A joining structure includes a first member, a second member of a material different from that of the first member, and a separation mechanism provided between the first member and the second member and that separates the first member and the second member from each other, wherein a resin is filled into the space between the edge of at least one member among the first member and the second member, and the other member.

The invention provides a fitted platform (1) for positioning between two adjacent blades of an aviation turbine engine fan, said platform comprising a flow passage wall (10) made of composite material having a central portion (16) and first and second margins (18) each extending in a longitudinal direction of said wall, each margin extending over a determined distance (D) from the central portion (16) in a transverse direction of said wall, said flow passage wall comprising fiber reinforcement densified by a matrix, the platform being characterized in that the fiber reinforcement present in the central portion (16) presents three-dimensional weaving, and in that the fiber reinforcement present in the first and second margins (18) presents two-dimensional weaving, at least in part. The invention also provides a fan module, a turbine engine, and a method of fabricating such a platform.

A component having a flat reinforcing element of a first stiffness and a flat material of a second stiffness. The first stiffness is higher than the second stiffness. The flat reinforcing element has a first end on a first narrow side. The flat material, on a second narrow side thereof, has a second end that bifurcates into two strips. The two strips of the second end enclose the first end on both sides in a zone of enclosure.

Provided is a composite (A) including a metal plate (B) and a reinforcing member (C) that is made of a resin. The metal plate (B) includes a joint portion (2) that is continuous with one end of a body portion (1), a hole that is formed through the body portion (1) in a thickness direction of the body portion (1) in the proximity of the joint portion (2), and a guide portion provided around the hole. The reinforcing member (C) continuously includes a main portion (5), a coupling portion (6) formed in the hole (3), and a locking portion (7) that is held in close contact with a surface on another side of the body portion (1). The guide portion (4) is at least one of a protruding portion provided on at least one of a rear side and a lateral side relative to the hole (3) in a direction from the body portion (1) to the joint portion (2), and a recessed portion extended from a front side relative to the hole (3) to the hole (3) in the direction from the body portion to the joint portion. In insert molding of the composite (A), a molten resin is introduced preferentially into the hole (3). With this, the joint portion (2) is formed reliably in good condition free from adhesion of the resin.

A fiber-reinforced polymer composite assembly, that includes a plurality of sheets, each formed from a composite mixture including a fibrous material and a resin, wherein each of the first plurality of sheets are cut to one or more predetermined dimensions. The plurality of sheets are configured to form a stack, and wherein the stack is shaped by positioning the stack on a mold and pressing and consolidating/curing the stack to form a doubly-curved geometric shape. An insert may be positioned between the plurality of sheets, prior to the pressing and consolidating/curing, wherein the fibrous material may in include paper, and wherein the resin includes one of a thermoset resin or a thermoplastic resin.

A fiber preform is provided for use in an overmolding process that includes a fiber bundle arranged in a predetermined pattern and attached to itself by a plurality of stitches of a thread to form at least one preform layer. At least one positioning element is associated with the at least one preform layer, the at least one positioning element configured to engage with at least one corresponding alignment element on a mold to indicate proper positioning of the fiber preform within the mold. A process of overmolding is also provided in which the at least one positioning element of the fiber preform engages with the at least one corresponding alignment element on the mold to indicate proper positioning. The mold cavity is then filled with a resin to permeate the fiber preform engaging the mold in a unique orientation to yield an article upon resin cure.

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.

A process for the production of composite materials at low temperatures, as well as a composite material obtained by the process and articles of manufacture comprising the composite material are provided.

According to the present invention, there is provided a pipe forming apparatus for forming a pipe at an installation site. The apparatus includes a former upon which material is wound, and a mold for receiving the former bearing the wound material. An applicator is provided for applying curable liquid within the mold. Advantageously, the pipe is formed at site to provide for efficient formation of a pipeline. A transported ISO container providing the material and curable liquid to the site can produce 800 metres of pipeline section, compared with 60 metres in the prior art, representing a significant increase in efficiency.

A canister for storing and launching a self-propelled projectile comprises: a) an inner layer comprising an aluminum foil; b) a top layer consisting of an injected thermoplastic polymer; and c) optionally, a primer and/or a topcoat.