Spinner fairing assembly

An apparatus comprising a spinner fairing assembly comprising a spinner configured to be fixed relative to a gimbaled yoke coupled to a mast system, and a spinner base configured to be fixed relative to the mast system. A spinner fairing assembly comprising a spinner aligned along a first axis, and a spinner base aligned along a second axis and configured to interface with the spinner, wherein the spinner is configured to transition between a neutral position and a canted position with respect to the spinner base, wherein the first axis and the second axis are coincident in the neutral position, and wherein the first axis and the second axis are not coincident and meet at an origin within the spinner in the canted position.

CROSS-REFERENCE TO RELATED APPLICATIONS

Not applicable.

Not applicable.

REFERENCE TO A MICROFICHE APPENDIX

Not applicable.

BACKGROUND

Spinner fairings may be employed to reduce the overall aerodynamic drag of an aircraft. Conventional spinner fairings used with rotor system (e.g., a tilt rotor system) may be in a fixed orientation with respect to a mast or nacelle. In such examples, the spinner fairing may require large fairing cutouts with sufficient clearance for fairing hardware connections (e.g., bolt linkages) and proper range of motion for during operation (e.g., flapping, feathering, coning, etc.). Large cutouts or voids in the exterior of the spinner fairing may degrade the performance and/or the ability to reduce aerodynamic drag by the spinner fairing. In an embodiment, it may be desirable to further improve the aerodynamic properties (e.g., further reduce the overall aerodynamic drag) of a spinner fairing to improve the overall performance of an aircraft system.

SUMMARY

In one aspect, the disclosure includes an apparatus comprising a spinner fairing assembly comprising a spinner configured to be fixed relative to a gimbaled yoke coupled to a mast system, and a spinner base configured to be fixed relative to the mast system.

In another aspect, the disclosure includes a spinner fairing assembly comprising a spinner aligned along a first axis, and a spinner base aligned along a second axis and configured to interface with the spinner, wherein the spinner is configured to transition between a neutral position and a canted position with respect to the spinner base, wherein the first axis and the second axis are coincident in the neutral position, and wherein the first axis and the second axis are not coincident and meet at an origin within the spinner in the canted position.

In yet another aspect, the disclosure includes a method comprising providing a spinner fairing assembly comprising a spinner aligned along a first axis, and a spinner base aligned along a second axis and configured to interface with the spinner, wherein the spinner is configured to transition between a neutral position and a canted position with respect to the spinner base, wherein the first axis and the second axis are coincident in the neutral position, and wherein the first axis and the second axis are not coincident and meet at an origin within the spinner in the canted position.

DETAILED DESCRIPTION

Disclosed herein are embodiments of a spinner fairing assembly (SFA), a rotor system comprising a SFA, and methods of using the same. In an embodiment, the SFA may be employed to improve the aerodynamic performance (e.g., reduce aerodynamic drag) while maintaining normal operation functionality (e.g., during flapping, feathering, coning, etc.), as will be disclosed herein.

In an embodiment, a SFA may be incorporated and/or integrated with a rotor aircraft (e.g., a tilt rotor aircraft, a helicopter, etc.) having one or more rotor systems (e.g., a main rotor, a tail rotor, etc.). As such, a SFA may be employed to provide an aerodynamic surface during operation. For example, the SFA may provide an aerodynamic surface in one or more directions, for example, in two directions (e.g., a longitudinal direction and a horizontal direction) for a tilt rotor aircraft. Referring toFIG. 1, a tilt rotor aircraft50is illustrated. In an embodiment, a tilt rotor aircraft50may generally comprise a fuselage52, a wing member54, and a tail member56, and a plurality of engines58a,58b. While described as a single wing member54, it is understood that the wing member54may be formed from separate components such that two or more wing members54are coupled to fuselage52(e.g., each side of the fuselage52may comprise a separate wing member54). The aircraft50may also include a first rotor system60aand a second rotor system60b. The first rotor system60ais located on an end portion of a first side of the wing member54, while the second rotor system60bis located on a second side of the wing member54. The first rotor system60aand the second rotor system60bmay be substantially symmetric of each other about the fuselage52.

