Abstract: A blade, for a rotor of an aircraft, comprising a hollow cylindrical sleeve, a stop fastened to the cylindrical sleeve, a profiled portion, and an anchoring device, a blade body and a hollow torsion box secured to the profiled portion. The anchoring device and the blade body are positioned inside the cylindrical sleeve. The anchoring device surrounds the stop in order to form a stop for the profiled portion parallel to a longitudinal axis of the blade. The hollow torsion box is secured to the profiled portion, and comprises a bearing zone in contact with an inner wall of the cylindrical sleeve, taking up the bending loads on the blade.

Abstract: A blade (1) having an outer covering (2) defining a cavity (8). A carriage (20) is arranged in said cavity (8), the carriage (20) being provided with a torsion bar (21) and at least two arms (22) secured to the torsion bar (21). The blade has one connection per arm provided both with an upstream guide gallery and with a downstream guide gallery, each arm extending transversely from an upstream end that slides in an upstream guide gallery to a downstream end that slides in a downstream guide gallery. At least one connection is a helical connection (40) obtained with the help of an upstream guide gallery (33) and the downstream guide gallery (34) of the segment (101) presenting distinct orientations, giving rise to movement in rotation (ROT1) of the segment (101) under the effect of the carriage (20) moving in translation.

Abstract: A twist mechanism for twisting a rotary-wing blade (2). A twist member (8) is movable by an actuator (11) of the centrifugal force type, which twist member has at least one flyweight (14) for driving a rotary member (13) about a pivot axis (A). The flyweight (14) is radially movable on the rotary member (13) by movement means. The centrifugal force FC to which the flyweight (14) is subjected as a result of the blade (2) being caused to rotate induces drive torque CM for causing the rotary member (13) to pivot, thereby causing the twist member (8) to be moved. The twist member (8) is in engagement with the blade (2) at its free end and is connected to the rotary member (13) via remote mechanical transmission means (12).

Abstract: A blade (1) having an outer covering (2) defining a cavity (8). A carriage (20) is arranged in said cavity (8), the carriage (20) being provided with a torsion bar (21) and at least two arms (22) secured to the torsion bar (21). The blade has one connection per arm provided both with an upstream guide gallery and with a downstream guide gallery, each arm extending transversely from an upstream end that slides in an upstream guide gallery to a downstream end that slides in a downstream guide gallery. At least one connection is a helical connection (40) obtained with the help of an upstream guide gallery (33) and the downstream guide gallery (34) of the segment (101) presenting distinct orientations, giving rise to movement in rotation (ROTI) of the segment (101) under the effect of the carriage (20) moving in translation.

Abstract: A twist mechanism for twisting a rotary-wing blade (2). A twist member (8) is movable by an actuator (11) of the centrifugal force type, which twist member has at least one flyweight (14) for driving a rotary member (13) about a pivot axis (A). The flyweight (14) is radially movable on the rotary member (13) by movement means. The centrifugal force FC to which the flyweight (14) is subjected as a result of the blade (2) being caused to rotate induces drive torque CM for causing the rotary member (13) to pivot, thereby causing the twist member (8) to be moved. The twist member (8) is in engagement with the blade (2) at its free end and is connected to the rotary member (13) via remote mechanical transmission means (12).

Abstract: A rotorcraft blade (P) is provided in succession with a radial segment (1) and then a swept segment (2), the swept segment (2) being provided with at least one forwardly-swept segment (2?) and/or rearwardly-swept segment (2?). In addition, the blade has a single spar coming from the blade root. The invention is remarkable in that the single spar includes a radial spar (10) in the radial segment (1), after which the single spar splits where the radial segment (1) becomes the swept segment (2) to form thereafter in the swept segment (2) a primary spar (11) and a secondary spar (12).

Abstract: The present invention relates to a rotorcraft blade (1) provided with a distributed spar (10) on a leading edge (4), a suction side (2), and a pressure side (3) of the blade, and the invention also relates to a method of fabricating such a spar. The blade is provided with a fastener insert (20) integrated in the blade root for the purpose of fastening the blade to a rotor, the fastener insert (20) comprising a horizontal shaft (21) perpendicular to the span of the blade and to an axis of rotation of said rotor, with the distributed spar (10) of the blade being wound in part about the horizontal shaft.

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 blade (1) provided with a distributed spar (10) on a leading edge (4), a suction side (2), and a pressure side (3) of the blade, and the invention also relates to a method of fabricating such a spar. The blade is provided with a fastener insert (20) integrated in the blade root for the purpose of fastening the blade to a rotor, the fastener insert (20) comprising a horizontal shaft (21) perpendicular to the span of the blade and to an axis of rotation of said rotor, with the distributed spar (10) of the blade being wound in part about the horizontal shaft.

Abstract: The present invention relates to a rotorcraft blade (P) provided in succession with a radial segment (1) and then a swept segment (2), said swept segment (2) being provided with at least one forwardly-swept segment (2?) and/or rearwardly-swept segment (2?). In addition, the blade has a single spar coming from the blade root. The invention is remarkable in that the single spar comprises a radial spar (10) in the radial segment (1), after which the single spar splits where the radial segment (1) becomes the swept segment (2) to form thereafter in the swept segment (2) a primary spar (11) and a secondary spar (12).

Abstract: The invention concerns a hybridome called 5C5 (CNCM no I-2184) and the monoclonal antibody 5C5 which it produces. Said monoclonal antibody which specifically recognises most human renal cell carcinomas, is developed for diagnosing, imaging and treating human renal cell carcinomas.

Abstract: Compounds inhibiting the activation of the nuclear factor ?B (NF-?B) are used for the preparation of medications adapted for the treatment of malignant hemopathies and solid tumors, and for the prevention of the appearance or the treatment, of phenomena of resistance to cytotoxic molecules used in the scope of treatment of the above pathologies, appearing in patients treated with these molecules when the latter are adapted to activate NF-?B.

Abstract: Compounds inhibiting the activation of the nuclear factor ?B (NF-?B) are used for the preparation of medications adapted for the treatment of malignant hemopathies and solid tumors, and for the prevention of the appearance or the treatment, of phenomena of resistance to cytotoxic molecules used in the scope of treatment of the above pathologies, appearing in patients treated with these molecules when the latter are adapted to activate NF-?B.

Abstract: The present invention describes a DNA-antibody conjugate and a method for integration of foreign DNA into cells in a tissue-specific manner by conjugating the foreign DNA with a target specific antibody.