A method and apparatus for the additive manufacturing of three-dimensional objects are disclosed. Two or more materials are extruded simultaneously as a composite, with at least one material in liquid form and at least one material in a solid continuous strand completely encased within the liquid material. A means of curing the liquid material after extrusion hardens the composite. A part is constructed using a series of extruded composite paths. The strand material within the composite contains specific chemical, mechanical, or electrical characteristics that instill the object with enhanced capabilities not possible with only one material.

Method for producing composite components having an undevelopable surface. To be able to maintain the tolerances when manufacturing especially large components in the case of composite components with undevelopable surfaces, it is proposed according to the invention to drape a cut-to-size blank on a molding tool and to determine the deviation of the cut-to-size blank edge from the setpoint cut-to-size edge. Then, on the basis of the deviation, a new cut-to-size blank edge is calculated, and a new cut-to-size blank is created and re-draped for examination purposes. The method is repeated until the deviations are below a tolerable threshold value. The method is furthermore carried out for each textile ply of the composite component.

An on-orbit composite filament forming device for space 3D printing includes a constant tension unwinding module, a replaceable resin filament rotary wrapping module, a melt preheating chamber, a curved channel impregnation chamber, a variable aperture resin recovery device, a heat protective housing, a convective cooling device, a traction device, and a winding device. The replaceable resin filament rotary wrapping module wraps a resin filament on a surface of a carbon fiber by circumferential rotation and is provided with an active unwinding reel placed on a circular rail centered on the carbon fiber; the melt preheating chamber is used for melting resin to wrap the surface of the fiber, and is equipped with a lifting device for automatic opening and closing; the curved channel impregnation chamber is formed with a wedge-shaped high-pressure impregnation zone by mutual extrusion of upper and lower pressure blocks, thereby improving the quality of fiber impregnation.

An on-orbit composite filament forming device for space 3D printing includes a constant tension unwinding module, a replaceable resin filament rotary wrapping module, a melt preheating chamber, a curved channel impregnation chamber, a variable aperture resin recovery device, a heat protective housing, a convective cooling device, a traction device, and a winding device. The replaceable resin filament rotary wrapping module wraps a resin filament on a surface of a carbon fiber by circumferential rotation and is provided with an active unwinding reel placed on a circular rail centered on the carbon fiber; the melt preheating chamber is used for melting resin to wrap the surface of the fiber, and is equipped with a lifting device for automatic opening and closing; the curved channel impregnation chamber is formed with a wedge-shaped high-pressure impregnation zone by mutual extrusion of upper and lower pressure blocks, thereby improving the quality of fiber impregnation.

The present disclosure relates to a system for manufacturing a hybrid component including a first thermal supplier configured to heat a steel plate, a rolling roll for undercut configured to pressurize the steel plate heated by the first thermal supplier, and to form an undercut on one surface of the steel plate, a first molding roll configured to pressurize the steel plate formed with the undercut to mold the steel plate in a shape of a component to be manufactured, a composite material feeder configured to supply a composite material tape to be seated on one surface of the steel plate formed with the undercut through the first molding roll, and a composite material pressurization roll configured to pressurize the steel plate on which the composite material tape is seated.

A process for preparing a composite part, the process comprising: recovering unsaturated resin prepreg scrap; combining the recovered unsaturated resin prepreg scrap with a second resinous thermosetting component; and co-molding the prepreg scrap and resinous thermosetting component together under a pressure of 25 to 4000 psi and at a temperature of 100-400 F.

A method and apparatus for the additive manufacturing of three-dimensional objects are disclosed. Two or more materials are extruded simultaneously as a composite, with at least one material in liquid form and at least one material in a solid continuous strand completely encased within the liquid material. A means of curing the liquid material after extrusion hardens the composite. A part is constructed using a series of extruded composite paths. The strand material within the composite contains specific chemical, mechanical, or electrical characteristics that instill the object with enhanced capabilities not possible with only one material.

A system for manufacturing modular aircraft includes at least at least a common tooling component, including at least one or more of a first component in a shape of a nose and a second component in a shape of a wing. The system further including at least a modular tooling component in a shape of a main body, wherein connecting the at least a common tooling components to the at least modular component forms a mold in a shape of at least a portion of a blended wing body (BWB) aircraft with no clear demarcation between the shape of the wing and a shape of a main body along an edge of the shape of the BWB.

A wind turbine blade including a shell structure defining a leading edge and a trailing edge, and an upwind shell and a downwind shell joined along at least one of the leading edge or the trailing edge. The shell structure includes an assembly of preformed parts processed into a collection of prefabricated laminates. The invention also includes a method of manufacturing a wind turbine blade, the method includes processing a number of preformed parts into a collection of prefabricated laminates and assembling the collection of prefabricated laminates to build a shell structure defining a leading edge and a trailing edge.

The present disclosure provides a molding system for fabricating a FRP composite article. The molding system includes a detector, a resin dispenser, a processing module, and a molding machine. The detector is configured to capture a graph of a woven fiber from a top view. The resin dispenser is configured to provide a resin to the woven fiber to form a FRP. The processing module is configured to receive the graph and a plurality of parameters of the FRP. The processing module includes a CNN model, and is configured to use the CNN model to obtain a plurality of predicted mechanical properties of the FRP according to the graph and the plurality of parameters of the FRP. The molding machine is configured to mold the FRP to fabricate the FRP composite article according to the plurality of predicted mechanical properties.