Methods and machine for manufacturing vertically oriented core of multiwalls and multiwalls comprising such core. Multiwalls or cores of multiwalls with transversely oriented flutes in their core are sliced perpendicularly relative to the axis of rotation of the flutes. The slices are bent relative to the origin multiwall or core, packed together, welded or fused or mechanically pressed to each other and their top and bottom surfaces leveled to provide a vertically oriented shortened flutes that form the core. The top and bottom surfaces of the core are then laminated. Machine configurations are also provided for continuous manufacturing of vertically oriented cores of multiwalls.

A method and system for manufacturing a conical shaped acoustic structure. A sheet of acoustical material is cut to form individual pieces using a cutter system. Each individual piece in the individual pieces has a flat pattern for the conical shaped acoustic structure. An individual piece is positioned around a mandrel with a conical shape using an actuator system. Two edges of the individual piece are positioned for joining. The two edges of the individual piece positioned around the mandrel are joined to form the conical shaped acoustic structure.

A process for producing a sandwich component. A first covering layer is formed on a molding surface of a molding tool; a core is produced by building up a cell structure having a multiplicity of cells in a thickness direction on the first covering layer via an additive production process; and a second covering layer is formed on a deposition surface of the core, the surface being situated on the opposite side from the first covering layer. A core for a sandwich component is furthermore described, as is a sandwich component.

A component is provided. The component includes a structure including a plurality of unit cells joined together, each unit cell of the plurality of unit cells having a mass density substantially similar to the mass density of every other unit cell of the plurality of unit cells. The plurality of unit cells includes a first portion of unit cells having a characteristic dimension and a first portion average stiffness, the characteristic dimension of the first portion of unit cells having a first value. The plurality of unit cells also includes a second portion of unit cells having the characteristic dimension and a second portion average stiffness, the characteristic dimension of the second portion of unit cells having a second value different from the first value, wherein the second portion average stiffness differs from the first portion average stiffness.

A honeycomb structure comprising carbon-fiber non-woven, sandwich structure comprising the honeycomb structure, and process for the production of the honeycomb structure.

A method and apparatus for fabricating a composite structure. The method comprises defining a shape for the composite structure with a first face sheet. The method places core sections on the shape defined by the first face sheet. The method places an adhesive in a group of joint cavities. The method places a second face sheet on the core sections placed on the first face sheet, wherein the first face sheet, the core sections, and the second face sheet, define a structural assembly in which the group of joint cavities are present. The method cures the structural assembly with the adhesive in the group of joint cavities to fabricate the composite structure in which the adhesive fills the group of joint cavities when the adhesive is cured.

A door for a thrust reversal system, an aircraft with such a door, and a method for manufacturing a door of a thrust reversal system. The door comprises a wall formed from long fibers embedded in a thermoplastic resin matrix and a network of ribs overmolded on one of the faces of the wall. A propulsion assembly of an aircraft comprises a thrust reversal system having a plurality of such doors.

FIG. 2 shows a microperforated panel absorber 22 comprising: a microperforated facing 24; a non-perforated facing 26; and a cellular core structure 28 therebetween; the core structure 28 provides a number of primary cells 33 and a number of secondary cells 37; the secondary cells 37 each provide a reduced cell depth in comparison to the primary cells 33. FIG. 9 shows that the number of the primary cells 33 and the number of the secondary cells 37 ensures that sound absorption at frequencies up to and including the peak frequency is substantially maintained and that the sound absorption at frequencies higher than peak frequency is substantially increased relative to a comparable panel absorber in which the secondary cells are effectively replaced by primary cells.

A composite structure assembly includes a composite core including a flexible base and a plurality of cells extending from the flexible base. The composite core is conformable to different shapes. The plurality of cells are configured to move in response to movement of the flexible base. At least one of the plurality of cells may include a central column connected to a first flared end and a second flared end that is opposite from the first flared end.

Light weight fibrous veils are incorporated into the uncured composite face sheets of a honeycomb sandwich structure in order to reduce the lateral crushing of the honeycomb (core crush) that occurs during curing of the uncured structure in an autoclave or vacuum bag system. The light weight fibrous veils act as friction-promoting layers to reduce the relative movement of the uncured face sheets that leads to core crush during the curing process.