A castable, moldable, or extrudable magnesium-based alloy that includes one or more insoluble additives. The insoluble additives can be used to enhance the mechanical properties of the structure, such as ductility and/or tensile strength. The final structure can be enhanced by heat treatment, as well as deformation processing such as extrusion, forging, or rolling, to further improve the strength of the final structure as compared to the non-enhanced structure. The magnesium-based composite has improved thermal and mechanical properties by the modification of grain boundary properties through the addition of insoluble nanoparticles to the magnesium alloys. The magnesium-based composite can have a thermal conductivity that is greater than 180 W/m-K, and/or ductility exceeding 15-20% elongation to failure.

A castable, moldable, or extrudable magnesium-based alloy that includes one or more insoluble additives. The insoluble additives can be used to enhance the mechanical properties of the structure, such as ductility and/or tensile strength. The final structure can be enhanced by heat treatment, as well as deformation processing such as extrusion, forging, or rolling, to further improve the strength of the final structure as compared to the non-enhanced structure. The magnesium-based composite has improved thermal and mechanical properties by the modification of grain boundary properties through the addition of insoluble nanoparticles to the magnesium alloys. The magnesium-based composite can have a thermal conductivity that is greater than 180 W/m-K, and/or ductility exceeding 15-20% elongation to failure.

Aluminum-magnesium-manganese-zirconium-inoculant alloys that exhibit high strength, good ductility, high creep resistance, high thermal stability and durability.

A method of optimising one or more physical properties of an alloy comprises conducting a plurality of trials per an experimental design on a plurality of candidate alloys. Each trial comprises measuring a plurality of values of each physical property of the candidate alloys for different values of a plurality of parameters, wherein the parameters comprise respective concentrations of the two or more constituents, and one or more process parameters. The method further comprises fitting the plurality of values of the physical property and the plurality of parameters to a response surface model; and determining, from the fitted response surface model, optimised values of the parameters that optimise the respective responses; wherein the response surface model describes a non-linear relationship between a time integral of each of the physical property and a linear combination of non-linear functions of the plurality of parameters.

A method of optimising one or more physical properties of an alloy comprises conducting a plurality of trials per an experimental design on a plurality of candidate alloys. Each trial comprises measuring a plurality of values of each physical property of the candidate alloys for different values of a plurality of parameters, wherein the parameters comprise respective concentrations of the two or more constituents, and one or more process parameters. The method further comprises fitting the plurality of values of the physical property and the plurality of parameters to a response surface model; and determining, from the fitted response surface model, optimised values of the parameters that optimise the respective responses; wherein the response surface model describes a non-linear relationship between a time integral of each of the physical property and a linear combination of non-linear functions of the plurality of parameters.

The present disclosure discloses a method for preparing large-size rare earth magnesium alloy with high-performance ingots by short process severe plastic deformation. When in use, the pushing cylinder moves upward, and the back pressure plate is adjusted to the outlet of the extrusion deformation area. After the male mold stroke is completed, the recoverable discard block fills the extrusion deformation area, and the upsetting extrusion deformation is completed. Then, the pushing cylinder drives the back pressure plate to remove from the lower part of the lower mold cavity downward, and the recoverable discard block has been broken due to the high pressure. Then, the extruded blank and residual block powder are taken out from the lower part of the lower mold cavity, restored into a plate shape for the next use. The present disclosure can solve the tail shrinking phenomenon, save materials and increase the strengthening effect.

The present disclosure discloses a method for preparing large-size rare earth magnesium alloy with high-performance ingots by short process severe plastic deformation. When in use, the pushing cylinder moves upward, and the back pressure plate is adjusted to the outlet of the extrusion deformation area. After the male mold stroke is completed, the recoverable discard block fills the extrusion deformation area, and the upsetting extrusion deformation is completed. Then, the pushing cylinder drives the back pressure plate to remove from the lower part of the lower mold cavity downward, and the recoverable discard block has been broken due to the high pressure. Then, the extruded blank and residual block powder are taken out from the lower part of the lower mold cavity, restored into a plate shape for the next use. The present disclosure can solve the tail shrinking phenomenon, save materials and increase the strengthening effect.

The present disclosure intends to provide an aircraft member having both high strength and good ductility. Further, the present disclosure intends to provide an aircraft member satisfying required flame resistance. Further, the present disclosure intends to provide an aircraft member satisfying required corrosion resistance. In a method of manufacturing the aircraft member according to the present disclosure, a billet of an Mg—Al—Ca based alloy is extruded at an extrusion temperature that is higher than or equal to 350° C. and lower than or equal to 400° C. and at a ram rate that is higher than or equal to 1 mm/sec and lower than or equal to 3 mm/sec.

The present disclosure intends to provide an aircraft member having both high strength and good ductility. Further, the present disclosure intends to provide an aircraft member satisfying required flame resistance. Further, the present disclosure intends to provide an aircraft member satisfying required corrosion resistance. In a method of manufacturing the aircraft member according to the present disclosure, a billet of an Mg—Al—Ca based alloy is extruded at an extrusion temperature that is higher than or equal to 350° C. and lower than or equal to 400° C. and at a ram rate that is higher than or equal to 1 mm/sec and lower than or equal to 3 mm/sec.

The disclosure discloses a high-speed spinning magnesium alloy and a preparation method thereof, the magnesium alloy has Mg—Al—Zn—Mn—Sr alloy with a high formability and high strength, and its chemical composition mass percentage is: Al: 2.4-4.5 wt. %; Zn: 0.6-1.2 wt. %; Mn: 0.4-0.6 wt. %; Sr: 0.15-0.3 wt. %; the balance is Mg. The present disclosure adopts the principle that by increasing the content of Mn in the magnesium alloy, a large amount of Mn-rich phase is generated during the alloy preparation process, and the degree of subcooling is controlled so that a fine spherical dispersed nano-scale Mn-rich phase is obtained during the solidification process. The nano-scale Mn-rich precipitate phase can pin the grain boundaries and inhibit the grain boundary migration to refine grains and achieve the effect of improving the strength. The divorced eutectic Mg.sub.17Al.sub.12 phase generated during the casting process will deteriorate the structure, so Sr is added to the alloy, Sr combining with Al to suppress the coarse phase of divorced eutectic Mg.sub.17Al.sub.12, refine the grains, increase the amount of eutectic, and reduce the risk of thermal cracking of large-size cast bars. In addition, Sr weakens the texture during the high-temperature spinning forming process and reduces the risk of cracking during the spinning tension, which is beneficial to high-speed spinning forming.