The present invention relates to sandwich panels used as aircraft interior parts. In addition to provide a finishing function, the sandwich panels need to have certain mechanical properties and have sufficient fire resistance to retard the spread of fire within the vehicle interior. The present invention provides an aircraft interior panel with skins comprising natural fiber reinforced composites based either on an inorganic thermoset resin or a thermoplastic resin. Such panels provide the required flame and heat resistance, allow easy recycling and disposal, are cheaper and offer significant weight savings over conventional sandwich panels.

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.

A structural assembly includes a first member defining a matrix material, and a second member defining a skin. The skin has a roughed surface of hooks or barbs. The second member is engaged to the first member to define a mechanically interlocked assembly. The assembly may include an open-cell matrix material in a glue-less connection. The assembly may include a chemical bond in addition to a mechanical bond. The assembly may include internal layers of pre-impregnated composite fiber and resin. The skin member may act as a jig for a green composite member. The skin member may be deformed in a press to present a non-planar surface for such other members as may be attached to it. Assemblies may be formed with mechanical interconnection in place of glue or adhesive connections. Assemblies may be formed to may light, thin-walled pipe, flasks, pressure vessels and so forth.

The invention relates to an edge material for panels, the edge material being constructed from a plurality of bonded layers. The edge material comprises a first layer, which is non-metallic, and a core layer, which is made of at least one metal layer. The edge material also comprises a second layer, which is non-metallic. Furthermore, the invention relates to a corresponding sandwich panel and to a corresponding cover layer for panels.

A flexible unit cell is disclosed. The flexible unit cell is a single unit that can be repeated and interconnected to create a flexible design such as a covering for an object or person. The flexible unit includes a rigid portion and a flexible connection portion. Flexible units connect via the flexible connection portion to form a flexible design that can move and flex based on the connection of the flexible connection portions between flexible units. Further, the rigid portions of the flexible units may not be connected, allow such movement. The flexible unit is designed such that a flexible design made using such flexible units maintains a degree of rigidity so it can keep a shape of a surface of an object, but also maintains enough flexibility to conform to the surface even if the object bends or moves. Further disclosed are processes for manufacturing such flexible unit cells.

The present invention relates to a method for manufacturing a laminated object. A foam core and a skin are provided and the foam core and the skin are arranged relative to each other. The skin is heated. The skin is pierced by a vacuum application device. Further, vacuum is applied via the vacuum application device so as to withdraw a gaseous medium, in particular air, from within the foam core and from a space or spaces between the foam core and the skin, in order to draw the skin towards the foam core. Furthermore, the invention provides a manufacturing device for manufacturing a laminated object, laminated objects comprising a foam core and a skin, a method for producing pallets comprising a foam core and a skin, as well as pallets comprising a foam core and a skin.

A method of manufacturing at least one structural panel (20) for an engineering structure comprises conveying a layered structure (40) through a roller assembly comprising at least one pair of heating rollers (50) and at least one pair of cooling rollers (52), where the cooling rollers are at a lower temperature than the heating rollers. The layer structure comprises a thermoplastic foam layer 24 and at least one skin layer (22). The heating rollers 0 heat the skin layer (22) to melt at least part of the foam layer (24) adjacent to the skin layer (22) and bond the foam layer (24) to the skin (22). The cooling rollers (52) cool the layered structure (40) so that the thermoplastic resolidifies, retaining its bond with the skin to form the bonded panel (20). This approach greatly reduces manufacturing costs for structural panels.

Methods and apparatus for making and using tools, for example concrete cutting blades. The tool includes a first layer and a second layer that are oppositely disposed. The first and second layers include working surfaces that support at least one working element when the working element is applied to a work piece. Additionally, an intermediate structure is included between the first and second layers. The intermediate structure can include a plurality of components extending in the area between the structural surfaces and the working surfaces.

A method for repairing a honeycomb core sandwich structural body according to the present invention is a method in which a damaged portion that is formed in a honeycomb core sandwich structural body where a honeycomb structured core is held between a first outer skin and a second outer skin and that reaches the core through the first outer skin is repaired, the method including: a repair material mounting step of mounting a repair material on the damaged portion, the repair material including a patch that covers an opening of the damaged portion, and one or a plurality of braces that support the patch; a patch bonding step of bonding the patch to the first outer skin; and a brace bonding step of bonding the brace to the second outer skin or the core.

A printing method for printing a multi-material 3D model comprises the following steps: perform a slicing process on a multi-material 3D object to generate the multi-material object slices and the object slices of a useful object; compute a material-switching point and a retrieving point during the slicing process; print the multi-material object slices of a multi-material 3D model with one of the materials; when print to the material-switching point, switch to another different material and print useful objects with the material used before the material switching; when print to the retrieving point, print the multi-material object slices with the material used after the material switching; and repeat the above steps until completing the multi-material 3D model printing. The present disclosed example prints the useful object via the remaining materials after the material switching which effectively reduces the cost with of multi-materials printing.