| 摘要 |
PROBLEM TO BE SOLVED: To provide a helicopter blade flap control mechanism capable of reducing weight of airframe. SOLUTION: A flap 2 is attached at a rear edge near a wing tip of a blade 1 of a main rotor through an elastic body 3. An arm 4 is connected to a rear edge of a base part 11 of the blade 1. A pulley 51 provided on the arm 4. Pulleys 52, 53 are provided in a spur 12 of the blade 1. One end of a wire 6 is fixed on the flap 2 and another end of the wire 6 is fixed on a rotor hub 7. The wire 6 passes through the spur 12 and is wound on pulleys 51, 52 and 53. As a pitch angle of the blade 1 is increased, the flap 2 is pulled by the wire 6 and a flap angle is increased. When the tension of the wire 6 is released, the flap 2 returns to the original position and becomes flat by action of the elastic body 3.
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