CN106965927A - Rotor blade coupling arrangement for the rotor head of gyroplane - Google Patents
Rotor blade coupling arrangement for the rotor head of gyroplane Download PDFInfo
- Publication number
- CN106965927A CN106965927A CN201610998393.9A CN201610998393A CN106965927A CN 106965927 A CN106965927 A CN 106965927A CN 201610998393 A CN201610998393 A CN 201610998393A CN 106965927 A CN106965927 A CN 106965927A
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- China
- Prior art keywords
- rotor blade
- rotor
- coupling arrangement
- installed part
- damping unit
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/51—Damping of blade movements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/001—Vibration damping devices
- B64C2027/003—Vibration damping devices mounted on rotor hub, e.g. a rotary force generator
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Vibration Prevention Devices (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
A kind of rotor blade coupling arrangement for being used to be connected to mast includes：Rotor head central part；At least three rotor blade installed parts, on rotor head central part and for accommodating at least three rotor blades being located in rotor plane；And at least one attachment means, between adjacent rotor blade installed part, wherein rotor blade installed part can be pivoted motion rotating around the pivot axis extended perpendicular to rotor plane, wherein at least one attachment means are realized in the form of damping unit, and wherein rotor blade coupling arrangement includes the plate shape transmitting element for being connected at least one damping unit with rotor blade installed part alter-parallel respectively, the purpose of the present invention is to obtain with simple designs and ensure the rotor blade coupling arrangement of improved lead-lag motion damping.A part for this tabular transmitting element for being embodied as with rotor blade installed part intersecting respectively two adjacent damping unit of formation, so as to directly and be functionally connected to two adjacent damping units.
Description
Technical field
The present invention describes the rotor blade connection of the rotor head of the gyroplane for such as direct lift or helicopter
Connection device.
According to the present invention rotor blade coupling arrangement especially handle rotor blade rotate during occur flap and
Move pivotally.
Rotor blade coupling arrangement generally includes the rotational engagement part extended perpendicular to rotor plane, the wherein rotational engagement
The resistance that part produces the angular adjustment between rotor blade to the lift of single rotor blade installed part and each auto correlation is can
Regulation.According to the position of each rotor blade, the pivoted motion in rotor plane.The pivoting action is respectively directed to
Rear, i.e., (" delayed (lag) ") opposite with the direction of rotation of rotor blade, or be directing forwardly, i.e., along the rotation of rotor blade
Direction (" advanced (lead) ").Angular adjustment resistance can generally be adjusted by means of hydraulic dampening element, hydraulic dampening element point
These so-called lead-lag motions are not slowed down or suppress.Hydraulic dampening element is especially multiple in terms of its installation, examination and maintenance
It is miscellaneous.This lead-lag motion is mainly caused by Coriolis (Coriolis) power and aerodynamic drag, and wherein these are advanced-stagnant
Move afterwards is also influenceed by centrifugal force and inertia force.
Background technology
The known rotor blade coupling arrangement for example from US2008/0159862A1, plurality of damping element is (in rotation
It is elastic on the direction of rotation of rotor blade) connecting element between the adjacent rotor blade of two difference is set to, and
Suppress lead-lag motion.
Lead to from this damping element known to US2008/0159862A1 between the adjacent rotor blade of two difference
Often it is also referred to as damper " between blade ".In US2008/0159862A1 it is known the adjacent rotor blade of two difference it
Between there is damping element rotor blade coupling arrangement there is complicated design.For example, in single damping element and rotor leaf
The additional arrangement of two respective fasteners and connecting bracket is needed in transitional region between piece installed part, wherein these are added
The maintenance workload of part is especially big.Furthermore, it may be determined that, such two engage with blade pitch axis is separated
Part can produce negative dynamic effect (negative dynamic effect).
Other rotor blade coupling arrangements well known in the prior art are described below, it is characterised in that rotor blade installed part
Intersection region in connecting element and for suppress lead-lag motion damping unit.
US2010/0215496A1 discloses a kind of rotor blade coupling arrangement, and it, which has, is similar to from US2008/
The design of rotor blade coupling arrangement known to 0159862A1.
Include being arranged in from rotor blade coupling arrangement known to US2010/0215496A1 and handed over rotor blade installed part
Damping unit in the region of fork, the wherein damping unit include elastomer member.Bullet of the damping based on elastomer member
Property reverse.The rod being especially made up of rigid material is disposed between damping unit as the connecting element between rotor blade.
From rotor blade coupling arrangement known to US2010/0215496A1 its installation and maintenance in terms of be complicated.
US4915585 discloses another rotor blade coupling arrangement, and it, which has, is respectively disposed at rotor blade installation
Multiple rotor blades on part and the damping unit for suppressing lead-lag motion.US4915585 is also disclosed adjacent
The damping unit of the form of fastening means or so-called " between blade " damper between rotor blade installed part.According to preferred change
Type, known rotor blade coupling arrangement also includes the V-arrangement rigidity intersected respectively with rotor blade installed part from US4915585
One lever arm of the lever element of design, wherein lever element is hingedly connected to damping element, and another lever arm is firm
It is connected to damping unit to property.
The content of the invention
The present invention is based on a kind of purpose of rotor blade coupling arrangement is realized, the rotor blade coupling arrangement includes minimum
The fastener (joint) of amount, has simplified design compared with from rotor blade coupling arrangement known in the art, and really
Protecting lead-lag motion has improved damping.
