Silicon nitride-based ceramic tools are considered ideal for cutting high-temperature alloys because of their superior hardness, wear resistance and high-temperature stability. However, their lack of toughness limits wider applications. To overcome these challenges, researchers have introduced a variety of reinforced phases into the Si₃N₄-based ceramic tool material system to enhance its comprehensive mechanical properties, and these studies provide theoretical guidance for the design and application of Si₃N₄-based ceramic tools. In this paper, a detailed review of domestic and foreign for Si₃N₄-based ceramic tool material toughening methods, especially focusing on summarizing the improvement effects and mechanisms of various reinforced phases relative to Si₃N₄-based ceramic tool material mechanical properties; on this basis, this paper summarizes the current status of the application of Si₃N₄-based ceramic tools in cutting hightemperature alloys in recent years, and the research direction of Si₃N₄-based ceramic tool material system and tool cutting performance is prospected.

Silicon carbide (SiC) materials are widely used in various fields, including national defense, aerospace, energy, and environmental protection owing to its excellent properties such as lightweight, high-strength, and excellentthermal-stability. However, SiC ceramics face a challenge due to the mutually restrictive relationship between their irregular structure and formability. While traditional manufacturing methods can produce high-performance SiC ceramic parts, forming complex structures remains difficult. On the other hand, additive manufacturing is capable of creating intricate designs, but integrating high strength and toughness into SiC-based ceramics through this method poses significant challenges. Therefore, researching additive manufacturing techniques for SiC structural ceramics that offer high precision, strength, and toughness is of great importance. This paper systematically summarizes the SiC-based ceramics produced by current additive manufacturing methods. It analyzes and discusses SiC-based ceramics reinforced through continuous fibers, short-cut fibers/whiskers, and sandwich structure toughening techniques. Based on the current research status, the article also outlines future development trends, providing valuable insights for advancing high-precision, high-strength, and tough additive manufacturing of large-scale, complex SiC-based ceramic components.

Piezoelectric ceramics are widely applied in fields such as medical imaging, acoustic sensors, acoustic transducers, and ultrasonic motors due to their piezoelectricity, dielectric properties, and elasticity. With the development of electronic devices toward miniaturization and portability, the market demand for small piezoelectric ceramics with complex geometries is gradually increasing. Piezoelectric ceramics manufactured by traditional technology can exhibit good piezoelectric properties, but there are still challenges in manufacturing complex structures. Additive manufacturing technology is a kind of advanced manufacturing technology based on three-dimensional model data and the use of material layer by layer to directly manufacture solid parts. Compared with traditional manufacturing technology, additive manufacturing technology does not require molds, can be designed according to the shape of the device and through the 3D digital model directly manufacturing solid parts, realizing the parts “free manufacturing”, solving the forming problem of many complex structural parts, and greatly reducing the processing procedures, shortening the processing cycle. This paper summarizes the current development of additive manufacturing technology to manufacture piezoelectric ceramics, introduces the progress of piezoelectric ceramics in the field of application, and the research direction and prospects of additive manufacturing piezoelectric ceramic technology at the current stage were discussed.

Al₂O₃/ZrO₂ eutectic ceramics, with excellent high-temperature mechanical properties and structural stability,  ave become potential materials for hot-end components in aero-engines and gas turbines. Laser directed energy deposition (LDED) technology overcomes the limitations of traditional fabrication methods, such as sintering deformation, by directly melting powders to enable the one-step fabrication of complex ceramic components. The application of integral hightemperature assistance can effectively suppress cracking during the fabricating process. However, the effect of high-temperature assistance on the microstructure and properties of the fabricated components remains unclear. This work systematically investigates the evolution of the microstructure and mechanical properties of Al₂O₃/ZrO₂ eutectic ceramics fabricated by LDED with integral high-temperature assistance as a function of the assistance temperature. The results show that the integral hightemperature assistance significantly influences the microstructure and mechanical properties of Al₂O₃/ZrO₂ eutectic ceramics. At an assistance temperature of 1273 K, the grain size of the fabricated sample increases by approximately 32.16% compared to samples manufactured at room temperature. The average fracture toughness is (4.9±0.3) MPa·m^1/2, which represents a 17.2% improvement over room-temperature samples. The flexural strength and compressive strength reach their maximum at an assistance temperature of 773 K, with values of (324.27±18.23) MPa and (354.19±37.53) MPa, respectively.

