A honeycomb core includes a honeycomb substrate comprised of a number of sheets. A number of traces are printed onto the sheets of the honeycomb substrate. A number of integrated electronic devices are disposed within the honeycomb substrate. The integrated electronic devices are electrically coupled to the traces.

A method of repairing a composite structure includes providing an assembled composite structure comprising a substantially rigid outer component, wherein the composite structure comprises a void space at least partially bounded by the outer component. The method further includes forming an injection hole through the outer component to provide a path between the void space and space external to the composite structure. The method further includes injecting foam into the void space through the injection hole while the foam is in a substantially unexpanded state and expanding the foam within the void space.

A method for creating a honeycomb core having venting pathways includes controlling where a resin is applied to sheets by creating a resin affinity portion and a resin repellant portion on the sheets. The resin affinity portion and the resin repellant portion forms the venting pathways. A honeycomb substrate is then formed from the sheets.

Packages used to deliver items or other payloads via a drone may be customized and 3D printed to house the payload. The package may be customized to minimize the size and/or weight needed to house the payload. The customized packages may include one or more attachment mechanisms adapted to engage with or otherwise be coupled to the drone for delivery. Multiple individual customized packages can be secured together into a composite package for delivery by drone. The customized package may be designed to be aerodynamic given the shape of the payload and the flight characteristics of the drone. The drone itself may be the package, with the payload housed within a portion of the drone. The package and/or a portion of the drone (e.g., fuselage, wing, body, frame, etc.) may be printed at least partially in, on, or around an item or package to be transported by the drone.

Adhesive bondlines in a cell-based structural array are thermally cured using tooling blocks inserted into the cells. The tooling blocks have embedded susceptors that are inductively heated by an alternating electromagnetic field generated by an electromagnet.

A method of repairing a sandwich structure includes: removing a damaged portion of a core and a damaged portion of a first facesheet to form an open volume; filling the open volume with an ultraviolet-curable photomonomer; partially curing the ultraviolet-curable photomonomer to form a plurality of photopolymer waveguides by utilizing ultraviolet light; and arranging a replacement facesheet on the damaged portion of the first facesheet and over the photopolymer waveguides.

A honeycomb extrusion die (120) includes a die body (302) including an inlet face (306) and an exit face. The die body (302) has slot inlets (309) and a plurality of pins (320, 500) disposed between the slot inlets (309) and the exit face. The plurality of pins (320, 500) include side surfaces (322, 500B) configured to define a matrix of intersecting slots (324), wherein the matrix of intersecting slots (324) has slot exit (509) widths at the exit face. Divots (526) extend into a plurality of the side surfaces (322, 500B) between the slot inlets (309) and the exit face. Each individual divot (526) has a divot san depth (D55) extending into a side surface (500A, 500B, 502A, 502B) of the side surfaces (322, 500B). A ratio between a slot exit width (W53) W53 of an individual slot (324) and the divot depth (D55) of an individual divot (526) extending into a side surface (500A, 500B, 502A, 502B) of the individual slot (324) is greater than 1.2. Methods of forming honeycomb bodies with honeycomb structures are provided, as are other aspects.

Disclosed herein is a molded laminated structure having negative draft angles and methods of manufacturing a molded laminated structure having negative draft angles. A preliminary structure having a first outer layer and a second outer layer is molded with a bend that divides the preliminary structure into two sections with an angle between the two sections of less than 180-degrees. Portions that extends from the sections are at positive draft angles. A groove is formed in the preliminary structure at the bend but not formed in a constant cross-section of the second outer layer. The preliminary structure is folding along the bend to at least partially close the groove and form a molded laminated structure with portions that extend at a negative draft configuration while retaining the second outer layer continuous throughout the molded laminated structure.

A honeycomb extrusion die (100), a method of making the same, and an apparatus for forming the same. The die (100) includes: a feed hole plate (202) comprising an input surface (202A), an opposing output surface (202B), and feed holes (108) configured to guide a batch material from the input surface (202A) to the output surface (202B); and a pin assembly (204) comprising pins (300) disposed on the feed hole plate (202). At least one of the pins includes: a tail (304); a head (302) connected to the tail (304) and comprising alignment surfaces (314) configured to align the pins (300), flow surfaces (316) disposed between the alignment surfaces (314), and a tapered portion (310) comprising a contact surface (308) adhered to the output surface (202B) of the feed hole plate (202); and a first groove (306) disposed between the head (302) and the tail (304). In the pin assembly (204), the alignment surfaces (314) contact adjacent pins (300) to align the pins (300), such that discharge slots are at least partially defined by the tails (304) of the pins (300).

A folded core structure formed from an uncut flat body, has a plurality of consecutive 3D-structures and connecting areas each formed by plastic deformation, and includes first and second primary surfaces oriented plane-parallel to each other. The first and second primary surfaces include a first secondary surface extending over the entire width of the folded core structure and extending over a part of the length of the folded core structure. The first secondary surface is oriented parallel to the first primary surface, and the first secondary surface is located at a distance from the first primary surface between the first and second primary surfaces. A channel for fluid flow at least along the width of the folded core structure is provided. The first and/or second primary surface is/are configured to provide dimensional stability under a compression force applied perpendicular to the first primary surface of the folded core structure.