These purposes realize that the rotor blade coupling arrangement is used to couple by the rotor blade coupling arrangement of the present invention
To mast with formed for gyroplane, particularly direct lift or helicopter rotor head, and including：- rotor
Head central part ,-at least three rotor blade installed parts, it is arranged on the rotor head central part and is located at rotation for accommodating
At least three rotor blades in wing plane, and-at least one attachment means, the adjacent rotor blade installed part it
Between, wherein, the rotor blade installed part can surround the pivot axis extended perpendicular to the rotor plane respectively and carry out pivot
Transhipment is dynamic, wherein, at least one described attachment means are realized in the form of damping unit, and, wherein, the rotor blade connection
Connection device include plate shape transmitting element, the plate shape transmitting element be connected to respectively with the rotor blade installed part alter-parallel to
A few damping unit, it is characterised in that the transmitting element intersected respectively with the rotor blade installed part is formed
A part for two adjacent damping units, so as to directly and be functionally connected to described two adjacent damping units.
According to the present invention, intersect the plate shape transmitting element formation two of (cross intersects) with rotor blade installed part respectively
A part for adjacent damping unit, and directly and it is functionally connected to two adjacent damping units.
The combination of the plate shape transmitting element and damping unit of all intersections formed respectively separated ring (divided ring) or
Ring arranges (ring arrangement, loop device).In the state of the rotor blade coupling arrangement of the present invention, wherein separately ring
Rotor head is connected to, this separates ring and does not produce directly machinery and rigidity between separated ring and mast (rotor mast)
Feature connection so that separate ring and installed in some sense in complete universal (cardanic) mode.Passed by intersection plate shape
Circular or polygon, particularly pentagon can be substantially implemented as by passing the ring arrangement of the overall composition of element and damping unit.
In other words, the respective ring or ring arrangement expression of separating of rotor blade coupling arrangement of the invention has flexible portion
Ring arrangement, wherein flexible portion is formed by damping unit.
Advantageously it is well established that being realized using this ring arrangement of the rotor blade coupling arrangement of the present invention on being related to
The special acoustic damping of so-called " Regression Model (the regressive mode) " of ground resonance.
In addition, can unexpectedly determine, the lead-lag damping system phase with known rotor blade coupling arrangement
Than the ring arrangement of rotor blade coupling arrangement of the invention is reduced to be occurred on damping unit during rotor blade rotates
Collection neutralizes motion of periodically flapping.In this application, it is also advantageous in this regard that this motion of flapping is with the rotor blade of the present invention
Inhibit sizable degree to coupling arrangement air force so that in the damping unit of the rotor blade coupling arrangement of the present invention
Part on the extra and undesirable load service life of part that is reduced and therefore extends damping unit.
According to preferred improvement, the plate shape transmitting element intersected with rotor blade installed part is implemented as with two arms
Angular or segmentation shape, two respective arms of the adjacent transmitting element of two of which by band type damper form damping
Device is connected to each other directly.Pass through the corresponding selection of the material and/or geometry (particularly thickness) of transmitting element, Ke Yishi
The sufficiently rigid design of the transmitting element now intersected with rotor blade installed part.It is particularly preferred that for realizing transmission member
The required rigid material of part is made up of the material for the type being generally used in Flight Vehicle Structure, for example aluminium, steel, titanium or they
Alloy or the complex fiber material for example with carbon fiber and/or glass fibre.
Although it is preferred that the plate shape transmitting element intersected is integratedly realized, it is also envisaged that, the plate shape of intersection is passed
Element is passed to be made up of some.However, in the context of the present invention, integral plate shape transmitting element and by some
The plate shape transmitting element of composition is realized in the form of the structural rigidity element without hinge portion.
Due to the transmitting element intersected with rotor blade installed part two adjacent damping units of formation according to the present invention
Global facility, and thus directly and the two adjacent damping units are functionally connected to, act on corresponding rotor blade
Power can directly be distributed to two damping units in an improved way so that the damping of lead-lag motion is similarly obtained and changed
It is kind.According to the present invention, term " feature connection " refers to that the transmitting element intersected is integrally formed into damping unit as follows
In：Relative motion can be carried out between the plate shape transmitting element of intersection and the miscellaneous part of damping unit.In the upper of the present invention
Hereinafter, the direct feature connection between plate shape transmitting element and damping unit should be explained as follows：With from
Known rotor blade coupling arrangement is compared in US4915585, does not have to arrange additionally between transmitting element and damping unit
Fastener.
In the context of the present invention, rotor blade coupling arrangement of the invention can be preferably coupled to the rotation of main rotor
Wing main shaft.Alternatively, however, it is conceivable that the rotor blade coupling arrangement of the present invention is arranged on anti-torque rotor.This
The rotor blade coupling arrangement of invention is also adapted to use in gyroplane that is manned and remotely driving.
Preferably, rotor blade coupling arrangement of the invention includes the elastic spherical axis for rotor blade installed part respectively
Element is held, to allow to move pivotally and motion of flapping.It is particularly preferred that real as follows in rotor blade coupling arrangement
Now with arrangement spherical bearing element：At least three rotor blade installed parts are flexibly operated along direction of rotation during rotation, and
At least three rotor blade installed parts can be performed around the pivot axis extended substantially perpendicular to rotor plane relative to rotation
Wing head central part moves pivotally, so as to allow " lead-lag " to move.In addition, elastic spherical bearing element is also as follows
Realize：Elastic spherical bearing element is flexibly operated along the direction moved of flapping.In addition, elastic spherical bearing element is designed to
Operated to flexible rotation relative to " blade pitch (blade pitch, blade pitgh) ".In expert, the bearing being so designed that
Element is also referred to as so-called " stacking sphere thrust bearing (laminated spherical thrush bearing) ".