The controllable distribution of continuous fibers on the rotary surface is the key to realize the high performance manufacturing of continuous fiber honeycomb rotary structure. In this paper, for the complex preparation process of continuous fiber honeycomb rotary structure and the difficulty in accurately controlling fiber distribution, we propose a column surface layered 3D printing method of continuous fiber honeycomb rotary structure, which realizes the controllable distribution of continuous fibers in any direction on the column surface through the path planning of the column surface layering. This method provides support for the integrated manufacturing of complex continuous fiber honeycomb rotary structures. The effects of continuous fiber honeycomb angle and size on the axial compression performance and failure mode of continuous fiber composite honeycomb rotary structures are investigated by column surface path planning. The results show that the angle and size of the continuous fiber honeycomb can be precisely regulated by column surface path planning, which can then control the deformation behavior and failure mode of the continuous fiber honeycomb rotary structure, and optimize the load-bearing performance and energy-absorbing characteristics of the continuous fiber honeycomb rotary structure. This study provides a new process method for high-performance moldless rapid manufacturing of aerospace composite rotary components.

Gyroid type triply periodic minimal surface (TPMS) structures exhibit outstanding performance in stiffness, energy absorption, heat dissipation, and thermal conductivity, making them highly promising for engineering applications such as cushioning and damping systems. However, adjusting the stiffness of TPMS structures often negatively impacts their energy absorption capacity and structural stability. This study proposes a derivative optimization design method that combines Voronoi-based porous structure design with a parameterized Gyroid approach, enabling tunable stiffness control of lattice structures while maintaining advantages in energy absorption and heat dissipation. Lattice structures based on Delaunay and Voronoi cells were fabricated using selective laser sintering (SLS), the effects of seed point distribution changes on the structural morphology and mechanical properties were also analyzed by compression experiments. Additionally, the heat dissipation performance and structural stability of two Voronoi-optimized lattice structures— isosurface columnar lattice structures (ISLS_V) and sheet-like ISLS_V (Sheet-ISLS_V) were investigated. The results demonstrate that the stiffness of the lattice structures can be adjusted by modifying the number and distribution of seed points. Benefiting from the smooth surface characteristics of Voronoi-cell lattices, the Sheet-ISLS_V structure at 1400 seed points exhibited superior strength and energy absorption capacity compared to the Gyroid structure, with a 6.3% increase in energy absorption rate. The optimized design of the Sheet-ISLS_V structure provides valuable insights for TPMS structural optimization and its engineering applications.

The superplastic deformation behavior of rolled TiB_w/TA15 titanium matrix composites at different strain rates in the temperature range of 920–980 ℃ was studied from the phase transition point below 100 ℃. The results show that the rolled TiB_w/TA15 titanium matrix composites exhibit good superplasticity at high temperature, and the best superplasticity at 960 ℃ and strain rate of 0.001 s^–1, the elongation of the composites is as high as 569 %. At the same time, the hyperbolic sinusoidal Arrhenius constitutive equation of the composite was established, and the activation energy of the composite was obtained and the superplastic deformation mechanism was revealed. The microstructure analysis shows that under the optimal superplastic deformation condition, α phase has a significant dynamic recrystallization spheroidization, and there is no obvious cavity in the interior.

Magnesium-lithium alloy, lightweight metal with high specific strength and ductility, is one of the most attractive structural and functional materials for the automotive, aerospace, and defense industries. However, its industrial applications are severely limited by its low strength, and low modulus. Hence, the preparation and processing (alloying, casting, heat-treatment and compounding), and research progress of various types of high-strength, and high-modulus casting Mg–Li alloys were summarized in this paper, which provides new ideas for researchers to develop high-strength and high-modulus Mg–Li alloys. Meanwhile, the advantages and limitation of preparation processes of different types were discussed, and the future development prospect and research direction were proposed. Finally, the development direction of the high-strength and high-modulus casting magnesium-lithium alloy is concluded.

