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Magnesium alloys have received a lot of attention in aerospace, automotive, electronic communications and other fields due to their low density, high specific strength and damping performance. However, magnesium alloy sheets prepared by conventional thermomechanical processing usually have a strong basal texture, resulting in poor formability. In this paper, Mg–Mn–Ce alloys with good plastic forming ability were prepared by studying and optimizing the annealing process. Under the low-temperature annealing condition, it can promote the static recrystallization and grain refinement of Mg–Mn–Ce alloy, and also eliminate the internal stress. With the increase of annealing temperature, a large amount of dispersed Mg12Ce as a stable second phase effectively hindered the grain boundary migration, while the nanoscale α-Mn forms a fine second phase to inhibit grain growth, and both of them together greatly stabilize the deformation structure of the alloy, and maintain a good grain organization under the condition of annealing temperature of 300 °C and holding time of 30 min. The present work also improves the Arrhenius constitutive equation for the Mg–Mn–Ce alloy with respect to the degree of deviation, which significantly improves the accuracy of the model in predicting the thermoforming behavior. Meanwhile, to address the shortcomings of the traditional forming method of magnesium alloy, the processing process of spreading the centrifugal casting tube flat is proposed, the forming process is simulated, and the location of easy breakage in the forming process is predicted. These findings provide microanalytical support for the improvement of forming properties of magnesium alloys by annealing.

Magnesium-manganese series alloys, as materials with very low-density value, have excellent mechanical properties and corrosion resistance, and have broad prospects in automotive, aerospace, biomedical and other fields. In this work, the thermal deformation behavior and microstructural evolution of Mg–Mn–Ce alloys were investigated through uniaxial hot stretching experiments on Mg–Mn–Ce alloy plates under different deformation conditions, with the main focus on the plastic deformation mechanism of Mg–Mn–Ce alloys under different forming conditions. The unified viscoplastic constitutive equation for coupled damage is developed and compared with different types of constitutive equation models. Remarkably, the decrease in peak stress with increasing temperature or decreasing strain rate in Mg–Mn–Ce alloys is due to the fact that the internal slip system of the material is more easily activated with increasing temperature. As the temperature increases, the dislocations within the material decrease, which is due to the fact that the temperature increase makes the DRX action progressively stronger than the dislocation action, and the DRX leads to a significant coarsening of the grains at 573 K. In addition, the fracture behavior of the alloy under different deformation conditions has also been investigated, and the fracture pattern of Mg–Mn–Ce alloys transitions from pronounced cleavage fracture to the appearance of dimples and finally to ductile fracture with a large number of dimples as the temperature increases.

Carbon fiber composite fan blade (CFCFB) is gradually applied to aerospace because it possesses less density and high strength than metal materials. However, the flexural property of conventional CFCFB is generally limited due to centrifugal and aerodynamic flexural stresses. Herein, a bionic gradient double-twisted structure (BGDTS), which was composed of different modulus carbon fiber prepreg gradient structure (inspired by metopograpsus frontalis cheliped tip) and double-twisted (inspired by coelacanth scale) layup structure was designed. Besides, the flexural properties of laminates with different structures and materials were tested, and the 3D Hashin failure criterion was used for simulation analysis. The experimental and simulation results showed that bionic gradient double-twisted structure laminate (BGDTSL) had the best flexural performance (peak flexural force 1125.12 N). Then, the excellent moulding accuracy of CFCFB was verified by the three-dimensional scanning test (moulding accuracy less than 0.56 mm). Among, the tip, middle, and root peak flexural force of the BGDTS-CFCFB were 7022 N, 3327 N, and 5184 N, which increased by 9.27%, 4.59%, and 14.31% compared with traditional structure CFCFB prepared by T800 (TS-CFCFB@T800). The researches in this work offer a prospective way to effectually devise and manufacture exquisitely structured CFCFBs that are more suitable for aeronautical engineering.