There is provided a multi-layer adhesive for reducing squeeze out. The multi-layer adhesive comprises a first adhesive layer having a first adhesive property and a second adhesive layer having a second adhesive property. The second adhesive property is different from the first adhesive property. The first adhesive layer and the second adhesive layer form a film adhesive. In another embodiment, there is provided a structure comprising a first component and a second component bonded with the multi-layer adhesive.

Disclosed is an actuator of an aircraft including at least one limit stop in which at least one of the bearing surfaces, named destructible bearing surface (19), has at least one destructible portion which is able to, and is arranged to, be irreversibly deformed under the effect of the co-operation by limit contact between the driving member bearing surface (19) and the driven member bearing surface (20), each destructible portion of each destructible bearing surface being mounted to be removable with respect to the stop so as to be able to be replaced. It relates to an aircraft including at least one actuator provided with such an actuator.

Method for manufacturing a base structure (8) of an aeronautical torsion box (1) for an aircraft (11) characterized in that it comprises the steps of: a.providing at least a fresh skin (3), at least one fresh stringer (4), at least a fresh front spar (5) and fresh rear spar (6), b.positioning the fresh skin (3), the at least one fresh stringer, the fresh spars (5, 6) in a curing tool in a configuration corresponding to that of a base structure (8), c.subjecting the structure (8) to a single curing cycle, obtaining a cured base structure (8).

Method for manufacturing a base structure (8) of an aeronautical torsion box (1) for an aircraft (11) characterized in that it comprises the steps of: a.providing at least a fresh skin (3), at least one fresh stringer (4), at least a fresh front spar (5) and fresh rear spar (6), b.positioning the fresh skin (3), the at least one fresh stringer, the fresh spars (5, 6) in a curing tool in a configuration corresponding to that of a base structure (8), c.subjecting the structure (8) to a single curing cycle, obtaining a cured base structure (8).

Highly integrated infused box made of composite material with two skins (3), several ribs (4), several stringers (5), a front spar and a rear spar, comprising a first semibox (1) and a second semibox (2) joined by connecting means, in which the first semibox (1) comprises one skin (3) and the ribs (4), and the second semibox (2) comprises one skin (3), the front spar, the rear spar and the stringers (5). A manufacturing method is also provided, which comprises forming processes for the first semibox (1), the second semibox (2) and an assembly process of the first semibox (1) with the second semibox (2).

A device for protecting a front spar structure of a central casing -of an aircraft wing and at least one item of equipment situated in the wing, comprising: a shielding surface extending in front of the front spar of the central casing, from a surface of an intersection between the wing and the fuselage delimited by the root of the wing, transversely to the surface of intersection, to a first rib of the central casing partially surrounding at least one item of equipment; and means -for fixing the shielding surface to the central casing producing an isostatic link.

An image projector to be installed in a space used for placing a dead mass to mitigate aeroelastic vibrations suffered by the horizontal stabilizer of an aircraft. The image projector replaces the dead mass. The image projector may be connectable to the surface of a closed rib of the horizontal stabilizer. The image projector may include a structural features configured to mitigate at least the same aeroelastic vibrations as the dead mass. The image projector is configured to project at least one image.

An aerodynamic profile for an aircraft, comprises a core (6, 7, 8) made of foam, a skin (11, 12) defining an outer surface of the wing and cloths (14) form-ing spars and/or ribs. The profile comprises a wing, a canard, a horizontal stabiliser, a vertical stabiliser, an aileron, a flaperon, a wingtip winglet, an elevator, an elevon, a rudder or a flap.

An aerodynamic profile for an aircraft, comprises a core (6, 7, 8) made of foam, a skin (11, 12) defining an outer surface of the wing and cloths (14) form-ing spars and/or ribs. The profile comprises a wing, a canard, a horizontal stabiliser, a vertical stabiliser, an aileron, a flaperon, a wingtip winglet, an elevator, an elevon, a rudder or a flap.