Abstract: A rotor blade (1) provided with an outer covering (2) and with at least one load take-up spar (10) associated with at least one pin-receiving bushing (3). Each spar (10) is a compartmentalized spar comprising centrifugal force take-up means (20) incorporated within a twisting stress take-up casing (30), said centrifugal force take-up means (20) comprising at least two boxes (21, 22), each having said pin-receiving bushing (3) of the spar (10) passing therethrough, each box (21, 22) including a closed retention belt (23) extending in the spanwise direction of the blade, the retention belt (23) of one box (22) surrounding the retention belt (23) of another box (21), each retention belt (23) being provided with unidirectional fibers (24) wound around said pin-receiving bushing (3), said casing (30) being provided with inclined fibers (31) presenting an angle relative to said unidirectional fibers (24).

Abstract: Method for fabricating a reinforcing coating for a part made of composite material. Pre-impregnated reinforcing fibers are used in the form of slivers and said slivers are laid on the part in two layers of longitudinal slivers by being placed thereon. This fabrication makes provision for using an angular orientation for the slivers of each layer respectively of 0° and of some other angle relative to said determined direction of the solid body for covering using an interlaced pattern type that gives layer crossing lines parallel to a longitudinal axis of the solid body for covering, which pattern type is selected to form interlacing patterns that limit the number of layer crossing lines along the longitudinal axis of the solid body for covering to a single line.

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 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 rotor blade (1) provided with an outer covering (2) and with at least one load take-up spar (10) associated with at least one pin-receiving bushing (3). Each spar (10) is a compartmentalized spar comprising centrifugal force take-up means (20) incorporated within a twisting stress take-up casing (30), said centrifugal force take-up means (20) comprising at least two boxes (21, 22), each having said pin-receiving bushing (3) of the spar (10) passing therethrough, each box (21, 22) including a closed retention belt (23) extending in the spanwise direction of the blade, the retention belt (23) of one box (22) surrounding the retention belt (23) of another box (21), each retention belt (23) being provided with unidirectional fibers (24) wound around said pin-receiving bushing (3), said casing (30) being provided with inclined fibers (31) presenting an angle relative to said unidirectional fibers (24).

Abstract: An electrical power supply device (10) provided with electrically-conductive metal electrical connection means (12) secured to an electrical power supply wire (11), said connection means (12) comprising a first portion (13) connected to said power supply wire (11), followed by a second portion (14) that extends longitudinally and that is suitable for being permanently bonded to a resistor element (3) that is provided with a plurality of electrically-conductive layers (4). Said second portion (14) is tapering, presenting thickness (e) that decreases, starting from said first portion (13), said second portion (14) having at least one slot (15) passing through said second portion (14) in said direction in elevation.

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: Method for fabricating a reinforcing coating for a part made of composite material. Pre-impregnated reinforcing fibers are used in the form of slivers and said slivers are laid on the part in two layers of longitudinal slivers by being placed thereon. This fabrication makes provision for using an angular orientation for the slivers of each layer respectively of 0° and of some other angle relative to said determined direction of the solid body for covering using an interlaced pattern type that gives layer crossing lines parallel to a longitudinal axis of the solid body for covering, which pattern type is selected to form interlacing patterns that limit the number of layer crossing lines along the longitudinal axis of the solid body for covering to a single line.

Abstract: A blade (10) of a rotary wing (3), the blade being rigid in twisting and extending from a root (11) to a free end (12), said blade (10) including at least one swept-back segment (23). The blade (10) includes movable twist means (30) fastened to the swept-back segment (23), said blade (10) having actuator means (40) for twisting the blade (10) by varying the angular position of said twist means (30) relative to said swept-back segment (23).

Abstract: The present invention relates to a rotorcraft rotor blade (1) that comprises at least one tiltable trailing-edge flap (5), said flap (5) being suitable for pivoting about a virtual hinge axis (Y?) extending substantially in the span direction of said blade (1) and of said flap (5). The blade (1) is remarkable in that the flap (5) is provided with at least two fastener ball joints (30), each provided with an inner cage (32) together with an outer cage (33) and a first pin (31) that is also secured to said flap (5), the first pins (31) of the fastener ball joints (30) being perpendicular to the virtual pivot axis (Y?) of the flap (5). In addition, the blade (1) is provided at its trailing edge (BF) with a fastener tongue (20) provided with ball-receiving sockets (21), the outer cages (33) of the fastener ball joints (30) being secured to the ball-receiving sockets (21).