Rotor head central part is preferably characterized in that with least two openings, wherein being respectively disposed with each opening
Elastic spherical bearing element.Alternatively, it is also contemplated that at the position placement of mechanical bearing element, rather than elastic sphere
Bearing element.
This elastic spherical bearing element advantageously causes centrifugal load to be delivered to rotation from respective rotor blade installed part
Wing main shaft.This elastic spherical bearing element especially transmits centrifugal force (under stress) and allows flap motion, pivot fortune
Dynamic and so-called rotation " blade pitch " motion.In the context of the present invention, term " elastomer " refers to preferably as material
Expect the rubber used so that spherical bearing elastic deformation under stretching and compressive load, but then revert again to their original
Begin undeformed shape.
There is disclosed herein other advantageous embodiments.
The plate shape transmitting element of intersection is preferably mounted so that they for example can have by sliding bearing, particularly
The sphere rocker bearing (spherical rocker bearing) of anti-friction layer, and/or by elastomer bearing, particularly tool
There is the sphere rocker bearing of one or more elastomer layers, tilted relative to rotor blade installed part.This rocker bearing can
Accessible rotary motion is carried out between airfoil blades installed part and transmitting element.
Damping unit realizes preferably in the form of band type damper, wherein it is particularly preferred that band type damper include and
Accommodate at least two plate shape transmitting elements at least in part, the two plate shape transmitting elements be spaced apart from each other and respectively with it is adjacent
Rotor blade installed part intersect.In other words, in the context of the present invention it is conceivable that with any kind of board-like resistance
The shape of Buddhist nun's device or any other " between blade " damper (such as hydraulic damper, it can accommodate the plate shape transmitting element of intersection)
Formula realizes damping unit.
In the damping unit realized in the form of band type damper, in other words, damp by the board-like of elastomeric plates form
The shearing of the active cell (active unit) of damper is realized.Elastomeric plates preferably it is incorporated as it is viscoelastic, i.e., for
Energy accumulation is elastic, and is sticky for energy absorption and energy conversion (damping).
The elastomeric plates of band type damper preferably by comprising such as natural rubber, silicon rubber, ethylene propylene diene rubber (EPDM),
The rubber element of polyurethane, butyl rubber, polyurethane rubber, polyvinyl acetate, polyvinyl chloride etc..It is desirable to select with extremely
The material of few 0.1 fissipation factor is used for elastomeric plates.
Plate shape transmitting element preferably includes the metal of such as aluminium, steel or titanium, or is for example drawn with carbon fiber, Kev
(Kevlar) material of the complex fiber material form of fiber, aramid fiber and/or glass fibre.
Because the plate shape transmitting element intersected respectively with rotor blade installed part is accommodated simultaneously by damping unit at least in part
And be in other words integrated into damping unit, therefore the plate shape transmitting element intersected shows as two in the case according to the invention
The part of individual adjacent damping unit.Due to by with the plate shape transmitting element that rotor blade installed part intersects be integrated into two it is adjacent
Damping unit in, the plate shape transmitting element of intersection directly and is functionally connected to two adjacent damping units.
Compared to the damping unit for the band type damper form being disposed between rotor blade installed part, rocker bearing is excellent
Selection of land more rigidly realizes in the intersection region of rotor blade installed part, especially along the direction of rotation of rotor blade and/
Or along blade pitch axis (blade pitch axis, blade pitch axis) be linear.In the context of the present invention,
The rigidity of the damping unit of band type damper form refers to selection and the part by its part and its geometry or shape
Achievable fastening caused by rigidity.
The damping unit (being realized in the form of band type damper) of the rotor blade coupling arrangement of the present invention is preferably able to
Realize, or realized with the rigidity between 0.5kN/mm and 10kN/mm, particularly between 1kN/mm and 4kN/mm.Change speech
It, the rigidity of the damping unit of band type damper form easily can be adjusted specifically for respective application, and special
Not, the resonant frequency of rotor is adjustable.
It is particularly preferred that the damping compared to the band type damper form being disposed between rotor blade installed part is filled
Put, rocker bearing is realized with the rigidity of more than at least three times (at least three-times more), especially with least five
Times more than rigidity realization, especially along the direction of rotation of rotor blade and/or along blade pitch axis be linear.Relatively
The rigidity for the rocker bearing realized in the rigidity of damping unit is higher, joins from rotor blade installed part to the rotor blade of the present invention
Loss in the respective motion transmission for separating ring or ring arrangement of connection device is lower.Another program of the present invention is related to a kind of rotation
Wing head, it includes the rotor blade coupling arrangement of the present invention, and is intended to be connected to mast.
According to the advantageous embodiment of the rotor blade coupling arrangement of the present invention, rocker bearing can by rocker bearing installation bolt and
Sphere rocker bearing ball element is constituted, and wherein rocker bearing installation bolt is actually similar to the rotor leaf radially outward arranged
Piece installed part causes it substantially to extend along the direction of blade pitch axis.
According to another preferred improvement of the rotor blade coupling arrangement of the present invention, rocker bearing is alternately recessed respectively
Enter in the respective transmitting element for separating ring or the plane of a loop of ring arrangement.
