Abstract: Disclosed herein is a tool for forming a composite part. The tool comprises a first layer, a second layer, spaced apart from the first layer, and a low-density core interposed between the first layer and the second layer. The low-density core has a density less than the first layer and the second layer and comprises a plurality of empty cells at least partially defined by the first layer and the second layer. The tool also comprises a heating source and one of: each one of the plurality of empty cells extends across a width or length of the first layer and the second layer; or adjacent ones of the plurality of empty cells are fluidically interconnected by a fluid port formed in the low-density core.

Abstract: Disclosed herein is a cure tool for managing a thermal cycle of a composite component. The cure tool, in certain examples, includes a base plate comprising a work surface, for supporting the composite component, and a back surface opposite the work surface. The cure tool also includes one or more fins protruding from the back surface of the base plate and in thermal communication with the base plate. The cure tool additionally includes one or more heating elements coupled to each of the one or more fins and configured to selectively provide heat to the base plate.

Abstract: A method apparatus, and system method for manufacturing a composite part. A set of composite preforms is placed on a set of slip sheets. The set of slip sheets with the set of composite preforms is attached to a cure mandrel to form a composite preform assembly.

Abstract: A work platform configured to support one or more workers in proximity to a workpiece. The work platform includes sliders that are aligned along the length of the workpiece. The sliders are laterally movable towards and away from the workpiece. The sliders are individually movable with a position of each of the sliders relative to the workpiece being a function of the rotational position of the workpiece.

Abstract: A tooling assembly for manufacturing a porous composite structure. The tooling assembly includes a first tooling member and a second tooling member. The first tooling member includes a first body that defines a first internal volume and a first inlet. The first inlet is fluidly coupled with the first internal volume. The first tooling member also includes a first tooling surface that defines a plurality of first perforations that are fluidly coupled with the first internal volume. The second tooling member includes a second body that defines a second internal volume and a second inlet. The second inlet is fluidly coupled with the second internal volume. The second tooling member also includes a second tooling surface that defines a plurality of second perforations that are fluidly coupled with the second internal volume.

Abstract: A tooling assembly for manufacturing a porous composite structure. The tooling assembly includes a first tooling member and a second tooling member. The first tooling member includes a first body that defines a first internal volume and a first inlet. The first inlet is fluidly coupled with the first internal volume. The first tooling member also includes a first tooling surface that defines a plurality of first perforations that are fluidly coupled with the first internal volume. The second tooling member includes a second body that defines a second internal volume and a second inlet. The second inlet is fluidly coupled with the second internal volume. The second tooling member also includes a second tooling surface that defines a plurality of second perforations that are fluidly coupled with the second internal volume.

Abstract: Disclosed herein is a tool for forming a composite part. The tool comprises a first layer, a second layer, spaced apart from the first layer, and a low-density core interposed between the first layer and the second layer. The low-density core has a density less than the first layer and the second layer and comprises a plurality of empty cells at least partially defined by the first layer and the second layer. The tool also comprises a heating source and one of: each one of the plurality of empty cells extends across a width or length of the first layer and the second layer; or adjacent ones of the plurality of empty cells are fluidically interconnected by a fluid port formed in the low-density core.

Abstract: Disclosed herein is a cure tool for managing a thermal cycle of a composite component. The cure tool, in certain examples, includes a base plate comprising a work surface, for supporting the composite component, and a back surface opposite the work surface. The cure tool also includes one or more fins protruding from the back surface of the base plate and in thermal communication with the base plate. The cure tool additionally includes one or more heating elements coupled to each of the one or more fins and configured to selectively provide heat to the base plate.

Abstract: Core structures for composite panels, aircraft including the same, and related methods. A core structure includes a core body defining a first body side, a second body side, and a plurality of core cells. Each core cell includes at least one cell wall and defines a tubular cell void. Each core cell includes a bulk region and a transition region. Each cell wall is flared within the transition region to increase a surface area of the first body side relative to an average transverse cross-sectional area of the core body. A composite panel includes a core structure with at least one laminate ply coupled to the first body side of a core body. A method of manufacturing a composite panel includes forming a core body via an additive manufacturing process and operatively attaching at least one laminate ply to the core body.

Abstract: A tooling assembly for manufacturing a porous composite structure. The tooling assembly includes a first tooling member and a second tooling member. The first tooling member includes a first body that defines a first internal volume and a first inlet. The first inlet is fluidly coupled with the first internal volume. The first tooling member also includes a first tooling surface that defines a plurality of first perforations that are fluidly coupled with the first internal volume. The second tooling member includes a second body that defines a second internal volume and a second inlet. The second inlet is fluidly coupled with the second internal volume. The second tooling member also includes a second tooling surface that defines a plurality of second perforations that are fluidly coupled with the second internal volume.

Abstract: A tooling assembly for manufacturing a porous composite structure. The tooling assembly includes a first tooling member and a second tooling member. The first tooling member includes a first body that defines a first internal volume and a first inlet. The first inlet is fluidly coupled with the first internal volume. The first tooling member also includes a first tooling surface that defines a plurality of first perforations that are fluidly coupled with the first internal volume. The second tooling member includes a second body that defines a second internal volume and a second inlet. The second inlet is fluidly coupled with the second internal volume. The second tooling member also includes a second tooling surface that defines a plurality of second perforations that are fluidly coupled with the second internal volume.

Abstract: Core structures for composite panels, aircraft including the same, and related methods. A core structure includes a core body defining a first body side, a second body side, and a plurality of core cells. Each core cell includes at least one cell wall and defines a tubular cell void. Each core cell includes a bulk region and a transition region. Each cell wall is flared within the transition region to increase a surface area of the first body side relative to an average transverse cross-sectional area of the core body. A composite panel includes a core structure with at least one laminate ply coupled to the first body side of a core body. A method of manufacturing a composite panel includes forming a core body via an additive manufacturing process and operatively attaching at least one laminate ply to the core body.