Abstract: A method of fabricating a filler body for a blade of a rotor. In addition, such a method comprises a succession of steps of adding material layer by layer, each step consisting in making a new layer of material on a preceding layer of material made in the preceding step, at least one of the steps consisting in making an openwork layer of material presenting a plurality of openings, the succession of steps of adding material layer by layer generating openwork layers of material, each having a closed outline, the respective closed outlines of the openwork layers of material touching mutually in pairs and forming a closed envelope of the filler body for the blade.

Abstract: A rotorcraft comprising a fuselage, a single main rotor, and a first propeller and a second propeller. The rotorcraft has an adjustment system configured, at least during a stage of hovering flight, to position the first propeller in a first low speed configuration in order to exert a first thrust including a first horizontal component and a first vertical component, the adjustment system being configured, at least during the stage of hovering flight, to position the second propeller in a second low speed configuration so as to exert a second thrust comprising a second horizontal component and a second vertical component.

Abstract: A method of fabricating a blade spar that includes transversely at least one arrangement. A pressure-side mold and a suction-side mold are defined for each arrangement that is to be fabricated. Each mold includes at least one removable slide and a base. Each slide is then removed from a mold and the tape segments of a hank are laid by a fiber-placement method on each mold. Each mold is closed by putting the slides into place on the mold. During a finalizing step, the molds are juxtaposed and the spar is heated.

Abstract: A rotorcraft comprising a fuselage, a single main rotor, and a first propeller and a second propeller. The rotorcraft has an adjustment system configured, at least during a stage of hovering flight, to position the first propeller in a first low speed configuration in order to exert a first thrust including a first horizontal component and a first vertical component, the adjustment system being configured, at least during the stage of hovering flight, to position the second propeller in a second low speed configuration so as to exert a second thrust comprising a second horizontal component and a second vertical component.

Abstract: The present invention relates to a deposition head provided with an assemblage comprising a of impregnated fibers arranged against a backing tape. The deposition head includes a slide and a movement actuator connected to the slide to move the slide in translation from a high position to a low position, said slide carrying a peeling roller, said backing tape extending over a circular arc against the peeling roller, said low position being configured so that said peeling roller presses said tape of impregnated fibers against a deposition surface only in the low position of the slide, said circular arc occupying a first angle in the low position of the slide and a second angle in the high position of the slide, said first angle being greater than said second angle.

Abstract: A monolithic blade of a rotorcraft rotor, the blade comprising at least locally an airfoil zone having a pressure side face and a suction side face. The invention is remarkable in that the blade has a root zone including a finger with a spherical bearing surface arranged at a root end of the blade, a recess suitable for receiving a laminated spherical bearing, and a flexible portion having a preferred direction of deformation in bending about a flapping axis of the blade, the flexible portion being arranged between the finger and the recess.

Abstract: A method of fabricating a filler body for a blade of a rotor. In addition, such a method comprises a succession of steps of adding material layer by layer, each step consisting in making a new layer of material on a preceding layer of material made in the preceding step, at least one of the steps consisting in making an openwork layer of material presenting a plurality of openings, the succession of steps of adding material layer by layer generating openwork layers of material, each having a closed outline, the respective closed outlines of the openwork layers of material touching mutually in pairs and forming a closed envelope of the filler body for the blade.

Abstract: A method of fabricating a spar for a blade, which spar includes transversely at least one arrangement. A male former is defined for each arrangement that is to be fabricated and each arrangement is subdivided into a pressure-side subassembly and a suction-side subassembly, each comprising a plurality of hanks, each hank comprising a plurality of U-shaped tape segments stacked on one another. Each subassembly of an arrangement is fabricated outside a mold for fabricating the blade on a single former adapted to that particular arrangement, fabrication being by stacking tape segments on the former using a fiber placement method implemented by a placement head.

Abstract: A method of fabricating a blade spar that includes transversely at least one arrangement. A pressure-side mold and a suction-side mold are defined for each arrangement that is to be fabricated. Each mold includes at least one removable slide and a base. Each slide is then removed from a mold and the tape segments of a hank are laid by a fiber-placement method on each mold. Each mold is closed by putting the slides into place on the mold. During a finalizing step, the molds are juxtaposed and the spar is heated.

Abstract: A method of fabricating a spar for a blade, which spar includes transversely at least one arrangement. A male former is defined for each arrangement that is to be fabricated and each arrangement is subdivided into a pressure-side subassembly and a suction-side subassembly, each comprising a plurality of hanks, each hank comprising a plurality of U-shaped tape segments stacked on one another. Each subassembly of an arrangement is fabricated outside a mold for fabricating the blade on a single former adapted to that particular arrangement, fabrication being by stacking tape segments on the former using a fiber placement method implemented by a placement head.

Abstract: A method of fabricating a blade spar that includes transversely at least one arrangement. A pressure-side mold and a suction-side mold are defined for each arrangement that is to be fabricated. Each mold includes at least one removable slide and a base. Each slide is then removed from a mold and the tape segments of a hank are laid by a fiber-placement method on each mold. Each mold is closed by putting the slides into place on the mold. During a finalizing step, the molds are juxtaposed and the spar is heated.