Brief description of the drawings
The preferred illustrative embodiment of the purpose of the present invention is more fully described with reference to the accompanying drawings.In the drawings：
Fig. 1 shows the stereogram of the preferred embodiment of the rotor blade coupling arrangement of the present invention；
Fig. 2 shows the details of the rotor blade coupling arrangement 2 of the invention of the zoomed-in view with damping unit D；
Fig. 3 shows the rotor blade installation along the rotor blade coupling arrangements of the invention splitted of the line A-A in Fig. 1
The section of part；
Fig. 4 shows the rotor blade installation along the rotor blade coupling arrangements of the invention splitted of the line B-B in Fig. 1
Section between part, rocker bearing and transmitting element；
Fig. 5 shows the rotor blade coupling arrangement of the invention along the band type damper forms splitted of the line C-C in Fig. 1
Damping unit D section；
Fig. 6 shows the stereogram of the additional preferred embodiments of the rotor blade coupling arrangement of the present invention；
Fig. 7 a show the additional of rotor blade coupling arrangement being splitted along line the A '-A ' in Fig. 6, by the present invention
The longitudinal section of the rotor blade installed part of preferred embodiment；
Fig. 7 b show the additional of rotor blade coupling arrangement being splitted along line the A '-A ' in Fig. 6, by the present invention
The longitudinal section of the rotor blade installed part of preferred embodiment, wherein, rocker bearing installation bolt radial deflection；
Fig. 8 a show the additional of rotor blade coupling arrangement being splitted along line the B '-B ' in Fig. 6, by the present invention
The cross section of the rotor blade installed part of preferred embodiment；And
Fig. 8 b show along line the B '-B ' in Fig. 6 the rotor of rotor blade coupling arrangement of the invention splitted, passed through
The cross section of blade mount, wherein, rocker bearing installation bolt is deflected along direction of rotation.
Embodiment
Fig. 1 shows the stereogram of the preferred embodiment of the rotor blade coupling arrangement 2 of the invention of rotor head 1.At this
In the case of kind, five unshowned rotor blades can be arranged on rotor head 1 by the rotor blade coupling arrangement 2 of the present invention
On.Rotor blade coupling arrangement 2 includes rotor head central part 7 and on rotor head central part and for accommodating five rotations
Five rotor blade installed parts 4 of wing blade.Rotor head central part 7 is connected to mast in the way of anti-torsion (in Fig. 1 not
Show), wherein mast can rotatably be set by unshowned driver, and the required lift that flies is on edge
Produced during direction of rotation U rotation.
Rotor blade installed part 4 includes upper rotor blade installing plate 5 and lower rotor blade installing plate 6 respectively.It is outside in footpath
In portion region, rotor blade installing plate 5 and 6 has opening 33, to accommodate the resilient support bolt for fastening rotor blade
33.Fig. 1 also show the blade adjustments rod 35 for being connected to rotor blade installed part 4, wherein the energy of rotor blade installed part 4 coupled
It is enough to be rotated by blade adjustments rod 35 around blade pitch axis Rbp (also referred to as " blade-pitch " axis) so that can to adjust
Rotor blade rises or falls (so-called " blade pitch ") relative to the blade pitch angle for flowing into air, and gyroplane.
Rotor head central part 7 shown in Fig. 1 realizes that it is additionally provided with opening 8 in the form of disk, wherein, elastic spherical axis
Element 20 is held to be arranged in opening 8.Double-head arrow LL in Fig. 1 represent elastic spherical bearing element 20 respectively allow for it is described
Lead-lag motion is relevant, around the three-dimensional pivoting action LL perpendicular to the rotor plane RE pivot axis RLL extended, this
Occurred according to the arrangement (alignment, alignment) of rotor blade 3.Pivoting action LL in rotor plane RE can be along rotation
Direction U (" advanced ") or the direction (" delayed ") opposite with direction of rotation U occur.
According to Fig. 1, shape is distinguished in the combination with rotor blade installed part 4 and damping unit the D all transmitting elements 10 intersected
Composition open loop or ring arrangement, wherein under the coupled situation of the rotor blade coupling arrangement of the invention with rotor head, dividing
Directly mechanical connection is not present between open loop and mast --- as shown in Figure 1 --- so that because upper panel blade is installed
Being articulated and connected between part 5 and lower panel blade mount 6, is separated ring and is installed in complete universal mode.
Hereafter, identical part is indicated by the same numbers in figure.
Fig. 2 shows the details of the rotor blade coupling arrangement 2 of the present invention, i.e. damping unit D zoomed-in view, the resistance
Buddhist nun's device D is arranged between two adjacent rotor blade installed parts 4, as so-called " between blade " damper and with plate
The form of formula damper is realized.
Upper damping element 15 ' and lower damping element 16 ' are arranged on the plate shape transmission to form ring segment (ring segment)
On first arm 11 of element 10, so as to be integrally formed in the way of feature is connected with damping unit D, to form the first damper portion
D1.In addition, upper damping element 15 " and lower damping element 16 " are arranged on the adjacent tabular transmission of adjacent rotor blade installed part 4
On second arm 12 of element 10, and thus it is integrally formed in the way of feature is connected with damping unit, to form second
Damper portion D2.In this case, being articulated and connected between the plate shape transmitting element 10 of formation adjacent annular section favorably is shifted
Into damping unit.
Fig. 2 also show damping element 15 ', 15 ", 16 ', 16 ", and these damping elements have respectively is enclosed in two plates
Elastomeric plates 18 between 17.Damping element 15 ', 15 ", 16 ', 16 " can be secured to one another by vulcanization and/or bonding.Plate 17 can
To be for example made up of the metal or complex fiber material of such as steel, aluminium or titanium.