Aiming at the nonlinear error problem caused by linear interpolation of rotation axis and tool axis vector deviation from the theoretical plane in the mirror milling of aviation thin-walled parts, a low-fluctuation interpolation tool axis vector method of rotation axis suitable for mirror milling was proposed to optimize the nonlinear error. Firstly, the motion chain model and nonlinear error model of mirror milling machine tool were established, and the positive correlation between nonlinear error and the motion of the rotation axis of the machine tool was obtained. Then, based on the kinematics of the machine tool, the optimization interval was determined by the nonlinear error constraint and the angular velocity constraint of the axis of rotation. Finally, for the pre-interpolated tool axis vector of the minimum surface of nonlinear error, the pre-interpolation vector corresponds to the discrete rotation axis angle point, and the interpolated tool axis vector satisfying the mirror milling was determined within the allowable range of nonlinear error. After simulation and experiment, the maximum nonlinearity error is reduced by 73.18%, the overall wall thickness error is reduced by 68.24%, and the processing path time is reduced by 4.39%, which effectively verifies the feasibility of the proposed method.

In order to reveal the different damage mechanisms of the 3D–orthogonal C/SiC composite (3D–C/SiC) rudder fins and mental bolt combined structure, and of the carbon cloth stitching C/SiC composite (2D–C/SiC) rudder fins and mental bolt combined structure, interlaminar shear tests and combined bending-torsion loading tests were conducted to investigate the influence of fiber preform configuration on the interlaminar shear and bending-torsion coupled mechanical properties of the 2D–C/SiC composites cut from the low stress area of the corresponding failed rudder fins. The results show that the 2D–C/SiC composites have lower strength property while higher stiffness property compared with the 3D–C/SiC composites. The material test results were compared with the test results of its rudder fins structure, and the reason for the very low strength of the combined 3D–C/SiC composite fins and bolt structure were analyzed. It is show that the applied load on dangerous section of the rudder fins structure is shared by the rudder shaft and the bolt. According to the basic principle in combined structure that the load is distributed based on the stiffness ratio of the components, the load borne by 3D–C/SiC composite rudder shaft with lower density and stiffness is inevitably lower, and the bolt yields early due to its relatively higher load, thus reducing the load-bearing strength of the combined structure.

Multi-stations integral measurement field is currently the most effective method for large-scale 3D measurement in manufacturing plants. The accuracy evaluation of the method is of great significance for ensuring the reliability of measurement results and the rationality of measurement task planning. To fuse the multi-source observation data in the integral measurement field accuracy evaluation process, a model based on geometric constraints was established, and an accuracy evaluation method for integral measurement fields was proposed. Indicators such as instrument observation uncertainty, instrument pose parameter uncertainty, and point coordinate uncertainty were included in the accuracy evaluation method. Firstly, a rapid and accurate assessment of the instrument observation on-site uncertainty was implemented based on the statistical information of the measurement results. Then the uncertainty propagation process was analyzed using the method recommended in guide to the expression of uncertainty in measurement (GUM), and evaluation methods for the uncertainty of instrument pose parameters and target point coordinates were established. Finally, the rationality of the integral measurement field accuracy evaluation method was verified through simulation and on-site experiments.

In order to achieve uniform surface finishing of aero-engine blades and improve the performance of aeroengine compressor blades, the influence of container configuration and blade installation attitude on polishing effect was studied based on discrete element numerical simulation. The results show that within the range of experimental parameters, when the container height is 124 mm, the container width is 120 mm, the container length is 80 mm, and the blade surface is installed at 90° with the vibration direction, the wear depth and uniformity of the compressor blade finishing are better, which is the optimal container configuration size and installation attitude parameters. After finishing the compressor blade according to the optimal parameters obtained from the simulation, the surface burr and forged oxide of the compressor blade were removed; The sharp edge is passivated, the edge is rounded and neat; The surface is bright. The roughness grade of the blade surface is greatly improved, and the key dimensions of the blade are within the allowable range. The stress state is improved. The research method and results lay a foundation for the efficient and low-cost processing of compressor blades.