BACKGROUND
Helicopter rotor blades are subject to aerodynamic and inertial forces that, in turn, create vibratory (oscillatory) motions because of the non-uniform flow environment in which these aircraft are designed to operate. With reference to FIG. 1, the aerodynamic forces can cause the rotor to cone and flap as it rotates. When the rotor cones, all blades move up or down in unison. When the rotor flaps, opposing blades move in opposite directions. This coning and flapping are accommodated by the rotor hub either by bearings or by deflection of structural members. The radial location of this bearing or flexure is important because it determines the rotor hub moment used to control the helicopter and, therefore, this location is usually a design parameter that must be controlled. The component described as a “Yoke” in the present technology is designed with a flexure that provides this deflection to permit the blade to cone and to flap.
In the case of a flexure type hub, where the flapping “hinge” is due to the structural deflection of the flexure, the term “virtual hinge” is used. Typically, the location of this virtual hinge is specified by the intersection of two lines drawn tangent to the inboard and outboard slope of the deflected yoke. Dynamically, the flap moment at the hub is the same as if there was a pure hinge. The yoke of some embodiments of the present technology is tapered to give the precise moment desired at the hub for a specified amount of blade flapping.
The combination of coning and flapping creates Coriolis forces caused by the blade center-of-gravity moving radially as the rotor flaps. These loads are imposed in the chordwise direction and can be quite large at the root end of the blades and hub. In the design of the present technology these loads are reduced by the lag hinge and damper that tune the first lag mode below the rotor rotational speed (RPM or CPS). This tuning is referred to as “soft-in-plane” and is achieved by the lag hinge and damper incorporated in embodiments of the present technology.
SUMMARY
This Summary is provided to introduce a selection of concepts in a simplified form that are further described below in the Detailed Description. This Summary, and the foregoing Background, is not intended to identify key aspects or essential aspects of the claimed subject matter. Moreover, this Summary is not intended for use as an aid in determining the scope of the claimed subject matter.
The present disclosure provides an advanced technology hub for rotor aircraft.
These and other aspects of the present system and method will be apparent after consideration of the Detailed Description and Figures herein. It is to be understood, however, that the scope of the invention shall be determined by the claims as issued and not by whether given subject matter addresses any or all issues noted in the Background or includes any features or aspects recited in this Summary.
DRAWINGS
Non-limiting and non-exhaustive embodiments of the present invention, including the preferred embodiment, are described with reference to the following figures, wherein like reference numerals refer to like parts throughout the various views unless otherwise specified.
FIG. 1 depicts a schematic, elevation view of a prior art helicopter and demonstrates coning and flapping of the rotor commonly caused by aerodynamic and inertia forces on the helicopter rotor.
FIG. 2 depicts a partial, isometric view of one embodiment of a rotor mast and hub of a soft in-plane rotor of the present technology. Manual blade fold for transportation or storage is illustrated. The cross-section A-A is presented in FIG. 5.
FIG. 3 depicts a partial, exploded view of one embodiment of a rotor hub of the present technology illustrating the assembly of major comments.
FIG. 4 depicts the assembly of the joint accommodating blade pitch change and the transfer of shears between the grip and the yoke.
FIG. 5 presents the details of Section A-A referenced in FIG. 2.
FIG. 6 describes the assembly of the blade to the outboard end of the grip.
DETAILED DESCRIPTION
Embodiments are described more fully below with reference to the accompanying figures, which form a part hereof and show, by way of illustration, specific exemplary embodiments. These embodiments are disclosed in sufficient detail to enable those skilled in the art to practice the invention. However, embodiments may be implemented in many different forms and should not be construed as being limited to the embodiments set forth herein. The following detailed description is, therefore, not to be taken in a limiting sense.
With reference to FIGS. 2-6 a novel rotor hub is presented. Various embodiments of the rotor hub of the present technology may incorporate one or more of the following design characteristics:
- 1) The yoke may be made of graphite epoxy, which allows embodiments of the rotor hub design to have a tapered thickness and stiffness to achieve a precise location of the virtual flapping hinge.
- 2) A lag hinge may be incorporated at an outboard end of the grip (inboard end of the blade) that accommodates small lag motion and reduces moments due to blade inertial and aerodynamic forces.
- 3) A lag spring/damper may be incorporated that is placed along the blade radial axis providing a compact installation that also reduces drag. This arrangement also allows blade folding by disengaging the damper attachment pin and rotating the blade around the lag hinge. This reduces the space required to hanger or store the aircraft.
With reference to FIGS. 2 and 3, one embodiment of a soft in-plane rotor hub design 10 is depicted. In the depicted embodiment, a hub plate 12 attaches a yoke 14 to a mast 16 and is at least partially responsible for transmitting torque. A yoke arm 18 accommodates flapping and coning and reacts blade beam and chord shears. The yoke arm 18 does not, however, react CF. Grip 16 transmits CF from a blade 20 to a hub center section 22 and beam 24 and chord shears 26 to the yoke 14. This accommodates blade attachment and blade lead-lag and damper motion, providing a soft in-plane rotor. Pitch hinges 28 provide blade pitch change for the blade 20 with-out transmitting CF load. A tension-torsion strap 30 provides tension CF load path structure without reacting torsion or bending. A bearing/bushing 32 permits blade lag motion. An elastomeric spring damper 34 creates moments about the lag hinge 36 to optimize the natural frequency of the rotor lag mode and provides damping to help stabilize this mode.
