| 摘要 |
A flap actuation system for a helicopter rotor blade (10). The rotor blade (10) includes a root end, a tip end, a trailing edge and a flap hinged to at least a portion of the trailing edge about a pivot axis. The flap actuation system includes at least one supply line (26) mounted within the rotor blade and extending outward from the root end. The supply line (26) is adapted to channel pressurized fluid. At least one actuator (28) fluidly connected to the supply line (26). The actuator (28) includes a displacement member (32) and a head member (30). The head member (30) is engaged with the flap (18) and is adapted to pivot the flap (18) about its pivot axis when pressurized fluid is conveyed through the supply line (26). In one embodiment of the invention there are two supply lines (26A, 26B), each extending outward from the root end and is adapted to channel pressurized fluid. There is at least one actuator (28A, 28B) fluidly connected to each supply line (26A, 26B). The actuator (28A) on one of the supply lines (26A) is adapted to pivot the flap (18) upward when pressurized, and the actuator (28B) on the other supply line (26B) is adapted to pivot the flap (18) downward when pressurized.
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