In one embodiment, a rotor blade may comprise a blade body (300), a spar structure (306a-b), and a blade nose (308). The blade body (300) may comprise a skin (311), wherein the skin (311) is configured to form an airfoil shape, and wherein the airfoil shape comprises an inboard end, an outboard end, a leading edge (303), and a trailing edge (304). The spar structure may comprise a first spar cap (306a) and a second spar cap (306b), wherein the first spar cap (306a) is coupled to an upper portion of the skin (311), and wherein the second spar cap (306b) is coupled to a lower portion of the skin (311). The blade nose (308) may comprise a cavity, wherein the cavity is configured to house a plurality of modular weights (310) at a plurality of radial blade locations, wherein the plurality of radial blade locations comprises a range of locations between the inboard end and the outboard end.
ADAPTABLE ROTOR BLADE DESIGN FOR PERFORMANCE FLEXIBILITY
ROTORBLATTDESIGN MIT AJUSTIERBARER LEISTUNG
CONCEPTION DE PALE DE ROTOR PERMETTANT UN AJUSTAGE DE SA PERFORMANCE
2019-11-13
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
ADAPTABLE ROTOR BLADE DESIGN FOR PERFORMANCE FLEXIBILITY
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