Methods for reworking structures and reworked cellular core panels, reworked structures comprising the reworked cellular core panels, and guides and cutting apparatuses for reworking cellular acoustic panels and reworking cellular non-acoustic panels are disclosed.

The invention relates to a timepiece component made of composite material including at least one reinforcement and one matrix, the reinforcement having a three-dimensional honeycomb structure with a plurality of cells into which the matrix is injected.

The invention also concerns a method for manufacturing such a timepiece component.

Provided are splices, comprising honeycomb cores and adhesive layers with tie clips supporting the honeycomb cores. Also provided are methods of forming such splices. Each tie clip includes two legs and a bridging portion joining the legs. When forming a splice, an adhesive layer is positioned between two honeycomb cores. One leg of the tie clip is inserted into the full cell of one honeycomb core, while the other leg is inserted into the full cell of the other honeycomb core. The bridging portion extends across the adhesive layer. While curing the adhesive layer, the tie clip supports the honeycomb cores with respect to each other and maintains their orientation. The tie clip becomes a part of the splice. The tie clip may be buried in the honeycomb cores without extending above the first face of the splice.

A method of producing a core for a composite panel along a continuous production line is disclosed. The method includes the steps of providing a thermoplastic sheet of material onto the production line and vacuum forming the thermoplastic sheet of material into alternating pairs of matching shapes, providing the thermoplastic sheet of material with alternating pairs of matching shapes onto upper and lower conveyor belts that are operating at lower speeds than the production line causing the pairs of matching shapes to bunch up and form a honeycomb structure, and cutting the honeycomb structure into discrete sections with spaces therebetween. A plurality of reinforced plastic bands with gaps therebetween are provided and the honeycomb structure is aligned with the gaps. The plurality of reinforced plastic bands and the honeycomb structure are secured together.

A composite core assembly includes a composite core structure having internal material interfaces and an attachment rail coupled to the composite core structure. The attachment rail includes a first planar surface and a second planar surface adjoined with the first planar surface. The first planar surface is arranged parallel to an internal material interface plane of the composite core structure, and the first planar portion is at least partially integrated into the composite core structure in an internal material interface plane. At least a portion of the first planar surface extends beyond a perimeter surface of the composite core structure, and the second planar surface is configured to attach to the surrounding support member. The core material does not have net edge facets or flat edges positioned next to surrounding structure, and/or may not have a structure arranged parallel to the adjacent support structure to attach to the support structure.

A composite sandwich panel comprises a first composite skin, a second composite skin, a hollow cell core between the first composite skin and the second composite skin, and a first over-crush edge region with a first edge. The first edge has a first thickness at least 40% less than a nominal thickness of the composite sandwich panel. The first over-crush edge region has a length of at least 0.25 inches over which a thickness of the composite sandwich panel decreases.

A method of injecting potting material into at least a portion of a workpiece, comprises positioning a potting press, containing the potting material, over a target area of the workpiece. The target area contains openings, passing entirely through the workpiece. Simultaneously with positioning the potting press over the target area of the workpiece, the potting material is injected into each one of the openings within the target area.

The invention discloses a starch-based multi-channel airflow unit and a preparation method and an application thereof. The preparation method of the present invention comprises the following steps: melting a polylactic acid, wherein a temperature of a first temperature control zone is 135 C. to 145 C., a temperature of a second temperature control zone is 175 C. to 185 C., a temperature of a third temperature control zone is 190 C. to 200 C., and a temperature of a fourth temperature control zone is 175 C. to 185 C.; gelatinizing a starch-based material, adding the starch-based material in the third temperature control zone and fully mixing the mixture; adding a polyol in the third temperature control zone, and fully mixing the mixture; and extruding out the mixed material through twin screws, sizing in vacuum, cooling and sizing, and winding and cutting to obtain the starch-based multi-channel airflow unit.

A composite core assembly includes a composite core structure having internal material interfaces and an attachment rail coupled to the composite core structure. The attachment rail includes a first planar surface and a second planar surface adjoined with the first planar surface. The first planar surface is arranged parallel to an internal material interface plane of the composite core structure, and the first planar portion is at least partially integrated into the composite core structure in an internal material interface plane. At least a portion of the first planar surface extends beyond a perimeter surface of the composite core structure, and the second planar surface is configured to attach to the surrounding support member. The core material does not have net edge facets or flat edges positioned next to surrounding structure, and/or may not have a structure arranged parallel to the adjacent support structure to attach to the support structure.

A load structure may include a panel having a core, and a coating of polyurethane around the core. The load structure may also have a layer of carpet or felt on at least a portion of a first side of the panel. The load structure may further include an over mold coating on a second side of the panel.