Abstract: The present invention relates to a sighting system for an aircraft, in particular a rotary wing aircraft such as a helicopter. According to the invention, the sighting system comprises, in combination, an observation first individual apparatus integrated in the sides of the aircraft, and an axial fire second individual apparatus integrated at the front of aircraft, said first and second apparatuses being connected to the onboard computer of the aircraft.

Abstract: A gunsight device for a rotating-wing aircraft having a hollow rotor hub (1), on which there are radially mounted blades constituting said rotating wing, and which is connected to the main transmission box (2) by a drive shaft coaxial with the rotor of the aircraft. The device includes a nonrotating gunsight head (3) mounted, by means of a support (4), at the free upper end (5a) of a nonrotating mast (5) arranged coaxially inside the hub (1) and the drive shaft of the rotor, the other end (5b) of which mast is fixed into the main transmission box (2), a rolling contact bearing (6) coaxial with the rotor axis being provided between the hub (1) and the mast (5). A suspension (7), intended to filter out the excitations in roll and in pitch to which said gunsight head (3) is subjected, is provided between the base (4a) of the support (4) of the gunsight head (3) and the upper end (5 a) of the mast (5).

Abstract: The blade has its lower-surface and upper-surface skins of its shell, its front and rear filling bodies and its spar made of a composite material having the same thermoplastic matrix, preferably made of PEEK, reinforced preferably with carbon fibres. The spar is extended outside the shell by an integrated rooting part with linkage attachment, in a loop or laminate, in the same thermoplastic composite. The method consists in assembling the spar with the skins, after manufacturing these components in the form of prefabricated elementary pieces, by injecting under pressure a fluidized thermoplastic composite with short reinforcing fibres moulding the filling bodies.

Abstract: The vane (9) comprises a hollow metal central part forming its main vane section (24) and the vane (9) root (17) and vane (9) tip (18) are each arranged as an end fitting (25, 28) equipped with at least one transverse tab (26, 29) for fastening the vane (9). The method of manufacture consists in extruding a hollow metal section of cross-section corresponding to the aerodynamic profile of the vane, in cutting off a section portion of length not substantially less than the span of the vane, and in arranging each end of the section portion as an end fitting with at least one fastening tab, either by machining and deformation of the ends of the section portion, or by fitting end fittings attached to its ends.

Abstract: Electrical connector (CE) including a module carrier (PM) and a wiring chamber which are adjacent. The wiring chamber consists of two shells (C1, C2) which can be joined together, as well as to the module carrier (PM). Ducts (CH), consisting of two half-ducts which can be joined longitudinally, are provided for passage of the conductors. The ducts (CH) are held solidly fastened to the wiring chamber by being held captive between the two joined shells (C1, C2).

Abstract: For producing connections made from composite material for structures having at least two hollow or non-hollow bars, interconnected by at least one hollow connecting joint, separate production takes place of blanks of said different parts with the definitive shapes, but in which the impregnation resin for the assembly of said blanks has not yet been introduced, after which they are assembled by thermosetting resin transfer moulding, so as to produce the resin matrix of the connecting joint or the complete structure at the same time as the assembly. The blanks of the connecting joints are obtained by compressing a planar textile complex formed from hot preformable textile fibers between a cavity of a shaping mould and a countermould, by cutting and folding down onto the countermould the overlap parts and performing a thermal preforming cycle.

Abstract: Electrical connector including a module carrier (PM) and a wiring chamber which are adjacent. The connector includes several connection modules (MC) arranged in rows and in columns to give the module carrier (PM) an at least approximately square section. The wiring chamber consists of two shells (C1, C2) which can be joined together, as well as to the module carrier.

Abstract: A device for reading identification marks on an electrical cable (1), including at least one group of signs written longitudinally one after the other on the external surface of a longitudinal portion of the sheath (4) of the cable, includes a lighting assembly (30) and a camera (25) which are capable of forming the image of a longitudinal line of the external surface of the longitudinal sheath portion in order to form, longitudinal line by longitudinal line, the complete peripheral image of the external surface of the longitudinal sheath portion.

Abstract: A helicopter comprising: a single main rotor for forwards motion and for support; and an anti-torque system comprising: an auxiliary, anti-torque rotor rotated from the engine means of said main rotor and exerting controllable anti-torque lateral thrust; and at least one steering airfoil that is controllable in steering and that generates anti-torque transverse lift. According to the invention, the helicopter includes automatic swivel control means for automatically controlling the swivel angle of said steering airfoil as a function of the collective pitch angle of said main rotor and of the forward speed of said helicopter.

Abstract: Mechanical assembly for transmitting forces along an axis driven by a substantially axial movement in translation under the effect of a thrust load. This mechanical assembly comprises a transmitting part of the thrust load input movement and a receiving part of the thrust load output movement, said mechanical assembly comprising a detector for detecting the passing of a force threshold represented by a predetermined value of the thrust load, and including an elastic element and an indicator part arranged in such a way that when the thrust load exceeds the threshold value, the thrust load acts on the elastic element and modifies its axial dimension allowing the indicator part to move to the warning position.

Abstract: A device for linking a blade to the hub comprising a laminate attachment at the end of the rooting part with torsion bars of the blade, the laminate attachment being in abutment against the pins for holding on the hub. The opposite blades of the rotor may be arranged angularly offset with respect to the other blades.

Abstract: The variation in the length of the chord L and the variation of the offset Y'f of the aerodynamic center are such that the leading edge (5) and the trailing edge (6) of the blade (1), along its longitudinal extent, exhibit no break, the overall aerodynamic center of said blade Being substantially situated on the pitch variation axis.