A cellular confinement system includes PET sheets and honeycomb-shaped cells formed by intercrossing the PET sheets. A connecting hole is provided at a joint where the PET sheets are intercrossed. An injection molded fixing component for connecting the PET sheets is provided at the connecting hole. The injection molded fixing component includes an injection molded rod arranged in the connecting hole and fixing plates each arranged to be fixedly connected to a corresponding end of two ends of the injection molded rod. The fixing plates each fits against a side wall of a corresponding PET sheet. The injection molded fixing component includes the injection molded rod and the fixing piece. The injection molded rod is configured to connect the PET sheets at the joint where the PET sheets are intercrossed. The fixing plate is configured to prevent the PET sheets from being disengaged from the injection molded rod.

In a process for manufacturing a catalytic converter component, a ceramic unit is used that has been prepared by extruding green ceramic product through a die to form an extrusion having a honeycomb substrate structure in which tubular passages extend along the extrusion, the passages bounded by walls dividing adjacent passages from one another. The unit is obtained by cutting off a length of the extrusion and curing and firing it. The process further comprises flowing insulation material from one end of the unit into selected ones of the elongate passages, vaporizing a moisture content of the insulation material to form pores and curing the insulation material by using microwave irradiation to solidify the pores. The passages are selected so that the cured insulation material forms an internal thermal insulating barrier between a core zone of the unit and a radially outer zone of the unit.

A method of manufacturing a tiltrotor wing structure including providing a spar mold having a plurality of bores extending from an exterior surface of the mold to an interior surface of the mold, the plurality of bores corresponding to a plurality of primary coordination holes in a spar member, the spar mold having a periphery defined by a top edge, a bottom edge and outboard ends; selecting a plurality of resin impregnated plies to ensure that the plies continuously extend beyond the periphery of the spar mold; laying the plies in the spar mold; curing the plies in the mold to form a cured spar member that extends beyond the periphery of the spar mold; and accurately drilling a plurality of primary coordination holes in the cured spar member in the spar mold using a tool positioned in the plurality of bores.

In a preferred embodiment, a composite panel with a smooth outer surface, ready for painting with or without addition of primer, may be created by constructing a panel layup assembly upon a mold, the panel layup assembly including a composite panel having a core and a resin formulation, and a release film between the mold and the composite panel, where a smooth release surface of the release film is in contact with the composite panel upon construction; initiating curing of the composite panel at a first temperature within a lowermost ten percent of a curing temperature range of the resin formulation; continuing curing of the composite panel at a second temperature above the lowermost ten percent of the curing temperature range; and completing curing of the composite panel at a third temperature below the second temperature.

The heating method of honeycomb structure includes a heating step of supplying a power to a honeycomb structure body of a honeycomb structure including the tubular honeycomb structure body having porous partition walls to define and form a plurality of cells and a circumferential wall positioned at an outermost circumference, and heating by electricity conduction, and a catalyst loaded onto the partition walls of the honeycomb structure body, to heat the honeycomb structure body up to a target temperature, and in the heating step, there is provided, at least once, a supply power decrease section where the supply of the power to the honeycomb structure body is stopped or the power to be supplied to the honeycomb structure body is decreased before the lowest temperature in a heating region of the honeycomb structure body reaches the target temperature.

A method and apparatus for forming a ribbon configured for use in forming a honeycomb structure when the ribbon is in a folded state. The ribbon comprises a first edge and a second edge. At least one portion of the first edge is not parallel to at least one portion of the second edge when the ribbon is in an unfolded state.

A honeycomb for curved surface lightweight components includes a plurality of elongate ribbons and connecting regions. The connecting regions are provided, respectively, between opposing ribbons to connect the ribbons together in a portion-wise manner in a firmly bonded relationship in a transverse direction. The connecting regions are arranged at regular spacings along the longitudinal direction of a ribbon. Honeycomb-like cells form cavities between the ribbons. With respect to three successive ribbons, a displacement of the connecting regions between first and second ribbons relative to the connecting regions between second and third ribbons toward a first side of the longitudinal direction is lesser than toward a second side of the longitudinal direction. Consequently, at least a part of the cells in cross-section in the longitudinal direction/transverse direction plane have at least one longer limb corresponding to the greater displacement and at least one shorter limb corresponding to the lesser displacement.

A manufacturing method of a honeycomb structure forming die includes a linear slit forming step of forming, in a kneaded material discharging surface of a die substrate, a plurality of linear slits which are straight from one end to the other end on the kneaded material discharging surface, a slit sealing material disposing step of disposing a slit sealing material in parts of the plurality of linear slits, and a back hole forming step of forming back holes to introduce a kneaded material, in a kneaded material introducing surface of the die substrate which is present on a side opposite to the kneaded material discharging surface.

Preforms including fiber reinforced nodes for use in fiber reinforced composite structures and methods for making fiber reinforced composite structures. Preforms with woven fabric elements extending radially from a common node include at least one reinforcing fiber interwoven between at least two elements and passing through the node. A method of assembling preform structures using the preforms to provide a structure with reinforced nodes.

A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.