A method includes fabricating a part out of composite material including fiber reinforcement densified by a metal matrix.

A method includes fabricating a part out of composite material including fiber reinforcement densified by a metal matrix.

A method of forming a metal matrix composite component comprises: providing a body defining a mould cavity; covering a first surface of the mould cavity with a first reinforcement material; restraining the first reinforcement material relative to the body to restrict movement of the first reinforcement material in the mould cavity; adding a second reinforcement material to the mould cavity, the second reinforcement material being in contact with the first reinforcement material; adding molten metal to the mould cavity such that the first reinforcement material and the second reinforcement material become embedded in a continuous metal matrix when the molten metal solidifies.

The invention relates to a preparation method for a magnesium matrix composite. The preparation method comprises the following steps: (1) preparing magnesium ingots as raw materials and salt flux and reinforcements; (2) placing the salt flux in a crucible, performing heating to prepare salt flux melts, adding the reinforcements; (3) performing pouring into a normal-temperature crucible, and performing cooling to obtain precursors; (4) adding the raw materials in an iron crucible, and performing melting at 953K-1043K; (5) placing the precursors in raw material melt, after stirring, under a condition of 953K-993K, performing standing so that scum and melt are obtained; and (6) removing the scum, lowering temperature to 973K-982K, and performing casting. The method provided by the present invention is simple in process and low in cost. The method can be used for preparing bulk structural members of the magnesium matrix composite, and can be used for automatic production.

The invention relates to a preparation method for a magnesium matrix composite. The preparation method comprises the following steps: (1) preparing magnesium ingots as raw materials and salt flux and reinforcements; (2) placing the salt flux in a crucible, performing heating to prepare salt flux melts, adding the reinforcements; (3) performing pouring into a normal-temperature crucible, and performing cooling to obtain precursors; (4) adding the raw materials in an iron crucible, and performing melting at 953K-1043K; (5) placing the precursors in raw material melt, after stirring, under a condition of 953K-993K, performing standing so that scum and melt are obtained; and (6) removing the scum, lowering temperature to 973K-982K, and performing casting. The method provided by the present invention is simple in process and low in cost. The method can be used for preparing bulk structural members of the magnesium matrix composite, and can be used for automatic production.

Apparatus and methods for additively manufactured structures with augmented energy absorption properties are presented herein. Three dimensional (3D) additive manufacturing structures may be constructed with spatially dependent features to create crash components. When used in the construction of a transport vehicle, the crash components with spatially dependent additively manufactured features may enhance and augment crash energy absorption. This in turn absorbs and re-distributes more crash energy away from the vehicle's occupant(s), thereby improving the occupants' safety.

A method of forming an aircraft component includes providing an aluminum alloy. The method further includes mixing a shape memory alloy (SMA) with the aluminum alloy to form a combination of the SMA and the aluminum alloy. The method further includes forming the aircraft component with the combination of the SMA and the aluminum alloy.

A method for manufacturing a turbine engine vane a root connected to a blade extending in a longitudinal direction includes the steps of providing a root; and providing mold with a first cavity and a second cavity that together define a recess in which the vane is formed. The recess includes a first space in which the blade is formed and a second space in which the root (1), c) is formed. The method further includes the steps of providing aluminum strips; positioning a fibrous reinforcement; arranging the vane root in the second space; and injecting a foam comprising aluminum or injecting an aluminum alloy into the first space of the recess of the mold such that the foam impregnates the fibrous reinforcement.

A method for manufacturing a turbine engine vane a root connected to a blade extending in a longitudinal direction includes the steps of providing a root; and providing mold with a first cavity and a second cavity that together define a recess in which the vane is formed. The recess includes a first space in which the blade is formed and a second space in which the root (1), c) is formed. The method further includes the steps of providing aluminum strips; positioning a fibrous reinforcement; arranging the vane root in the second space; and injecting a foam comprising aluminum or injecting an aluminum alloy into the first space of the recess of the mold such that the foam impregnates the fibrous reinforcement.

A composite material comprising a metal matrix and nanocellulose supplement. The metal matrix is formed of a metal base material and may be monolithic throughout the composite material. The nanocellulose supplement improves a material property of the metal matrix and is formed of a nanocellulose supplement material dispersed in the metal base material. Importantly, the nanocellulose supplement material does not become damaged when the composite material is formed.