Referring toFIG. 2-4, an embodiment of a rotor system60is illustrated. As shown in the embodiments ofFIGS. 3 and 4, the rotor system60may generally comprise a SFA100, a gimbaled yoke150, and a plurality of fairings120. In an embodiment, the gimbaled yoke150may be generally configured to couple a main support mast (not shown but generally extending along an axis400) to a plurality of blades (not shown) via the fairings120. The gimbaled yoke150may include any other suitable rotor system components as would be appreciated by one of ordinary skill upon viewing this disclosure. In an embodiment, the gimbaled yoke150may allow the blades to rotate about the mast (e.g., to provide lift), to change pitch while rotating either collectively or cyclically (e.g., to accommodate vertical loads or to maneuver), perhaps to pivot within the gimbaled yoke150plane that contains the fairings120(e.g., to provide lead-lag control), and/or any other articulation or movement as would be appreciated by one of ordinary skill in the art upon viewing this disclosure. As such, the gimbaled yoke150is configured to pivot the gimbaled yoke150plane relative to the axis400.

In an embodiment, the gimbaled yoke150may be formed of a metal, a plastic, a composite material (e.g. carbon fiber or fiberglass), combinations thereof, or any other suitable material as would be appreciated by one of ordinary skill in the art upon viewing this disclosure. Additionally, in an embodiment, the gimbaled yoke150may be configured to support any suitable number of blades and/or fairings120, for example, 2, 3, 4, 5, 6, 7, 8, 9, 10, etc.

In an embodiment, the SFA100may be generally configured to cover and/or shield the gimbaled yoke150, for example, to prevent or reduce damage to the gimbaled yoke150from environmental conditions (e.g., rain, water, snow, sand, debris, etc.) and to provide improved aerodynamic performance during operation. In an embodiment, the SFA100may be configurable between a neutral configuration and a canted configuration, as will be disclosed herein.

In an embodiment, the SFA100may generally comprise a spinner102, a spinner base106, and a plurality of fairing ports104. The spinner102and/or the spinner base106may be formed of a metal, a plastic, a glass fiber, a carbon fiber, other composite materials, any other rigid or semi-rigid material as would be appreciated by one of ordinary skill in the art upon viewing this disclosure, or combination thereof.

In an embodiment, the spinner102may be generally rounded (e.g., parabolic, conical, spherical, parabolic, egg shaped, bullet shaped, bell shaped, etc.), axially symmetrical (e.g., about the axis400), and hollow. The spinner102may comprise a lower surface110and the plurality of fairing ports104, as will be disclosed herein. In an embodiment, the spinner102is a section of a sphere centered on an origin (e.g. a center of the tilting/canting movement) for the gimbaled yoke150. Additionally, the spinner102may be coupled to the gimbaled yoke150and/or a rotor assembly such that the spinner102is in a fixed position relative to the gimbaled yoke150and/or rotor assembly. For example, in the embodiments ofFIGS. 3-4, an interior surface103of the spinner102may be coupled to the gimbaled yoke150via one or more mounting brackets112, the one or more mounting bracket comprises two arms connected above the gimbaled yoke and extending out to a circumferential attachment section which conforms to the inner surface of the spinner fairing. In such an embodiment, the spinner102may be configured to move with the gimbaled yoke150, as will be disclosed herein.

In an embodiment, the spinner base106may be positioned proximate and/or adjacent to the lower surface110of the spinner102. The spinner base106may generally be cylindrical and comprises an upper surface108and a lower surface107. In an embodiment, the upper surface108is a section of a sphere centered on an origin within the gimbaled yoke150. In an embodiment, the spinner base106may comprise and/or be formed with a nacelle or upper pylon, for example, a fuselage or nacelle of an aircraft. In such a case, the mast rotates with the spinner base106. In an alternative embodiment, the spinner base106may be coupled to the mast system via the lower surface107. In such a case, the spinner base106rotates with the mast. As used herein, the term “fixed relative to” generally refers to a lack of translation movement while allowing rotating movement and is intended to cover both of these embodiments, namely the embodiment where one part of the SFA100does not move laterally but allows rotation relative to the named object, and the embodiment where one part of the SFA100is affixed to the named object such that there is no lateral movement or rotation. In an embodiment, the space or interface between the lower surface110and the upper surface108may be small (e.g., about 0.025 inches, about 0.01 inches, about 0.05 inches, etc.) and may comprise air, oil, grease, or any suitable material there between.