Abstract: The present invention relates to a rotorcraft rotor blade (1) having at least one trailing edge flap (5) that is tiltable, the flap (5) being suitable for pivoting about a virtual hinge axis (Y?) extending substantially along the span of the blade (1) and of the flap (5). The blade (1) is remarkable in that the flap (5) is provided with at least one main ball joint (30) having an inner cage (32) and an outer cage (33), and a first shaft (31) secured to the flap (5), the front portion (33?) of the outer cage (33) of the main ball joint (30) being connected to a linear actuator (10) which is arranged in the blade (1) and which enables the flap (5) to be pivoted, the first shaft (31) of the main ball joint (30) extending substantially perpendicularly to the virtual hinge axis (Y?) about which the flap (5) pivots.

Abstract: A rotorcraft rotor blade (1) includes at least one tiltable trailing-edge flap (5), the flap (5) being suitable for pivoting about a virtual hinge axis (Y?) extending substantially along the span of the blade (1) and of the flap (5). The blade (1) is remarkable in that it is provided with at least one main ball joint (30) provided with an inner cage (32) together with a first pin (31) and an outer cage (33), the front portion (33?) of the outer cage (33) of the main ball joint (30) being connected to a linear actuator (10, 10?) arranged in the blade (1) and serving to pivot the flap (5), the first pin (31) of the main ball joint (30) being substantially perpendicular to the virtual hinge axis (Y?) about which the flap (5) pivots.

Abstract: A rotary-wing aircraft rotor blade (23) includes (semi)conductive loops (10) extending along axes (19A to 19C, 19W to 19Z) that are oblique relative to the longitudinal axis (26) of the blade. Impedance changes in the loops are sensed that indicate a location of damage to the blade.

Abstract: The present invention relates to a rotorcraft rotor blade (1) including at least one tiltable trailing-edge flap (5), said flap (5) being suitable for pivoting about a virtual hinge axis (Y?) extending substantially along the span of said blade (1) and of said flap (5). The blade (1) is remarkable in that it is provided with at least one main ball joint (30) provided with an inner cage (32) together with a first pin (31) and an outer cage (33), the front portion (33?) of said outer cage (33) of the main ball joint (30) being connected to a linear actuator (10, 10?) arranged in said blade (1) and serving to pivot said flap (5), said first pin (31) of the main ball joint (30) being substantially perpendicular to said virtual hinge axis (Y?) about which said flap (5) pivots.

Abstract: The present invention relates to a rotorcraft rotor blade (1) that comprises at least one tiltable trailing-edge flap (5), said flap (5) being suitable for pivoting about a virtual hinge axis (Y?) extending substantially in the span direction of said blade (1) and of said flap (5). The blade (1) is remarkable in that the flap (5) is provided with at least two fastener ball joints (30), each provided with an inner cage (32) together with an outer cage (33) and a first pin (31) that is also secured to said flap (5), the first pins (31) of the fastener ball joints (30) being perpendicular to the virtual pivot axis (Y?) of the flap (5). In addition, the blade (1) is provided at its trailing edge (BF) with a fastener tongue (20) provided with ball-receiving sockets (21), the outer cages (33) of the fastener ball joints (30) being secured to the ball-receiving sockets (21).

Abstract: The present invention relates to a rotorcraft rotor blade (1) having at least one trailing edge flap (5) that is tiltable, the flap (5) being suitable for pivoting about a virtual hinge axis (Y?) extending substantially along the span of the blade (1) and of the flap (5). The blade (1) is remarkable in that the flap (5) is provided with at least one main ball joint (30) having an inner cage (32) and an outer cage (33), and a first shaft (31) secured to the flap (5), the front portion (33?) of the outer cage (33) of the main ball joint (30) being connected to a linear actuator (10) which is arranged in the blade (1) and which enables the flap (5) to be pivoted, the first shaft (31) of the main ball joint (30) extending substantially perpendicularly to the virtual hinge axis (Y?) about which the flap (5) pivots.

Abstract: The present invention relates to a rotary-wing aircraft rotor blade (23) that presents a longitudinal axis (26) and that includes (semi)conductive loops (10) extending along axes (19, 19A to 19C, 19W to 19Z) or directions that are oblique relative to the longitudinal axis (26).

Abstract: The method comprises the following steps: producing a preform of the blade comprising a blade root section for connection to a hub and an aerodynamically profiled main blade section, the blade root section of the preform including at least one cylindrical portion for guidance in terms of incidence; arranging a respective peripheral metal ring around each cylindrical portion for guidance in terms of incidence of the preform; arranging the preform provided with each peripheral metal ring in an injection mould; injecting a thermosetting liquid resin into the mould; and heating the mould to make the thermosetting resin set.

Abstract: The method includes the following steps: producing a preform of the blade comprising a blade root section for connecting to a hub and an aerodynamically profiled main blade section, the preform including, in the blade root section, a pile of fabrics transverse to the span axis of the blade projecting with respect to the blade root section, so as to form a pitch control lever; arranging the preform in an injection mold; injecting a thermosetting liquid resin into the mold; and heating the mould to make the thermosetting resin set.