Damping unit D includes upper junction plate 28 and lower connecting plate 29, and they are in the first damper portion D1 and the second damper portion D2
Between produce connection.Connecting plate 28,29 and the miscellaneous part of damper portion D1, D2 are secured to one another and by pre-add by means of screw 30
Compression displacement of the stress to restriction.
According to damping unit D alternate embodiment, it is contemplated that damping element 15 ', 15 " is for example firm by vulcanization
Upper junction plate 28 is connected to property, to be consequently formed upper integral damping part, wherein plate 17 can be away from the one of arm 11,12
Advantageously it is eliminated (i.e. between connecting plate 28 and damping element 15 ', 15 ") on side, therefore to mitigate weight.Lower overall resistance
Buddhist nun's part can be similarly implemented by the way that damping element 16 ', 16 " is rigidly connected into lower connecting plate 29.With arm 11,12
It is secured to one another that upper damped part and lower damped part are for example threadably engaged part.
In the damping unit D shown in Fig. 2, during the operation of rotor head, the first arm 11 of transmitting element and the first resistance
The relative motion between miscellaneous part in Buddhist nun portion D1 occurs due to the shearing of the elastomeric plates 18 of damping element 15 ', 16 ',
And the relative motion between the miscellaneous part in the second arm 12 and the second damper portion D2 of additional transmitting element 10 is due to damping
The shearing of the elastomeric plates 18 of element 15 ", 16 " and occur.Each damping element 15 ', 15 ", 16 ', 16 " is with the pattern of sandwich-like
Realize, and be made up of respectively two plates 17 and the elastomeric plates 18 being disposed there between, wherein the difference of tabular transmitting element 10 position
Between two damping elements 15 ', 15 ", 16 ', 16 ".
Fig. 3 also show along what the line A-A in Fig. 1 was splitted, and there is upper rotor blade installing plate 5 and lower rotor blade to pacify
Fill the section of the rotor blade installed part 4 of the rotor blade coupling arrangement of the invention of plate 6.According to Fig. 3, installed by rocker bearing
The rocker bearing 25 that bolt 26 and sphere rocker bearing ball element 27 are constituted is arranged in the region of transmitting element 10, its
In, rocker bearing installation bolt 26 is actually similar to the ground of rotor blade installed part 4 and radially outward arranged so that its substantially edge
Blade pitch axis Rbp direction extension, and wherein this of rocker bearing installation bolt 26 is arranged in blade pitch axis
It is proved to be particularly advantageous during Rbp rotation.Rocker bearing 25 also includes rocker arm shaft bearing 40, and the rocker arm shaft bearing 40 is in face
There is the spherical form corresponding to rocker bearing ball element 27 to the side of rocker bearing ball element 27.Such as Teflon layer
Or the anti-friction layer of elastomer layer 41 is disposed in the region between rocker arm shaft bearing 40 and rocker bearing ball element 27.Shake
Arm axle is held in 25 distance pieces 19 being disposed between rotating vanes installing plate 5,6, and is fastened by means of fastening tool 42.Can
Selection of land is further envisioned that rocker arm shaft bearing 40 and distance piece 19 are realized in the form of the global facility of one so that installs and ties up
The workload of shield can be minimized advantageously.
Elastic spherical bearing element 20 is shown in the opening 8 of rotor head central part 7.Elastic spherical bearing element 20 includes
The parts of bearings 21 of shaping, in the form of spherical segment (spherical segment) realize parts of bearings 22 and partly hold
Receive the parts of bearings 23 of rotor head central part 7.Parts of bearings 21 is substantially rigidly connected to rotor blade installing plate 5,6.This
Outside, parts of bearings 22 is made up of laminar rubber/hardware, and due to its flexible design, it allows to pivot, flaps and adjusted with propeller pitch angle
Section.
Fig. 4 shows the rotor blade peace along the rotor blade coupling arrangements 2 of the invention splitted of the line B-B in Fig. 1
Section between piece installing 4, rocker bearing 25 and transmitting element 10, i.e., in the region of the recess 13 of transmitting element 10.According to figure
4, rocker bearing 25 is disposed in the distance piece 19 between rotor blade installing plate 5 and lower rotor blade installing plate 6 so that
Transmitting element 10 is in the case where " blade pitch " is adjusted, to be installed relative to the tiltable mode of rotor blade installed part 4.Shake
Arm axle, which holds 25, includes rocker bearing installation bolt 26, and the rocker bearing installation bolt 26 is wrapped by outer rocker arm bearing rolling element 27
Enclose so that rocker bearing 25 is realized in the form of sphere rocker bearing.Rocker bearing ball element 27 preferably by such as steel or
The metal of the higher-strengths such as titanium is made.
Fig. 5 also show rotor leaf of the invention being splitted along the line C-C in Fig. 1, by band type damper form
The damping unit D of piece coupling arrangement section.
Four through holes 32 are had according to Fig. 5, damping unit D.Sleeve 31 is respectively disposed with each hole 32, wherein passing through phase
The length of ground selection sleeve 32 is answered, prestressing force can be adjusted to the compression displacement to restriction.In other words, damping unit D part
The compression displacement of restriction is adjusted in the controlled mode of displacement.
