Abstract: A cascade for a jet engine thrust reverser is fabricated by co-consolidating pre-consolidated thermoplastic strongbacks and vanes. The strongbacks are reinforced with continuous fibers, and the vanes are reinforced with discontinuous fibers.

Abstract: An assembly of thermoplastic parts for forming a final composite part is presented where the assembly includes at least two prefabricated shells fabricated of thermoplastic. Each prefabricated shell has substantially the same shape as the final composite part and where the shapes of the prefabricated shells have dimensions that allow the prefabricated shells to be assembled into a nest for placement into a mold.

Abstract: Composite fasteners have a high fraction of discontinuous, randomly oriented reinforcing fibers. A charge of thermoplastic fiber flakes are heated to melting temperature within a reservoir, flowed into multiple mold cavities and compression molded. The molded fasteners have high strength, exhibit quasi-isotropic properties and may be produced in high volume.

Abstract: A cascade for a jet engine thrust reverser is fabricated by co-consolidating pre-consolidated thermoplastic strongbacks and vanes. The strongbacks are reinforced with continuous fibers, and the vanes are reinforced with discontinuous fibers.

Abstract: A cascade for a jet engine thrust reverser is fabricated by co-consolidating pre-consolidated thermoplastic strongbacks and vanes. The strongbacks are reinforced with continuous fibers, and the vanes are reinforced with discontinuous fibers.

Abstract: Composite fasteners have a high fraction of discontinuous, randomly oriented reinforcing fibers. A charge of thermoplastic fiber flakes are heated to melting temperature within a reservoir, flowed into multiple mold cavities and compression molded. The molded fasteners have high strength, exhibit quasi-isotropic properties and may be produced in high volume.

Abstract: Composite fasteners have a high fraction of discontinuous, randomly oriented reinforcing fibers. A charge of thermoplastic fiber flakes are heated to melting temperature within a reservoir, flowed into multiple mold cavities and compression molded. The molded fasteners have high strength, exhibit quasi-isotropic properties and may be produced in high volume.

Abstract: An assembly of thermoplastic parts for forming a final composite part is presented where the assembly includes at least two prefabricated shells fabricated of thermoplastic. Each prefabricated shell has substantially the same shape as the final composite part and where the shapes of the prefabricated shells have dimensions that allow the prefabricated shells to be assembled into a nest for placement into a mold.

Abstract: A cascade for a jet engine thrust reverser is fabricated by co-consolidating pre-consolidated thermoplastic strongbacks and vanes. The strongbacks are reinforced with continuous fibers, and the vanes are reinforced with discontinuous fibers.

Abstract: An apparatus and method are presented. An apparatus comprises a composite structure, a plurality of cavities extending into the composite structure, and a plurality of mandrels located within the plurality of cavities. The composite structure comprises a thermoplastic material that is consolidated. The plurality of mandrels comprises a first material that is configured to generate heat in response to a magnetic field.

Abstract: An apparatus and method are presented. An apparatus comprises a composite structure, a plurality of cavities extending into the composite structure, and a plurality of mandrels located within the plurality of cavities. The composite structure comprises a thermoplastic material that is consolidated. The plurality of mandrels comprises a first material that is configured to generate heat in response to a magnetic field.

Abstract: Concepts and technologies are disclosed herein for compression molding of composite material quasi-isotropic flakes. According to some embodiments disclosed herein, a first layer formed from a composite component material and a second layer formed from a composite component material are consolidated together to form a quasi-isotropic panel. Composite material flakes having quasi-isotropic properties (“quasi-flakes”) are obtained from the quasi-isotropic panel. A compression mold is filled with the quasi-flakes, and heat is applied to the compression mold to form a part.

Abstract: Concepts and technologies are disclosed herein for compression molding of composite material quasi-isotropic flakes. According to some embodiments disclosed herein, a first layer formed from a composite component material and a second layer formed from a composite component material are consolidated together to form a quasi-isotropic panel. Composite material flakes having quasi-isotropic properties (“quasi-flakes”) are obtained from the quasi-isotropic panel. A compression mold is filled with the quasi-flakes, and heat is applied to the compression mold to form a part.