In an embodiment, the spinner102may be positionable with respect to the spinner base106. For example, when the spinner102is coupled to the gimbaled yoke150, the spinner102may be configured to be positioned and/or repositioned with respect to the spinner base106in response to the canting of the gimbaled yoke150. In the embodiments ofFIGS. 3 and 5, the spinner102is configured in a neutral or “centered” position with respect to the spinner base106. In such an embodiment, the spinner102and the spinner base106may be coaxially centered and/or aligned along the axis400. Additionally, when the spinner102is in the neutral position, the SFA100may be configured in the neutral configuration.

In the embodiments ofFIGS. 4 and 6, the spinner102is configured in a canted or “tilted” position with respect to the spinner base106. In such an embodiment, the spinner base106may be centered and/or aligned along the axis400and the spinner102may be centered and/or aligned along a second axis402, which is normal to the gimbaled yoke150plane. In such an embodiment, the axis400and the second axis402may not be substantially coincident, but meet at the gimbal origin. In an embodiment, the spinner102may be tilted at an angle with respect to the spinner base106. For example, the spinner102may be tilted with respect to the spinner base106by an angle of about 0.1 degrees, about 0.5 degrees, about 1 degree, about 5 degrees, about 10 degrees, or any other suitable angle as would be appreciated by one of skill in the art upon viewing this disclosure. Additionally, when the spinner102is in the canted position, the SFA100may be configured in the canted configuration.

In an embodiment, when the spinner102is in the neutral position or canted position with respect to the spinner base106, the spinner102and/or the spinner base106may be configured to disallow or substantially disallow exposure between the interior of the SFA100and the exterior of the SFA100, thereby protecting and/or shielding the interior of the SFA100(e.g., the gimbaled yoke150) from environmental conditions (e.g., rain, water, snow, sand, debris, etc.). Additionally, when the spinner102is in the neutral position or canted position with respect to the spinner base106, the spinner102and/or the spinner base106may be configured to provide improved aerodynamic performance during operation, for example, via providing a more aerodynamic surface and reducing aerodynamic drag. For example, in the embodiment ofFIGS. 2-4, the lower surface110of the spinner102may form a rounded lower surface and the upper surface108of the spinner base106may form a concave surface. In such an embodiment, the lower surface110of the spinner102may be configured to slidably engage the upper surface of the spinner base106. For example, the lower surface110may slide along the upper surface108as the spinner102is positioned with respect to the spinner base106(e.g., transitioning from the neutral position to the canted position with respect to the second portion of the spinner base106). Additionally, in such an embodiment, when the spinner102is in the canted position with respect to the spinner base106, the lower surface110may be engaged (e.g., overlap) with the upper surface108such that the spinner102and/or the spinner base106are configured to disallow or substantially disallow exposure between the interior of the SFA100and the exterior of the SFA100and provide a more aerodynamic surface. Further, the spinner base106has a diameter less than the diameter of the spinner102, and thus does not collect or capture passing air (e.g., does not form a “scoop”) when the spinner102is canted (e.g., canted to a maximal angle) with respect to the spinner base106.

In an alternative embodiment, for example as illustrated inFIGS. 5 and 6, the spinner102is parabolic shaped and the spinner base106is shaped as a truncated cone. The lower surface110of the spinner102may have a diameter greater than the upper surface108of the spinner base106. For example, the spinner102may be overcut with respect to the spinner base106as shown inFIGS. 5 and 6. In such an embodiment, the spinner102may at least partially cover (e.g., overlap) a portion (e.g., the upper surface108) of the spinner base106. Additionally, in such an embodiment, when the spinner102is in the canted position with respect to the spinner base106, the lower surface110may overlap the upper surface108such that the spinner102and/or the spinner base106are configured to provide a substantially continuous surface. Similar to the embodiment inFIGS. 2-4, no portion of the spinner base106extends past the spinner102, which provides a smooth surface for passing air and a more aerodynamic surface.