According to Fig. 5, (it is respectively included in besieged elasticity between two plates 17 to damping element 15 ', 15 ", 16 ', 16 "
Body plate 18) it is partially positioned in form-fit fashion in arm 11,12 in connecting plate 28,29 and on the opposite sides.By
In this arrangement of damping element 15 ', 15 ", 16 ', 16 ", for example, the arm 11 of plate shape transmitting element 10 is relative to miscellaneous part
(for example, damping unit D connecting plate 28,29) can advantageously be suppressed along direction x relative motion.
For example, relative motion of the arm 11 of plate shape transmitting element 10 along direction x is moved by the lead-lag of rotor blade
It is caused, in other words, it is suppressed by the shearing of the elastomeric plates 18 of the damping element 15 ', 16 ' on damper portion D1.According to figure
5, gap d 1 (damper portion D1) and d2 (damper portion D2) be respectively present in screw 30 extend through in the region of arm 11 and arm 12 with
And the external diameter of respective sleeve 31, wherein these gap ds 1, d2 limit maximum displacement distance.In addition, extra shift length d3
It is limited between the first arm 11 of plate shape transmitting element 10 and the second arm 12 of another plate shape transmitting element 10, the wherein displacement
Shift length d1+d2 summation is ideally corresponded roughly to apart from d3.
Plate shape transmitting element 10 and arm 11,12 are able to absorb the bullet due on x, y direction that gap d 1 and d2 are produced
Property thrust deformation, and due to the elastic compression morphotropism in damping element 15 ', 16 ' and 15 ", 16 " in a z-direction
Some deformations.
Fig. 6 shows the stereogram of the additional preferred embodiments of the rotor blade coupling arrangement 2 of the present invention, wherein, rocking arm
Bearing 25 is distinguished in recessed transmitting element 10, and the transmitting element 10 is perpendicular to the respective plane of a loop for separating ring or loop device.
Upper damping element 15 ' and lower damping element 16 ' are disposed in the first of the plate shape transmitting element 10 to form ring segment
On arm 11, so as to be integrally formed in the way of feature is connected with damping unit D, to form the first damper portion D1.
In this case, rocker bearing 25 includes rocker arm shaft bearing 40, and the rocker arm shaft bearing 40 is towards rocker bearing
There is the spherical form corresponding to rocker bearing ball element 27 on the side of ball element 27.In this case, rocker arm shaft
Bearing 40 is received and in the recess of plate shape transmitting element 10.The anti-friction layer or aluminium bronze of such as Teflon layer or conjunction
The anti-friction layer of suitable plastics or elastomer layer 41 is disposed in the area between rocker arm shaft bearing 40 and rocker bearing ball element 27
In domain, wherein the layer can be connected to steel, ceramics or the tungsten carbide of hardening and polishing.
In this embodiment, rocker bearing installation bolt 26 is substantially pacified in the upper rotor blade of rotor blade installed part 4
Fill and extend between plate 5 and lower rotor blade installing plate 6.
Fig. 7 a show the rotor of rotor blade coupling arrangement being splitted along line the A '-A ' in Fig. 6, by the present invention
The longitudinal section of blade mount 4.
In this case, rotor head central part 7 has opening 8, wherein elastic spherical bearing element 20 is arranged in
In opening 8.Parts of bearings 21 that bearing element 20 includes shaping, the parts of bearings 22 and partly realized in spherical segment form
Accommodate the parts of bearings 23 of rotor head central part 7.
Rocker bearing 25 includes rocker bearing installation bolt 26, and the rocker bearing installation bolt 26 is by outer rocker arm bearing ball
Element 27 is surrounded so that rocker bearing 25 is realized in the form of sphere rocker bearing.According to Fig. 7 a, in upper rotor blade installing plate
The rocker bearing installation bolt 26 extended between 5 and lower rotor blade installing plate 6 is contained in guide cylinder 43 and lower guide cylinder 44
In, wherein in this case, upper guide cylinder 43 is integrally formed on upper rotor blade installing plate 5, and the one of lower guide cylinder 44
It is formed on lower rotor blade installing plate 6.Or it is also contemplated that guide cylinder 43,44 is realized and quilt in the form of individual components
It is fastened on rotor blade installing plate 5,6.
According to Fig. 7 a, the rocker bearing 25 being made up of rocker bearing installation bolt 26 and sphere rocker bearing ball element 27
In the region for being arranged in transmitting element 10, wherein, idle condition or inactive state in rotor, rocker bearing installation bolt 26
It is arranged or is aligned perpendicular relative to respectively plane of a loop and perpendicular to propeller pitch angle axis Rbp.In addition, rocker bearing installation bolt 26
It is arranged such that it extends parallel to the longitudinal axis of bolt 34 in this case.
In this application, Fig. 7 b show the rotor blade connection dress under the mode of operation of the rotor of rotary wing blade
2 are put, wherein, rocker bearing installation bolt 26 can be tilted or yaw tilt angle á respectively, and the inclination angle is preferably 20 °, especially
Ground is 1 ° to 5 °.
As an example, Fig. 7 b show rocker bearing installation bolt 26, its direction along blade pitch axis Rbp radially to
Extrinsic deflection inclination angle á.
Fig. 8 a, which also show, to be splitted along line the B '-B ' in Fig. 6, by the additional of rotor blade coupling arrangement of the invention
The cross section of the rotor blade installed part of preferred embodiment.
In this case, rocker bearing installation bolt 26 under the idle condition of rotor or inactive state respectively by cloth
Put or be aligned perpendicular relative to plane of a loop.
