Embodiments of a bi-axial compliant bearing assembly and methods of assembling the bi-axial compliant bearing assembly are disclosed. A bi-axial compliant bearing assembly employs a transition bearing race. The transition bearing race comprises a cylindrical surface. The cylindrical surface is confi
Embodiments of a bi-axial compliant bearing assembly and methods of assembling the bi-axial compliant bearing assembly are disclosed. A bi-axial compliant bearing assembly employs a transition bearing race. The transition bearing race comprises a cylindrical surface. The cylindrical surface is configured to rotatably engage a rotational bearing element and to slidably engage the rotational bearing element along an axis. The transition bearing race also includes a spherically-compliant surface. The spherically-compliant surface is configured to engage a spherically-compliant element and to enable the spherically-compliant element to rotate transversely to the axis.
대표청구항▼
1. A transition bearing race, comprising: a cylindrical surface configured to rotatably engage a rotational bearing element and to slidably engage the rotational bearing element along a first axis; anda spherically-compliant surface including at least a section of a spherical surface and at least on
1. A transition bearing race, comprising: a cylindrical surface configured to rotatably engage a rotational bearing element and to slidably engage the rotational bearing element along a first axis; anda spherically-compliant surface including at least a section of a spherical surface and at least one loading slot, the spherically-compliant surface configured to engage a spherically-compliant element, wherein the at least one loading slot is configured to facilitate engagement of the spherically-compliant element with the spherically-compliant surface, and the spherically-compliant element, when engaged with the spherically-compliant surface, is enabled to: change an angle of intersection between a second axis of the spherically-compliant element and the first axis; androtate around the first axis. 2. The transition bearing race of claim 1, wherein: the cylindrical surface includes an outward-facing cylindrical surface configured to receive an inward-facing cylindrical surface of the rotational bearing element; andthe spherically-compliant surface includes an inward-facing spherically-compliant surface configured to engage an outward-facing spherically-compliant surface of the spherically-compliant element. 3. The transition bearing race of claim 2, further comprising a pair of loading slots formed within opposing sides of the inward-facing spherically-compliant surface at a first end of the inward-facing spherically-compliant surface, wherein the pair of loading slots enables the spherically-compliant element to be slidably received within the inward-facing spherically-compliant surface. 4. The transition bearing race of claim 2, further comprising a loading ramp at a first end of the outward-facing cylindrical surface, wherein the loading ramp facilitates the inward-facing cylindrical surface of the rotational bearing element being slidably received over the outward-facing cylindrical surface. 5. The transition bearing race of claim 1, wherein: the cylindrical surface includes an inward-facing cylindrical surface configured to receive an outward-facing cylindrical surface of the rotational bearing element; andthe spherically-compliant surface includes an outward-facing spherically-compliant surface configured to engage an inward-facing spherically-compliant surface of the spherically-compliant element. 6. A system, comprising: a transition bearing race, comprising: an outward-facing cylindrical surface disposed about an axis; andan inward-facing spherically-compliant surface including at least one loading slot;a rotational bearing element including an inward-facing cylindrical surface configured to rotatably and slidably engage the outward-facing cylindrical surface along the axis; anda spherically-compliant element having an outward-facing spherically-compliant surface configured to rotatably engage the inward-facing spherically-compliant surface to enable the spherically-compliant element to rotate transversely to the axis, the at least one loading slot to enable the spherically-compliant element to be slidably received by the inward-facing spherically-compliant surface. 7. The system of claim 6, further comprising a pair of loading slots formed within opposing sides of the inward-facing spherically-compliant surface and at a first end of the inward-facing spherically-compliant surface, wherein the pair of loading slots enables the spherically-compliant element to be slidably received by the inward-facing spherically-compliant surface. 8. The system of claim 7, wherein each of the pair of loading slots has a loading slot width and the spherically-compliant element has an element width, such that the element width of the spherically-compliant element is less than the loading slot width of each of the pair of loading slots. 9. The system of claim 8, wherein the spherically-compliant element includes a plurality of mounting holes configured to enable the spherically-compliant element to be coupled to a first body after the spherically-compliant element has been received by the inward-facing spherically-compliant surface. 10. The system of claim 9, wherein the first body includes a spindle arm of a helicopter rotor hub assembly. 11. The system of claim 10, wherein the spherically-compliant element enables spherical compliance of the transition bearing race with respect to the spindle arm of the helicopter rotor hub assembly. 12. The system of claim 6, further comprising a loading ramp at a first end of the outward-facing cylindrical surface, wherein the loading ramp facilitates the inward-facing cylindrical surface of the rotational bearing element being slidably received over the outward-facing cylindrical surface. 13. The system of claim 6, wherein the rotational bearing element includes a plurality of rotatable bearings disposed on the inward-facing cylindrical surface, wherein each of the plurality of rotatable bearings has a rotation axis substantially coplanar with the axis and wherein the plurality of rotatable bearings is configured to enable the inward-facing cylindrical surface of the rotational bearing element to rotatably engage the outward-facing cylindrical surface. 14. The system of claim 13, wherein the plurality of rotatable bearings include one or more of needle bearings, tapered roller bearings, and ball bearings. 