Abstract: The present invention relates to a rotorcraft blade (1) provided with at least one spar (3) and an outer covering (4), said blade (1) including a hollow sleeve (10) with a wall (11) that is provided at least with said outer covering (4) secured to said spar (3). The blade includes a rotary damper (20) provided with an inner tubular strength member (21) and an outer tubular strength member (22) that are coaxial and connected together by a ring (23) of viscoelastic material, said inner tubular strength member (21) being secured to said covering (4), and said outer tubular strength member (22) being provided with a fork (25) possessing first and second tines (26, 27) facing each other so as to be suitable for receiving a first ball joint (41) close to the pitch-variation axis (AX1) of said blade (1).

Abstract: A method of forming a rotorcraft blade is provided. A first support shaft (8) is secured to a rigid attachment filler (1) of the blade that is reversibly fastened to a mandrel (20). Fibers are placed around the assembly comprising said attachment filler (1) and said mandrel (20) in order to fabricate a spar of said blade, said spar (40) then including a succession of fiber layers (31, 32, 33) that hold said attachment filler (1) captive at the root (51) of said blade. Said first shaft (8) is removed after the spar has polymerized.

Abstract: A method of forming a rotorcraft blade is provided. A first support shaft (8) is secured to a rigid attachment filler (1) of the blade that is reversibly fastened to a mandrel (20). Fibers are placed around the assembly comprising said attachment filler (1) and said mandrel (20) in order to fabricate a spar of said blade, said spar (40) then including a succession of fiber layers (31, 32, 33) that hold said attachment filler (1) captive at the root (51) of said blade. Said first shaft (8) is removed after the spar has polymerized.

Abstract: The present invention relates to a rotorcraft blade (1) provided with a dynamic balancing system having a balancing device (10). The balancing device (10) is embedded in the inside (INT) of the body of the blade (1) in such a manner that it does not open to the outside (EXT) of said blade (1).

Abstract: A rotorcraft rotor blade (1) has a blade root (1?) and a free end opposite from the blade root (1?), the blade (1) being provided at least with a spar (2) laid flat on a suction-side face (3) and a pressure side-face (4) of the blade (1), the main spar (2) being secured to an attachment fitting (5) at the blade root (1?). The attachment fitting (5) then includes first and second horizontal fastener bushings (10, 20), the first and second fastener bushings (10, 20) being both perpendicular to the span of the blade (1) and substantially perpendicular to an elevation direction (Z) that is substantially parallel to gravity (W), the elevation direction (Z) being perpendicular to the span.

Abstract: A rotorcraft blade is provided with a rigid attachment filler (1) and with a spar (40) that extends from a root (51) of the blade to a free end (52) of the blade, the attachment filler (1) having top, bottom, front, rear, left side, and right side faces (2, 3, 4, 5, 7, and 6). The spar (40) then includes a succession of fiber layers (31, 32, 33) that hold the attachment filler (1) captive at the root (51) of the blade, the spar (40) being secured to the top, bottom, front, rear, and left side faces (2, 3, 4, 5, and 7) of the attachment filler (1).

Abstract: The present invention relates to a rotorcraft blade (1) provided with at least one spar (3) and an outer covering (4), said blade (1) including a hollow sleeve (10) with a wall (11) that is provided at least with said outer covering (4) secured to said spar (3). The blade includes a rotary damper (20) provided with an inner tubular strength member (21) and an outer tubular strength member (22) that are coaxial and connected together by a ring (23) of viscoelastic material, said inner tubular strength member (21) being secured to said covering (4), and said outer tubular strength member (22) being provided with a fork (25) possessing first and second tines (26, 27) facing each other so as to be suitable for receiving a first ball joint (41) close to the pitch-variation axis (AX1) of said blade (1).

Abstract: The present invention relates to a rotorcraft blade (1) provided with a dynamic balancing system having a balancing device (10). The balancing device (10) is embedded in the inside (INT) of the body of the blade (1) in such a manner that it does not open to the outside (EXT) of said blade (1).

Abstract: A rotorcraft blade is provided with a rigid attachment filler (1) and with a spar (40) that extends from a root (51) of the blade to a free end (52) of the blade, the attachment filler (1) having top, bottom, front, rear, left side, and right side faces (2, 3, 4, 5, 7, and 6). The spar (40) then includes a succession of fiber layers (31, 32, 33) that hold the attachment filler (1) captive at the root (51) of the blade, the spar (40) being secured to the top, bottom, front, rear, and left side faces (2, 3, 4, 5, and 7) of the attachment filler (1).

Abstract: A rotorcraft rotor blade (1) has a blade root (1?) and a free end opposite from the blade root (1?), the blade (1) being provided at least with a spar (2) laid flat on a suction-side face (3) and a pressure side-face (4) of the blade (1), the main spar (2) being secured to an attachment fitting (5) at the blade root (1?). The attachment fitting (5) then includes first and second horizontal fastener bushings (10, 20), the first and second fastener bushings (10, 20) being both perpendicular to the span of the blade (1) and substantially perpendicular to an elevation direction (Z) that is substantially parallel to gravity (W), the elevation direction (Z) being perpendicular to the span.