ADAPTABLE ROTOR BLADE DESIGN FOR PERFORMANCE FLEXIBILITY

ADAPTABLE ROTOR BLADE DESIGN FOR PERFORMANCE FLEXIBILITY

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,...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: SUTTON, Drew A, PHILLIPS, Nolan B, WASIKOWSKI, Mark E, MARESH, Andrew Ryan
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
AEROPLANES
AIRCRAFT
AVIATION
COSMONAUTICS
HELICOPTERS
PERFORMING OPERATIONS
TRANSPORTING
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Beschreibung
Zusammenfassung: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.