The present application relates to a composite material and a method for molding the same. Firstly, components to be pressed is disposed in a gas-isolation element, and located between two pressing plates. Next, a plate is disposed based on a location of a prepreg element of the components, and then a hot pressing step is performed. After the hot pressing step, a cooling step is performed, thereby producing the composite material of the present application. A dimension of the composite material can be easily adjusted to meet requirements of various applications.

The present application relates to a composite material and a method for molding the same. Firstly, components to be pressed is disposed in a gas-isolation element, and located between two pressing plates. Next, a plate is disposed based on a location of a prepreg element of the components, and then a hot pressing step is performed. After the hot pressing step, a cooling step is performed, thereby producing the composite material of the present application. A dimension of the composite material can be easily adjusted to meet requirements of various applications.

There is provided a forming apparatus for forming a high contour composite structure. The forming apparatus includes an upper die and a lower die between which a composite charge is formed. The forming apparatus further includes a plurality of load cells, a control system, and an overlay tool assembly coupled to the upper die. The overlay tool assembly has scalloped sections positioned between pairs of the plurality of load cells, and positioned against portion(s) of the composite charge. The composite charge has ply discontinuity features through the one or more portions. The overlay tool assembly denies pressure and a through thickness compaction to the one or more portions of the composite charge during a forming process, to allow one or more plies in the one or more portions to move after the forming process, and to enable in-plane bending of the high contour composite structure in post-forming operations.

A method for forming a fiber-reinforced thermoplastic control surface may comprise: stacking plies of thermoplastic composite sheets to a first desired thickness to form a first skin; stacking plies of thermoplastic composite sheets to a second desired thickness to form a second skin; forming the first skin in a first contour; forming the second skin in a second contour; forming a stiffening member including a thermoplastic resin, the stiffening member including a shape having a plurality of peaks and troughs; assembling the stiffening member between the first skin and the second skin; and joining the stiffening member to the first skin and the second skin.

A method for forming a fiber-reinforced thermoplastic control surface may comprise: stacking plies of thermoplastic composite sheets to a first desired thickness to form a first skin; stacking plies of thermoplastic composite sheets to a second desired thickness to form a second skin; forming the first skin in a first contour; forming the second skin in a second contour; forming a stiffening member including a thermoplastic resin, the stiffening member including a shape having a plurality of peaks and troughs; assembling the stiffening member between the first skin and the second skin; and joining the stiffening member to the first skin and the second skin.

A laminating auxiliary jig includes a base having an accommodating recess, and a pressing plate pivotably attached to the base and having a positioning trough. When the pressing plate is opened, it is separated from the accommodating recess, which a first composite material is put into. When the pressing plate is closed, it is located in the accommodating recess and pressed on the first composite material, the positioning trough communicates with the accommodating recess, and at least one middle foam material is put into the positioning trough to be positioned and attached to the first composite material. When the pressing plate is opened again, a second composite material is put into the accommodating recess to be attached to the middle foam material. Therefore, the laminating auxiliary jig helps a user quickly complete laminating the multilayer composite material. The method of using the laminating auxiliary jig is also provided.

A laminating auxiliary jig includes a base having an accommodating recess, and a pressing plate pivotably attached to the base and having a positioning trough. When the pressing plate is opened, it is separated from the accommodating recess, which a first composite material is put into. When the pressing plate is closed, it is located in the accommodating recess and pressed on the first composite material, the positioning trough communicates with the accommodating recess, and at least one middle foam material is put into the positioning trough to be positioned and attached to the first composite material. When the pressing plate is opened again, a second composite material is put into the accommodating recess to be attached to the middle foam material. Therefore, the laminating auxiliary jig helps a user quickly complete laminating the multilayer composite material. The method of using the laminating auxiliary jig is also provided.

One embodiment is an apparatus including a mold configured to manufacture a composite structure at a heated temperature. The mold includes a first mold tool configured to mold a first portion of the composite structure, wherein the first mold tool comprises a plurality of strands of a fiber-reinforced thermoplastic material, wherein the fiber-reinforced thermoplastic material comprises a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands; and an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the first mold tool; and a second mold tool configured to mold a second portion of the composite structure.

Systems and methods are provided for fabricating composite parts. One embodiment is a method for fabricating a composite part, the method comprising: reducing a bulk factor of chips of chopped fiber while forming the chips into a pre-consolidated charge; shaping portions of the pre-consolidated charge into shaped volumetric charges that fit within a die; and compression molding the shaped volumetric charges within the die.

Systems and methods are provided for fabricating composite parts. One embodiment is a method for fabricating a composite part, the method comprising: reducing a bulk factor of chips of chopped fiber while forming the chips into a pre-consolidated charge; shaping portions of the pre-consolidated charge into shaped volumetric charges that fit within a die; and compression molding the shaped volumetric charges within the die.