A rotor blade assembly for providing vertical lift to an aircraft, having a rotor head and a plurality of blades, with each blade attached to a mechanism such as a cam surface, whereby movement of the mechanism causes the radial distance between the distal tip of the attached blade and the center of
A rotor blade assembly for providing vertical lift to an aircraft, having a rotor head and a plurality of blades, with each blade attached to a mechanism such as a cam surface, whereby movement of the mechanism causes the radial distance between the distal tip of the attached blade and the center of the rotor head to alter, decreasing or increasing the length of the lifting surface. The blades are moved from a fully extended position providing maximum lift, to a retracted position in which the blades are removed from the airstream. The pitch of the blades may be controlled by a pitch controller to achieve full helicopter responsiveness. A plurality of bladeletts may be positioned near the outer periphery of the rotor head. When they are moved into the airstream, passing air impacts the bladeletts exerting a pressure, causing rotational movement of the rotor blade assembly.
대표청구항▼
I claim: 1. A rotor blade assembly for providing vertical lift to an aircraft comprising: a rotor head; an operating wheel rotatable around a central point, and rotatable relative the rotor head; a plurality of blades, each blade attached to the operating wheel, each blade comprising a blade spar;
I claim: 1. A rotor blade assembly for providing vertical lift to an aircraft comprising: a rotor head; an operating wheel rotatable around a central point, and rotatable relative the rotor head; a plurality of blades, each blade attached to the operating wheel, each blade comprising a blade spar; whereby movement of the operating wheel causes the radial distance between the distal tip of the attached blade and the center of the rotor head to alter; a pitch controller having an opening, said blade spar passing through the opening in a sliding fit, the pitch controller connected to a swash plate; and a first spherical bearing interacting between the pitch controller and the pitch control rod, the pitch control rod interacting between the pitch controller and the swash plate whereby the pitch controller controls the pitch of each blade spar. 2. The rotor blade assembly of claim 1 further comprising a second spherical bearing connecting the blade spar to the operating cam, whereby the blade spar may rotate along its longitudinal axis. 3. The rotor blade assembly of claim 1 wherein the pitch controller opening has an internal shape substantially matching the external shape of the blade spar. 4. The rotor blade assembly of claim 2 wherein the internal shape of the pitch controller opening is polygonal. 5. The rotor blade assembly of claim 2 wherein the internal shape of the pitch controller opening is splined. 6. The rotor blade assembly of claim 1 further comprising a swiveling connector connecting the spar guide to the rotor head, wherein the spar guide may swivel relative to the rotor head. 7. A rotor blade assembly for providing vertical lift to an aircraft comprising: a rotor head; a plurality of cam surfaces; a plurality of blades, each blade attached to a cam surface, each blade comprising a blade spar; whereby movement of a cam surface causes the radial distance between the distal tip of the attached blade and the center of the rotor head to alter; a pitch controller having an opening, said blade spar passing through the opening in a sliding fit, the pitch controller connected to a swash plate; and a spherical bearing interacting between the pitch controller and the pitch control rod, the pitch control rod interacting between the pitch controller and the swash plate whereby the pitch controller controls the pitch of each blade spar. 8. The rotor blade assembly of claim 7 further comprising a second spherical bearing connecting the blade spar to the operating cam, whereby the blade spar may rotate along its longitudinal axis. 9. The rotor blade assembly of claim 7 further comprising: a plurality of bladeletts positioned near the outer periphery of the rotor head; the bladeletts having a retracted position wherein substantially all portions of the bladeletts are within the outer periphery of the rotor head; and a bladelett control mechanism for imparting force to the bladeletts, wherein the imparted force moves a portion of one or more bladeletts beyond the periphery of the rotor head, whereby passing air impacts the moved one or more bladeletts exerting a pressure which causes rotational movement of the rotor blade assembly. 10. The rotor blade assembly of claim 8 wherein the bladelett control mechanism further comprises: an actuator; and an actuator cable attached to the actuator and one or more bladeletts, wherein energizing the actuator pulls the actuator cable whereby the actuator cable transmits force to the one or more bladeletts. 11. A rotor blade assembly for providing vertical lift to an aircraft comprising: a rotor head; one or more blades attached to the rotor head; a piston chamber at the proximal end of said one or more blades, nearest to the center of the rotor head; a spar guide on each blade; a piston on each spar guide cooperating with the piston chamber, whereby fluid is forced into one side of the piston chamber driving the associated blade hydraulically in one direction, and whereby fluid is forced into the other side of the piston chamber driving the associated blade in the other direction; a pitch controller having an opening, said blade spar passing through the opening in a sliding fit, the pitch controller connected to a swash plate; and a spherical bearing interacting between the pitch controller and the pitch control rod, the pitch control rod interacting between the pitch controller and the swash plate whereby the pitch controller controls the pitch of each blade spar. 12. The rotor blade assembly of claim 11 further comprising a second spherical bearing connecting the blade spar to the operating cam, whereby the blade spar may rotate along its longitudinal axis.
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이 특허에 인용된 특허 (8)
C. Ed Covington ; Clifton B. Day ; Joseph J. Zierer, Anti-rotation clip.
Moffitt Robert C. ; Matuska David G. ; Fradenburgh Evan A., Rotor system having alternating length rotor blades and positioning means therefor for reducing blade-vortex interaction.
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