As an example, Fig. 8 b show the rocker bearing installation bolt in the direction of rotation upper deflecting of rotary wing blade
26.In this case, rocker bearing installation bolt 26 can also tilt in this direction around propeller pitch angle axis Rbp respectively or
Deflect an inclination angleThe inclination angle is preferably 20 °, in particular 5 ° to 15 °.
Due to the design of the rocker bearing 25 of sphere rocker bearing form, rocker bearing installation bolt 26 can be surrounded respectively
All axis tilt or yaw tilt angle á andThat is, in the centre position of any deflection as shown in Fig. 7 b and Fig. 8 b or folded
Plus it is middle inclination or yaw tilt angle á and
The rocker bearing for the rocker bearing 25 realized in the form of sphere rocker bearing (as shown in Fig. 6-Fig. 8 b) installs spiral shell
This arrangement of bolt 26 and arrangement advantageously ensure that the special abundant exercise free degree and collision free.Rocker bearing installation bolt
26 deflection or banking motion are generally by " blade pitch " around blade pitch axis Rbp, by around pivot axis RLL
Pivoting action and caused by motion of flapping (also referred to as " flapping ").
List of numerals
1 rotor head
2 rotor blade coupling arrangements
4 rotor blade installed parts
Rotor blade installing plate on 5
6 times rotor blade installing plates
7 rotor head central parts
8 openings
10 transmitting elements
11 first arms
12 second arms
13 recesses
Damping element on 15 ', 15 " (band type dampers)
16’；Damping element under 16 " (band type dampers)
17 plates (damping element)
18 elastomeric plates (damping element)
19 distance pieces
20 elastic spherical bearing elements
21 parts of bearings
22 parts of bearings
23 parts of bearings
25 rocker bearings
26 rocker bearing installation bolts
27 rocker bearing ball elements
28 upper junction plates
29 lower connecting plates
30 (band type damper) screws
31 (band type damper) sleeves
The hole of 32 (transmitting elements)
33 (rotor blade installed part) openings
34 (rotor blade installed part) bolts
35 blade adjustments bars
40 rocker arm shaft bearings
41 (rocker bearing) anti-friction layer/elastomer layers
42 fasteners
Guide cylinder on 43
44 times guide cylinders
á inclinations angle
D damping units
LL moves pivotally (lead-lag)
RE rotor planes
RLL pivotal axis
Rbp blade pitch axis
U (rotor blade) direction of rotation
Claims (7)
1. a kind of rotor blade coupling arrangement (2), for being connected to mast with formed be used for gyroplane, it is particularly direct
The rotor head (1) of lift or helicopter, the rotor blade coupling arrangement includes：
- rotor head central part (7),
- at least three rotor blade installed parts (4), it is arranged on the rotor head central part (7) and is located at for receiving
At least three rotor blades in rotor plane (RE), and
- at least one attachment means, between the adjacent rotor blade installed part (4),
Wherein, the rotor blade installed part (4) can surround the pivotal axis extended perpendicular to the rotor plane (RE) respectively
Line (RLL) is pivoted motion,
Wherein, at least one described attachment means are realized in the form of damping unit (D), and
Wherein, the rotor blade coupling arrangement (2) include plate shape transmitting element (10), the plate shape transmitting element respectively with institute
State rotor blade installed part (4) alter-parallel and be connected at least one described damping unit (D),
Characterized in that, the transmitting element (10) formation two intersected respectively with the rotor blade installed part (4) is adjacent
The damping unit (D) a part, so as to directly and be functionally connected to described two adjacent damping units (D).
2. rotor blade coupling arrangement (2) according to claim 1,
Characterized in that,
The transmitting element (10) intersected for example by sliding bearing, particularly has friction resistant by rocker bearing (25)
The sphere rocker bearing of layer (41), and/or by elastomer bearing, the particularly ball with one or more elastomer layers (41)
Face rocker bearing, is installed relative to the rotor blade installed part (4) in the inclined mode of energy.
3. rotor blade coupling arrangement (2) according to claim 1 or 2,
Characterized in that,
The damping unit (D) realized in the form of band type damper, wherein the band type damper is included and at least in part
Accommodate two transmitting elements (10), two transmitting elements be spaced apart from each other and respectively with the adjacent rotor leaf
Piece installed part (4) intersects.
4. rotor blade coupling arrangement (2) according to claim 3,
Characterized in that,
Compared to the damping unit (D) for the band type damper form being disposed between the rotor blade installed part (4),
The rocker bearing (25) is more rigidly implemented in the intersection region of the rotor blade installed part (4), particularly edge
The direction of rotation of the rotor blade and/or along the blade pitch axis (Rbp) be linear.
5. rotor blade coupling arrangement (2) according to claim 4,
Characterized in that,
The damping unit (D) of band type damper form between 0.5kN/mm and 10kN/mm, particularly 1kN/mm with
Rigidity between 4kN/mm can be implemented or be implemented.
6. the rotor blade coupling arrangement (2) according to claim 4 or 5,
Characterized in that,
Compared to the damping unit (D) for the band type damper form being disposed between the rotor blade installed part (4),
The rocker bearing (25) is realized with rigidity more than at least three times, is particularly realized with least more than five times of rigidity, especially
Be along the direction of rotation of the rotor blade and/or along the blade pitch axis (Rbp) be linear.
7. a kind of rotor head (1), including the rotor blade coupling arrangement (2) according to any one of foregoing claim, are used for
It is connected to mast (9).
