초록 ▼

A helicopter rotor blade that has a blade body and a control flap secured to the blade body. The rotor blade has a first primary mover capable of generating a first linear motion that is sufficient to generate a high amplitude, low frequency motion of the control flap; and a second primary mover cap

A helicopter rotor blade that has a blade body and a control flap secured to the blade body. The rotor blade has a first primary mover capable of generating a first linear motion that is sufficient to generate a high amplitude, low frequency motion of the control flap; and a second primary mover capable of generating a second linear motion that is sufficient to generate a small amplitude, high frequency motion of the control flap. Further, the rotor blade has a coupling transmission for combining the first linear motion with the second linear motion that generates a cumulative linear motion; and a second transmission device that causes the cumulative linear motion to rotate the control flap.

대표청구항 ▼

What is claimed is: 1. A helicopter rotor blade comprising: a blade body; a control flap rotatably secured to said blade body; a first primary mover operable to generate a first linear motion, said first linear motion operable to generate a high amplitude, low frequency motion of said control flap

What is claimed is: 1. A helicopter rotor blade comprising: a blade body; a control flap rotatably secured to said blade body; a first primary mover operable to generate a first linear motion, said first linear motion operable to generate a high amplitude, low frequency motion of said control flap to provide primary flight control; a second primary mover operable to generate a second linear motion, said second linear motion operable to generate a low amplitude, high frequency motion of said control flap to provide high harmonic control; a coupling transmission device operable to combine said first linear motion with said second linear motion to generate a cumulative linear motion; and a second transmission device to pitch said control flap relative to said blade body in response to said cumulative linear motion. 2. The helicopter rotor blade of claim 1, wherein said coupling transmission device comprises a rigid connection between said first and second primary movers. 3. The helicopter rotor blade of claim 1, wherein said first primary mover comprises an electric machine rotating a motor shaft and a first transmission device converting a rotary motion of said motor shaft into said first linear motion. 4. The helicopter rotor blade of claim 3, wherein said electric machine is a geared electric motor. 5. The helicopter rotor blade of claim 3 wherein said electric machine is secured to said blade body via a connector so that said electric machine can rotate said motor shaft about an axis of rotation in either direction. 6. The helicopter rotor blade of claim 5, wherein said first linear motion is in a direction parallel to said axis of rotation. 7. The helicopter rotor blade of claim 3, wherein said first primary mover generates a first thermal load on said electric machine. 8. The helicopter rotor blade of claim 3, wherein said first transmission device comprises a planetary roller screw mechanism or a ball screw mechanism. 9. The helicopter rotor blade of claim 3, wherein said first transmission device and said second transmission device are configured in series. 10. The helicopter rotor blade of claim 3, wherein said first transmission device and said second transmission device are configured in parallel. 11. The helicopter rotor blade of claim 1, wherein said second primary mover comprises a solid-state, induced strain stack device. 12. The helicopter rotor blade of claim 11, wherein said second primary mover generates a second thermal load on said stack device. 13. The helicopter rotor blade of claim 12, wherein said first thermal load is maintained on said first primary mover remote from said second thermal load on said second primary mover. 14. The helicopter rotor blade of claim 12, wherein said second thermal load is maintained on said second primary mover remote from said first thermal load on said first primary mover. 15. The helicopter rotor blade of claim 11, wherein said stack device comprises a device selected from the group consisting of a high strain single crystal piezoelectric stack, a magnetostrictive stack, and a TERFENOL-D stack. 16. The helicopter rotor blade of claim 1, wherein said first primary mover and said second primary mover are configured in series. 17. The helicopter rotor blade of claim 16, wherein first transmission device and said coupling transmission device are configured in series. 18. The helicopter rotor blade of claim 1, wherein said first primary mover and said second primary mover are configured in parallel. 19. The helicopter rotor blade of claim 18, wherein said first transmission device and said coupling transmission device are configured in parallel. 20. A helicopter rotor blade comprising: a blade body; a control flap rotatably secured to said blade body; a first primary mover operable to generate a first linear motion, said first primary mover includes an electric machine operable to rotate a motor shaft and a first transmission device which converts a rotary motion of said motor shaft into said first linear motion, said first linear motion operable to generate a high amplitude, low frequency motion of said control flap; a second primary mover operable to generate a second linear motion, said second linear motion operable to generate a low amplitude, high frequency motion of said control flap; a coupling transmission device for combining said first linear motion with said second linear motion to generate a cumulative linear motion, said second primary mover includes a solid-state, induced strain stack device configured as an annual cylinder so that said motor-shaft extends at least partially through said solid-state, induced strain stack device; and a second transmission device to pitch said control flap relative to said blade body in response to said cumulative linear motion. 21. A hybrid actuator comprising: an electric machine that generates a rotational motion; a first transmission device operable to convert said rotational motion into a first linear motion, said first linear motion operable to generate a high amplitude, low frequency motion; a solid-state, induced strain stack device that generates a second linear motion, said second linear motion operable to generate a low amplitude, high frequency motion; and a coupling transmission device that combines said first linear motion with said second linear motion into a cumulative linear motion; and a second transmission device to convert said cumulative linear motion to a rotational motion. 22. The hybrid actuator of claim 21, wherein said first transmission device and said coupling transmission device are configured in series. 23. The hybrid actuator of claim 21, wherein said first transmission device and said coupling transmission device are configured in parallel. 24. The hybrid actuator of claim 21, wherein said rotational motion is a pitch motion of a rotor blade control flap relative to a rotor blade body to which said rotor blade control flap is mounted.