A method for manufacturing a wing box for aircraft comprises the steps of arranging, on a curing surface, a first panel of composite material, alternately arranging, on the first panel, along a transverse direction, a rib of non-polymerized composite material and a tool comprising a central part, a bottom part and a top part, wherein the central part of each tool is interposed between said bottom part and the top part and may be extracted in a transverse direction, arranging a second panel of composite material by putting said second panel in contact with the flanges of each rib, pulling out the central part of each tool along the transverse direction and removing the top part and the bottom part of each tool, and subjecting the first panel, the second panel, and each rib to a curing process in autoclave with vacuum bag.

A method of producing a cascade array and a cascade array is provided. The method includes: forming a plurality of strongbacks from a first thermoplastic material; forming a plurality of comb subassemblies, each said comb subassembly including one of the plurality of strongbacks and a plurality of vanes comprising a second thermoplastic material extending outwardly from the respective one of the plurality strongbacks; and attaching the plurality of comb subassemblies into a unitary structure to produce the cascade array.

In one example, a method includes positioning, within a mold, a device with a movable element that defines a portion of a volume, and the volume is contained within the mold, as part of a molding process, at least partly defining a molded watercraft by introducing plastic into the mold, disposing the plastic about the movable element, and with the movable element, excluding the plastic from the portion of the volume that is defined by the movable element so as to define a recess and an undercut that are integral with the watercraft and extend lengthwise with respect to a centerline of the watercraft, and the recess and undercut are integral, and communicate, with each other.

A core system for the production of a fiber composite component includes at least two core elements which are coupled to one another and are displaceable relative to one another. At least one core element has a surface which is oblique to a displacement direction. A method for producing the fiber composite component uses the core system.

An eartip, mold device for manufacturing the eartip, and method of manufacturing the eartip are introduced, characterized by forming an upper bevel-portion with upper and lower molds of a first mold unit, placing the upper bevel-portion in an upper bevel receiving cavity of a second mold unit, forming a lower bevel-portion with a lower bevel cavity, and joining the upper and lower bevel-portions to form an eartip. The top of the lower hollow-cored guiding tube extends to form a buffer portion which connects and communicates with the upper hollow-cored guiding tube. The upper and lower bevel-portions are made of silicone of different rigidity. The upper bevel-portion thus made is soft enough to reach a user's ear canal deeply. The lower bevel-portion thus made is rigid enough to close the ear canal. An annular buffer cavity is inwardly, concavely formed at the bottom of the lower bevel cavity.

A method for producing an annular combustion chamber of a turbojet using CMC. For this, a shaping tool with movable slides is used and said chamber is produced around the tool, thereby producing a fibrous preform of which the shape is consolidated by drape moulding on the tool and pyrolysis, which is then densified by CVI. Several slides have back drafts, at least one other of such slides having a draft or neither a draft nor a back draft. Then, the slides are removed in a predetermined order imposed by the back drafts and the relative positions of the slides.

A machine for disassembling a lens mold assembly including a first mold part, a second mold part, and a molded-lens sandwiched therebetween. The machine includes a centering unit to center the lens mold assembly. The machine includes a disassembling module having a mold engagement mechanism to engage the first and second mold parts to clamp and move the lens mold assembly. The disassembling module includes a molded-lens holder mechanism having at least two clamping members to clamp the molded-lens of the lens mold assembly. The machine includes an alignment guidance module to detect relative positions between the molded lens of the lens mold assembly and the molded-lens holder mechanism to align the molded lens for clamping by the molded-lens holder mechanism. The mold engagement mechanism is configured to hold the first and second mold parts individually and to separate the first and second mold parts from the molded lens.

A mould comprises a mould body (1) for forming therearound a body (60) with a body cavity which is accessible via an opening. The mould body is assembled from a set of mutually cohesive body parts (30,40). The body parts (30,40) are mutually releasable and removable from the body via the opening. An inflatable body (60) can be manufactured with the mould. The inflatable body (60) comprises a wall of elastomer material, which wall at least in an inflated state of the body bounds a body cavity accessible through a wall opening. The body is inflatable by filling the body cavity with a fluid.

The present invention relates to a method of manufacturing a dental component, in particular a dental prosthesis or a partial dental prosthesis, by means of a dental furnace, comprising the following steps: (i) producing a model of the dental component; (ii) embedding the model in an investment material; (iii) removing the model from the investment material, in particular by heating or burning out, to obtain a negative mold of the model;

(iv) inserting a raw material required for manufacturing the dental component into the negative mold; (v) producing the dental component in the negative mold; and (vi) deflasking the dental component in an at least partly automated manner, in particular by means of a stripping manufacturing process, on the basis of a virtual model of the dental component.

A method of constructing a mandrel generally complementary to a spar cavity of a spar includes connecting a first component and a second component to form a central space there between and inserting a center component within the central space such that the center component retains the first component and second component in a desired position forming an outer surface of the mandrel which corresponds to an inner surface of the spar cavity.