Abstract: A blade of a rotor for a rotary-wing aircraft is equipped with an outer covering extending along the span of the blade. This outer covering is provided with an extrados skin and with an intrados skin defining a cavity. The blade also includes a structure that extends into the cavity and connects the blade to a hub of the rotor. The cavity is filled with a filling material that includes at least one partition parallel to a chord of the blade and at least two independent blocks of filling material filling the cavity, thereby allowing the reduction of the torsional rigidity along the span of the blade.

Abstract: A blade (1) of a rotor (100) for a rotary-wing aircraft equipped with an outer covering (2) extending along the span of the said blade (1). This outer covering (2) is provided with an extrados skin (2?) and with an intrados skin (2?) defining a cavity (8). The said blade (1) also includes structural means extending into the said cavity (8) and connecting the said blade (1) to a hub (110) of the said rotor (100). The said cavity (8) is filled with a filling material that includes at least one partition parallel to a chord of the said blade (1) [and] at least two independent blocks of filling material filling the said cavity (8), thereby allowing the reduction of the torsional rigidity along the span of the said blade (1).

Abstract: A rotor blade (1) with adaptive twisting, the blade being provided with an outer covering (2) extending along a pitch variation axis (AY) from a first end zone (3) to a second end zone (4), the outer covering (2) defining an internal cavity (8). The blade includes a strip (10) extending inside said cavity (8) along said pitch variation axis (AY), said strip (10) comprising a composite material that is anisotropic so as to be suitable for twisting under the effect of centrifugal forces (F) directed parallel to said pitch variation axis (AY) when the blade (1) is in rotation, said strip (10) being fastened to said outer covering (2) via first and second fastener means (11, 12) in order to be capable of twisting said outer covering (2).

Abstract: A rotor blade (1) with adaptive twisting, the blade being provided with an outer covering (2) extending along a pitch variation axis (AY) from a first end zone (3) to a second end zone (4), the outer covering (2) defining an internal cavity (8). The blade includes a strip (10) extending inside said cavity (8) along said pitch variation axis (AY), said strip (10) comprising a composite material that is anisotropic so as to be suitable for twisting under the effect of centrifugal forces (F) directed parallel to said pitch variation axis (AY) when the blade (1) is in rotation, said strip (10) being fastened to said outer covering (2) via first and second fastener means (11, 12) in order to be capable of twisting said outer covering (2).