15. The system of claim 13, further comprising one or more lubricant seals disposed on opposing sides of the rotational bearing element to contain a lubricant disposed between the inward-facing cylindrical surface of the rotational bearing element and the outward-facing cylindrical surface. 16. The system of claim 13, wherein the rotational bearing element is coupled to a helicopter rotor blade, wherein the rotational bearing element rotating around the axis enables rotation of the helicopter rotor blade to enable pitch adjustment of the helicopter rotor blade. 17. The system of claim 16, wherein the inward-facing cylindrical surface of the rotational bearing element slidably engages the outward-facing cylindrical surface to enable axial compliance of the helicopter rotor blade with respect to the transition bearing race. 18. A helicopter rotor hub assembly, comprising: a plurality of spindle arms, each of the plurality of spindle arms extending radially from a rotor hub; anda plurality of bi-axial compliant bearing assemblies, each of the plurality of bi-axial compliant bearing assemblies comprising: a transition bearing race including an outward-facing cylindrical surface and an inward-facing spherically-compliant surface;a rotational bearing element including an inward-facing cylindrical surface configured to rotatably and slidably engage the outward-facing cylindrical surface of the transition bearing race and an outer surface configured to engage a helicopter rotor blade; anda spherically-compliant element including an outward-facing spherically-compliant surface configured to rotatably engage the inward-facing spherically-compliant surface and a spindle coupling configured to be coupled to one of the plurality of spindle arms. 19. The helicopter rotor hub assembly of claim 18, wherein each of the plurality of spindle arms supports both an inboard bi-axial compliant bearing assembly and an outboard bi-axial compliant bearing assembly. 20. The helicopter rotor hub assembly of claim 19, wherein the helicopter rotor blade engages the rotational bearing element of each of the inboard bi-axial compliant bearing assembly and the outboard bi-axial compliant bearing assembly. 21. A method, comprising: providing a transition bearing race, comprising: an outward-facing cylindrical surface disposed about an axis; andan inward-facing spherically-compliant surface including at least one loading slot;providing a rotational bearing element having an inward-facing cylindrical surface configured to rotatably and slidably engage the outward-facing cylindrical surface;providing a spherically-compliant element having an outward-facing spherically-compliant surface configured to rotatably engage the inward-facing spherically-compliant surface;coupling the rotational bearing element to a first body;disposing the inward-facing spherically-compliant surface adjacent to a second body;inserting the spherically-compliant element into the inward-facing spherically-compliant surface, the at least one loading slot configured to facilitate inserting the spherically-compliant element into the inward-facing spherically-compliant surface;coupling the spherically-compliant element to the second body; andpositioning the first body to dispose the rotational bearing element over the outward-facing cylindrical surface of the transition bearing race. 22. The method of claim 21, wherein the inward-facing spherically-compliant surface includes a pair of loading slots configured to receive an edge of the spherically-compliant element, wherein the pair of loading slots is configured to facilitate inserting the spherically-compliant element into the inward-facing spherically-compliant surface. 23. The method of claim 22, further comprising rotating the spherically-compliant element such that its edge is receivable into the pair of loading slots. 24. The method of claim 21, wherein the outward-facing cylindrical surface of the transition bearing race includes a loading ramp at an end of the outward-facing cylindrical surface, wherein the loading ramp is configured to receive the inward-facing cylindrical surface of the rotational bearing element and guide the rotational beating element over the outward-facing cylindrical surface of the transition bearing race. 25. A bi-axial compliant bearing assembly for coupling a helicopter rotor blade to a helicopter rotor hub assembly, comprising: a transition bearing race, comprising: an outward-facing cylindrical surface disposed about an axis;a loading ramp abutting an edge of the outward-facing cylindrical surface, the loading ramp configured to guide an inward-facing cylindrical surface into place over the outward-facing cylindrical surface; andan inward-facing spherically-compliant surface including a pair of loading slots configured to receive an outward-facing spherically-compliant surface when the outward-facing spherically compliant surface is rotated and presented edgewise into the pair of loading slots;a rotational bearing element, comprising: an outer surface configured to engage a helicopter rotor blade;the inward-facing cylindrical surface configured to rotatably engage the outward-facing cylindrical surface about the axis and to slidably engage the outward-facing cylindrical surface along the axis; anda plurality of individual bearings supported by the inward-facing cylindrical surface, the plurality of individual bearings configured to enable the rotational bearing element to rotatably engage the outward-facing cylindrical surface; anda spherically-compliant element, comprising: the outward-facing spherically-compliant surface configured to rotatably engage the inward-facing spherically-compliant surface to enable the spherically-compliant element to rotate transversely to the axis; anda plurality of mounting tabs configured to engage a spindle arm of a helicopter rotor hub assembly. 26. The transition bearing race of claim 1, wherein the at least the section of the spherical surface has a cross-section along the first axis that has a curved profile. 27. The transition bearing race of claim 26, wherein a first circumference at a first point of the curved profile is a different size than a second circumference at a second point of the curved profile.
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이 특허에 인용된 특허 (13)
Desjardins Rene A. (Newtown Square PA), Compensation for kinematic foreshortening effect in pitch control system for rotary wing aircraft.
Dunham James L. (216 Redwood Ave. Willits CA 95490) Cutter Catherine C. (216 Redwood Ave. Willits CA 95490), Compliant bearing surface with enclosed fluid support.
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