With further reference to FIG. 2, a four-bladed rotor hub assembly 10 is mounted rigidly on the upper end of a mast 16 by means of a pair of hub clamp plates 36 and 38. In an alternate embodiment, an integral flange on the mast may also be used instead of the lower hub plate. The hub assembly 10 is characterized by a flat carbon-epoxy yoke center section 22, which is secured between the lower face of the upper clamp plate 36 and the upper face of the lower clamp plate 38. The upper hub clamp plate 36 includes a plate with an integral splined sleeve 42 that extends thru the hub assembly 10. The lower hub plate 38 is a simple flat ring that attaches to the upper plate 36 to complete the hub assembly 10. Four identical carbon-epoxy arms 44 are integral to the center section of the yoke 14 and extend outward from the center section. The hub 10 may be molded with the arms coned relative to the hub center section to reduce the steady stresses. If employed, this feature is described as “pre-cone”.
FIG. 3 depicts an exploded view of the carbon-epoxy yoke arm 44. Each yoke arm has two hinge fittings 46 fastened to the trailing edge. Each fitting has two vertical tabs 48. A tension-torsion strap 30 attaches to a steel fitting 50 to transfer centrifugal forces to the hub plates 12 and into the mast 16. The steel fitting 50 attaches to the hub plates 12 in a manner that prevents the centrifugal forces from being reacted by the carbon epoxy yoke center section. The strap 30 is soft torsionally to accommodate pitch change motion from the rotor controls. A blade grip 52 attaches to the outboard end of the tension-torsion strap 30 with a bolt 54. A pitch horn 56 attaches to the inboard end of the grip 52, or alternately, is an integral part of the grip 52. Integral internal webs 58, shown in FIG. 4, are included in each end of the grip 52. In another embodiment of this design, the tension-torsion strap 30 may be eliminated by extending the length of the grip 52 and attaching the root end of the grip 52 to a bearing attached to link 50.
Embodiments of the grip 52 attach to the yoke 14 as depicted in View A of FIG. 3, which is shown in greater detail in FIG. 4. A stainless-steel race and lined spherical bearings 60 are press fit inside the inboard and outboard internal webs 58 of the grip 52. The inside of the race 60 is lined for easy movement of the mono-ball inside the race to prevent the assembly from reacting a moment in any direction. The mono-ball spherical is lined on the inside IML, to provide a low friction surface for the bearing to slide on the sleeved shoulder bushing 62. This assembly provides for rotation of the bearing to accommodate blade pitch change while providing a load path for blade vertical and inplane shears to be transmitted to the grip 52. The grip 52 is then attached to the vertical arms 48 of the hinge fittings 46 with a sleeved shoulder bushing 62. The length of the shoulder bushing 62 is carefully controlled so that the vertical arms on the hinge fittings 46 are not subjected to bending stresses and to accommodate small axial motions to prevent centrifugal forces from being transmitted to the yoke 14. The Section A-A view of FIG. 5 also illustrates these details. The hinge fittings are attached to the yoke to complete the hub assembly.
The outboard end of the grip 52, shown in FIG. 6, has two in-line holes 64 and provisions for securing the blade 20, attaching a lag spring and damper, and accommodating blade fold. The larger hole on the inboard side of the grip accommodates an elastomeric bushing 66. The blade 20 has a mating hole on the root end and a bolt 68 attaches the blade 20 to the grip 52. The grip bearing is the primary load path for transferring centrifugal forces from the blade 20 to the grip 52. The bearing also acts as a lag hinge, providing flexibility for the blade lead and lag motion and tuning the first blade mode natural frequency below 1/rev which is characteristic of the descriptor “soft-in-plane”.
The smaller hole on the outboard end of the grip 52 is oversized to permit the blade lead-lag motion and to act as a stop when contacted by the bolt 70 which attaches the damper 72 to the blade 20 and passes thru the grip 52. The damper 72 also contains an elastomer that provides both a damping and spring force around the lag bushing. The damping force contributes to the damping required to lag mode. The outboard bolt 70 is also designed as an alternate load path for centrifugal force in the event the inboard bolt fails. Manual blade fold, illustrated in FIG. 2, is accommodated by disconnecting bolt 70 and rotating the blade 20 about the inboard bushing.
Although the technology has been described in language that is specific to certain structures, materials, and methodological steps, it is to be understood that the invention defined in the appended claims is not necessarily limited to the specific structures, materials, and/or steps described. Rather, the specific aspects and steps are described as forms of implementing the claimed invention. Since many embodiments of the invention can be practiced without departing from the spirit and scope of the invention, the invention resides in the claims hereinafter appended. Unless otherwise indicated, all numbers or expressions, such as those expressing dimensions, physical characteristics, etc. used in the specification (other than the claims) are understood as modified in all instances by the term “approximately.” At the very least, and not as an attempt to limit the application of the doctrine of equivalents to the claims, each numerical parameter recited in the specification or claims which is modified by the term “approximately” should at least be construed in light of the number of recited significant digits and by applying ordinary rounding techniques. Moreover, all ranges disclosed herein are to be understood to encompass and provide support for claims that recite any and all subranges or any and all individual values subsumed therein. For example, a stated range of 1 to 10 should be considered to include and provide support for claims that recite any and all subranges or individual values that are between and/or inclusive of the minimum value of 1 and the maximum value of 10; that is, all subranges beginning with a minimum value of 1 or more and ending with a maximum value of 10 or less (e.g., 5.5 to 10, 2.34 to 3.56, and so forth) or any values from 1 to 10 (e.g., 3, 5.8, 9.9994, and so forth).
Patent Application
20190344884