Abstract: The present invention relates to a deposition head provided with an assemblage comprising a of impregnated fibers arranged against a backing tape. The deposition head includes a slide and a movement actuator connected to the slide to move the slide in translation from a high position to a low position, said slide carrying a peeling roller, said backing tape extending over a circular arc against the peeling roller, said low position being configured so that said peeling roller presses said tape of impregnated fibers against a deposition surface only in the low position of the slide, said circular arc occupying a first angle in the low position of the slide and a second angle in the high position of the slide, said first angle being greater than said second angle.

Abstract: A monolithic blade of a rotorcraft rotor, the blade comprising at least locally an airfoil zone having a pressure side face and a suction side face. The invention is remarkable in that the blade has a root zone including a finger with a spherical bearing surface arranged at a root end of the blade, a recess suitable for receiving a laminated spherical bearing, and a flexible portion having a preferred direction of deformation in bending about a flapping axis of the blade, the flexible portion being arranged between the finger and the recess.

Abstract: A device (20) for folding a blade (5), the device comprising a fitting (30) and a cuff (50) connected to said fitting (30). The fitting (30) has at least one horizontal pin axis (31) perpendicular to a radial direction (AX2) and a clevis (35) axially offset relative to the horizontal pin axis (31) in the radial direction (AX2). The cuff (50) has an insert (51) inserted in said clevis (35), a vertical pin (70) passing through said clevis (35) and said insert (51). The cuff (50) includes at least one horizontal fastener pin axis (55) axially offset relative to said insert (51) along the radial direction (AX2), at least one lateral arm (80) connects said horizontal pin axis (31) to said fastener pin axis (55).

Abstract: The invention provides a rotary-wing aircraft rotor fitted with a connector device for connecting electrical power between a hub (1) and blades (2) of said rotor. For each of the blades (2), a wired connection (4) provides an electrical connection between the hub (1) and the blade (2). A guide path (13, 14, 15, 16, 17) holds the wired connection (4) in shape and guides it under tension to move over itself, accompanying the pivoting movement of the blade root (3).

Abstract: A blade (1) provided with a fitting (2) for fastening to a hub and with an airfoil element (10) having a spar (20) extending spanwise from an attachment zone (21) towards a distal zone (22), said attachment zone (21) surrounding a centrifugal force transmission bushing (31) that is connected to said fitting (2) by a through pin (3). The blade comprises a twisting force transmission member (40) provided with a first half-shell (41) and with a second half-shell (42) that together surround said attachment zone (21), each half-shell (41, 42) having a perforated first portion (43?, 43?) giving visual access to said bushing (31) when said airfoil element is removed from the fitting, and a second portion (44?, 44?) co-operating with a torsion box (50) surrounding said distal zone (22), said transmission member (40) being secured to said fitting in rotation about a torsion axis (AX) of the blade (1).

Abstract: A rotorcraft rotor fitted with a device for damping lead-lag oscillations of the blades (2) of the rotor. The blades (2) are hinge-mounted on a rotary hub (1) of the rotor via respective sleeves (3). The damper device comprises a set of dampers (6), each individually housed in a respective one of said sleeves (3) and deformable between two fastening points (8, 9), one with the sleeve and the other with an engagement member (7) for engaging the hub (1) via a linkage (10). For each of the sleeve (3), the damper (6) housed by a given sleeve (3) is in hinged engagement with the linkage (10) via a lever arm (11) hinged to the sleeve (3).

Abstract: A method of fabricating a blade spar that includes transversely at least one arrangement. A pressure-side mold and a suction-side mold are defined for each arrangement that is to be fabricated. Each mold includes at least one removable slide and a base. Each slide is then removed from a mold and the tape segments of a hank are laid by a fiber-placement method on each mold. Each mold is closed by putting the slides into place on the mold. During a finalizing step, the molds are juxtaposed and the spar is heated.

Abstract: A method of fabricating a spar for a blade, which spar includes transversely at least one arrangement. A male former is defined for each arrangement that is to be fabricated and each arrangement is subdivided into a pressure-side subassembly and a suction-side subassembly, each comprising a plurality of hanks, each hank comprising a plurality of U-shaped tape segments stacked on one another. Each subassembly of an arrangement is fabricated outside a mold for fabricating the blade on a single former adapted to that particular arrangement, fabrication being by stacking tape segments on the former using a fiber placement method implemented by a placement head.

Abstract: A device (20) for folding a blade (5), the device comprising a fitting (30) and a cuff (50) connected to said fitting (30). The fitting (30) has at least one horizontal pin axis (31) perpendicular to a radial direction (AX2) and a clevis (35) axially offset relative to the horizontal pin axis (31) in the radial direction (AX2). The cuff (50) has an insert (51) inserted in said clevis (35), a vertical pin (70) passing through said clevis (35) and said insert (51). The cuff (50) includes at least one horizontal fastener pin axis (55) axially offset relative to said insert (51) along the radial direction (AX2), at least one lateral arm (80) connects said horizontal pin axis (31) to said fastener pin axis (55).