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).
BLADE WITH REDUCED TORSIONAL RIGIDITY, AND ROTOR EQUIPPED WITH SUCH A BLADE
22.10.2015
Patent
Elektronische Ressource
Englisch
Blade with reduced torsional rigidity, and rotor equipped with such a blade
Europäisches Patentamt | 2020
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