failure mechanisms of two kinds of composite materials, aramid fibres and glass fibres, used for the casing containment ring under different impact energy are investigated through lowspeed impact tests. The test results show that when the impact energy is 36 J, the energy absorption capacity of aramid fibre and glass fibre composites is similar, and the damage of the two kinds of composites is dominated by matrix cracking. When the impact energy is increased to 117 J, the failure forms of the composites are mainly in the form of fibre tensile fracture and delamination damage, and the aramid fibre composites show better energy-absorbing ability through fibre fracture and delamination under high energy impact.

Fiber metal laminates (FMLs) are widely used in fields such as aerospace and rail transit due to their excellent comprehensive mechanical properties. FMLs are subjected to varying degrees of impact during application. Compared to high-velocity impact, the damage caused by low-velocity impact is mostly imperceptible to the naked eye, but it can still cause irreversible damage such as cracks and delamination, posing safety hazards. Therefore, research on lowvelocity impact damage of FMLs cannot be ignored. This paper explores and analyzes the low-velocity impact damage mechanism, influencing factors, and methods to improve the resistance to low-velocity impact of FMLs. It summarizes and discusses the evaluation methods of low-velocity impact performance, damage detection technology, and the current status of numerical simulation research. Finally, it proposes the research hotspots and development directions of future lowvelocity impact of FMLs.

For the typical structure of carbon-fiber-reinforced polyimide resin-based composite T-stringer-stiffened panels, the problem of porosity defects forming inside the local skin at the stringer end due to the difficulty of removing volatile components during co-bonding was addressed through material property and defect control research. To remove volatile components before the curing reaction initiated, differential scanning calorimetry (DSC) was used to determine the curing temperature ranges of the adhesive film and prepreg. Viscosity – temperature curve analysis showed that both materials exhibited low viscosity at 290 ℃, enabling volatile removal via pressure application. Thermogravimetric analysis (TGA) revealed volatile release rates of 67.94% and 88.96% for the adhesive film and prepreg at 290 ℃, confirming the effectiveness of applying pressure at this temperature to remove volatile components within the composite system. Based on the analysis of pore defect mechanisms, a defect control strategy involving stringer end chamfering was proposed. Results showed that this approach effectively mitigated fiber buckling and inhibited porosity formation.

The self-developed carbon fiber spreading equipment was used to prepare spreading carbon fiber (SCF) prepregs with spreading ratios of 2 and 5. The SCF composite laminates were prepared through a hot pressing process. The geometric dimensions of the SCF prepreg tape were characterized from various perspectives, including the spreading ratio, areal density, and thickness. The super-depth microscope was used to investigate the influence of the geometric dimensions of SCF unidirectional prepreg tapes on fiber arrangement defects and surface morphology. Additionally, the wettability of the fiber tapes and the resin impregnation rate were studied. The micromorphology of SCF composite laminates and their fracture morphology under tensile loading were analyzed using SEM. The results indicate that when the fiber spreading ratio increases from 2 to 5, the fiber width expands from 10 mm to 20 mm. At higher spreading ratios, the fibers are largely parallel to each other, with fewer instances of fiber misalignment or slippage; The surface energy of the SCF unidirectional prepreg tape increases, and the resin impregnation rate of the fibers also improves accordingly. The tensile strength of the SCF composite laminate increased by 18.7% at high spreading ratios. The microscopic morphology showed less fiber pullout, a regular tensile fracture surface, and no significant delamination between the fiber layers and the resin.

Carbon fiber-reinforced thermoplastic composites (CFRTP) has emerged as a new generation lightweight structural material, renowned for its exceptional strength-to-weight and stiffness-to-weight ratios, as well as its fatigue resistance. It has become a strategic material in the aerospace industry, replacing traditional metallic  mponents. However, due to significant differences in their physical and chemical properties, integrating multiple lightweight materials in production remains a substantial challenge. Recent studies have comprehensively reviewed the advancements in jointing technologies between metals and CFRTP, encompassing jointing processes, mechanisms, and interface control methods. First, the primary jointing processes and recent advancements in metals and CFRTP were introduced. The principles of thermal interface modification were further elaborated, followed by detailed discussions on mechanical and chemical, interface control methods. Finally, the current state of research and key challenges in jointing between metals and CFRTP have been systematically reviewed and summarized. Future directions have been proposed, offering theoretical and technical support for the lightweight design of next-generation aerospace equipment.

With the growing demand for lightweight and sustainable manufacturing in the aviation industry, thermoplastic composites have emerged as a major alternative to traditional metallic materials due to their high strength, recyclability, and high-efficiency forming characteristics. As a core method for the integrated assembly of thermoplastic composite components, welding technology has thus garnered significant industry attention for its advantages over mechanical fastening and adhesive bonding, including the reduction of fiber damage and enhanced structural integrity. Therefore, this paper systematically reviews the research advances and current applications of thermoplastic composite welding technologies in aviation. It focuses on the process principles, research progress, and aerospace application cases of five key techniques: Laser welding, resistance welding, induction welding, ultrasonic welding, and conduction welding. Additionally, this paper discussed future trends and research priorities for thermoplastic composite welding technologies.

MXene, as a novel two-dimensional material, exhibits significant application potential in the field of electromagnetic interference (EMI) shielding due to its excellent electrical conductivity, mechanical properties, and chemical stability. This paper aims to comprehensively review and analyze recent research progress on MXene composites, systematically establishing the intrinsic relationship between their structural characteristics, preparation techniques, and performance. Firstly, the electromagnetic shielding mechanisms of MXene and its diverse preparation methods are summarized; subsequently, the focus is on the macro-structural design of MXene-based composites, with an in-depth analysis of the effects of thin-film, porous, and gradient structures on their electromagnetic shielding effectiveness. This analysis not only covers the modulation mechanisms of structural morphology on electromagnetic wave absorption, reflection, and scattering behaviors but also reveals the scientific laws of structure-performance relationships. Finally, current challenges faced by MXene-based EMI shielding composites are comprehensively evaluated, and potential opportunities in future research are prospected, aiming to provide scientific guidance for the further development and application of MXene-based electromagnetic shielding materials.

To address the insufficient tensile strength of composite fan blade dovetail roots, a layup design strategy was developed. A finite element model of composite interlayer structures with resin pocket defects was developed to systematically analyze the effect of drop layer angles on structural strength. Additionally, a finite element model of composite dovetails was established to collect stress data of resin pockets in variable-thickness regions, enabling the optimization of layup design parameters based on the analysis. Results show that the interlayer structure strength increases by 28% at drop layer angles of 45° and 90° compared to the 0° condition. Following optimization, the maximum stress in dovetail resin pockets decreased from 121.57 MPa to 50.50 MPa, with overall strain values reduced and stress dispersion and resistance to strain concentration significantly enhanced in critical areas. This study provides a theoretical basis for the design of composite dovetail structures and offers engineering guidance for improving their stability and reliability under real-world operating conditions.