In an embodiment, the plurality of fairing ports104may be disposed radially about the spinner102(e.g., about the axis400). In an embodiment, each of the fairing ports104may be suitably sized to allow a fairing120to extend there through and for articulated movements of the fairing120(e.g., coning, feathering, flapping, etc.). In such an embodiment, the plurality of fairing ports104may be configured to provide a minimal surface void area within the spinner102. For example, in the embodiment ofFIG. 7, in a conventional spinner fairing housing202which is fixed with respect to a mast or nacelle, the conventional spinner fairing housing202may comprise fairing ports204sized to provide suitable clearances and tolerances for the movements of a fairing. In the embodiment ofFIG. 8, the spinner102is fixed and moves with the rotor assembly, thus the fairing ports104do not need to be sized to allow the fairings to move relative to the spinner. As such, the fairing port104of the spinner102may have an opening or void area substantially less than a conventional spinner fairing port (e.g., the fairing port204as shown inFIG. 7). In an embodiment, the fairing port104may comprise an opening or void area reduction of about 25%, 30%, 35%, 40%, 45%, 50%, 60%, or about any other suitable reduction percentage as would be appreciated by one of ordinary skill in the art upon viewing this disclosure, when compared to a conventional spinner fairing port. Additionally, in an embodiment, the spinner102may comprise any suitable number of fairing ports104, for example, 2, 3, 4, 5, 6, 7, 8, 9, 10, etc.

In an embodiment, a spinner fairing positioning method utilizing a SFA and/or a system comprising a SFA is disclosed herein. In an embodiment, as illustrated inFIG. 9, a spinner fairing position method800may generally comprise the steps of providing a rotor system comprising a SFA802, configuring the SFA804, and operating a rotor system comprising the SFA806.

In an embodiment, when providing a rotor system comprising a SFA802, a rotor system, such as a rotor system60, comprising a SFA, such as SFA100, may be provided. For example, a rotor system60comprising a SFA100may be designed similar to that described herein, manufactured, and incorporated and/or integrated with an aircraft (e.g., a helicopter, a tilt rotor, etc.).

In an embodiment, configuring the spinner fairing assembly804may comprise positioning the spinner102of the SFA100with respect to the spinner base106of the SFA100, for example, in response to positioning the gimbaled yoke150(e.g., in preparation to perform one or more movements and/or operations). For example, the spinner102may be positioned in the first or centered position with respect to the spinner base106. Alternatively, the spinner102may be positioned in the second or tilted position with respect to the spinner base106.

When operating a rotor system comprising the SFA806, the rotor system60may perform one or more articulated movements (e.g., flapping, feathering, coning, etc.) and/or operations (e.g., rotating). In an embodiment, the gimbaled yoke150of the rotor system60may rotate about a mast or axis (e.g., axis400). In such an embodiment, the spinner102of the SFA100is in a fixed position (e.g., coupled) with respect to the gimbaled yoke150and may rotate about the mast or axis. Additionally, in such an embodiment, the gimbaled yoke150may perform one or more articulated movements (e.g., flapping, feathering, coning, etc.) of one or more fairings120.

In an embodiment, the process of configuring the SFA804and operating the rotor system comprising the SFA806may be repeated. For example, in a manner similar to that disclosed herein, the SFA100may be configured and/or reconfigured as needed during operation.

In an embodiment, a spinner fairing assembly, such as SFA100, a rotor system comprising a SFA100, such as the rotor system60, a method of employing such a rotor system60and/or such a SFA100, or combinations thereof may be advantageously employed to improve the aerodynamic performance (e.g., reduce aerodynamic drag) while maintaining normal operation functionality (e.g., during flapping, feathering, coning, etc.). In an embodiment, as previously disclosed, a SFA allows rotor system comprising a plurality of fairings or blades to perform articulated movements (e.g., flapping, feathering, coning, etc.) while reducing the size of ports or cut-outs required to allow for such articulated movements. As such, a SFA may be employed to provide improved aerodynamic performance during operation, for example, via providing a more aerodynamic surface and reducing aerodynamic drag.