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH01639/15A CH711738A1 (en) | 2015-11-11 | 2015-11-11 | Blade coupling device for coupling with a rotor mast for forming a rotor head of a rotorcraft. |
| CH01639/15 | 2015-11-11 | ||
| CH01360/16 | 2016-10-11 | ||
| CH01360/16A CH711754A2 (en) | 2015-11-11 | 2016-10-11 | Blade coupling device for coupling with a rotor mast for forming a rotor head of a rotorcraft. |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106965927A true CN106965927A (en) | 2017-07-21 |
Family
ID=55182178
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610998393.9A Pending CN106965927A (en) | 2015-11-11 | 2016-11-11 | Rotor blade coupling arrangement for the rotor head of gyroplane |
Country Status (4)
| Country | Link |
|---|---|
| CN (1) | CN106965927A (en) |
| BR (1) | BR102016026434A2 (en) |
| CH (2) | CH711738A1 (en) |
| RU (1) | RU2016144174A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110316363A (en) * | 2018-03-28 | 2019-10-11 | 雅马哈发动机株式会社 | More gyroplanes |
| CN112597582A (en) * | 2020-12-11 | 2021-04-02 | 中国直升机设计研究所 | Longitudinal helicopter rotor and fuselage coupling stability modeling method |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT202100018017A1 (en) | 2021-07-08 | 2023-01-08 | Milano Politecnico | Improved damping helicopter rotor |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3842945A (en) * | 1971-05-13 | 1974-10-22 | J Potter | Viscoelastic damper |
| EP0080920A1 (en) * | 1981-11-25 | 1983-06-08 | AEROSPATIALE Société Nationale Industrielle | Rotor for rotor craft with articulated joints incorporated in the blade root |
| US4915585A (en) * | 1988-04-29 | 1990-04-10 | Aerospatiale Societe National Industrielle | Rotary-wing aircraft rotor head having resilient-return interblade ties with built-in damping |
| FR2929675A1 (en) * | 2008-04-07 | 2009-10-09 | Eurocopter France | Visco-elastic damping device for rotor blades of helicopter, has longitudinal parts continuously and mechanically connected with each other using number of rigid metallic elements extending from one of parts to another part |
| CN202244082U (en) * | 2011-08-29 | 2012-05-30 | 湖南山河科技股份有限公司 | Shimmy damper for rotor wing of helicopter |
| CN102501970A (en) * | 2011-11-15 | 2012-06-20 | 中国航空工业集团公司北京航空材料研究院 | Band type damper and preparation method thereof |
| CN103192986A (en) * | 2012-01-10 | 2013-07-10 | 贝尔直升机泰克斯特龙公司 | Rotorcraft vibration suppression system in a four corner pylon mount configuration |
-
2015
- 2015-11-11 CH CH01639/15A patent/CH711738A1/en not_active Application Discontinuation
-
2016
- 2016-10-11 CH CH01360/16A patent/CH711754A2/en not_active Application Discontinuation
- 2016-11-10 RU RU2016144174A patent/RU2016144174A/en not_active Application Discontinuation
- 2016-11-11 CN CN201610998393.9A patent/CN106965927A/en active Pending
- 2016-11-11 BR BR102016026434-0A patent/BR102016026434A2/en not_active Application Discontinuation
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3842945A (en) * | 1971-05-13 | 1974-10-22 | J Potter | Viscoelastic damper |
| EP0080920A1 (en) * | 1981-11-25 | 1983-06-08 | AEROSPATIALE Société Nationale Industrielle | Rotor for rotor craft with articulated joints incorporated in the blade root |
| US4915585A (en) * | 1988-04-29 | 1990-04-10 | Aerospatiale Societe National Industrielle | Rotary-wing aircraft rotor head having resilient-return interblade ties with built-in damping |
| FR2929675A1 (en) * | 2008-04-07 | 2009-10-09 | Eurocopter France | Visco-elastic damping device for rotor blades of helicopter, has longitudinal parts continuously and mechanically connected with each other using number of rigid metallic elements extending from one of parts to another part |
| CN202244082U (en) * | 2011-08-29 | 2012-05-30 | 湖南山河科技股份有限公司 | Shimmy damper for rotor wing of helicopter |
| CN102501970A (en) * | 2011-11-15 | 2012-06-20 | 中国航空工业集团公司北京航空材料研究院 | Band type damper and preparation method thereof |
| CN103192986A (en) * | 2012-01-10 | 2013-07-10 | 贝尔直升机泰克斯特龙公司 | Rotorcraft vibration suppression system in a four corner pylon mount configuration |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110316363A (en) * | 2018-03-28 | 2019-10-11 | 雅马哈发动机株式会社 | More gyroplanes |
| CN110316363B (en) * | 2018-03-28 | 2022-11-22 | 雅马哈发动机株式会社 | Multi-rotor aircraft |
| CN112597582A (en) * | 2020-12-11 | 2021-04-02 | 中国直升机设计研究所 | Longitudinal helicopter rotor and fuselage coupling stability modeling method |
Also Published As
| Publication number | Publication date |
|---|---|
| CH711738A1 (en) | 2017-05-15 |
| BR102016026434A2 (en) | 2018-05-02 |
| RU2016144174A (en) | 2018-05-10 |
| CH711754A2 (en) | 2017-05-15 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| CB02 | Change of applicant information |
Address after: Morris, Switzerland Applicant after: Popular science Pallister Group Ltd. Address before: Swiss hole Applicant before: Swiss Marienk Helicopter |
|
| CB02 | Change of applicant information | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170721 |
|
| RJ01 | Rejection of invention patent application after publication |