CN104340360B - The coupling device of aircraft landing gear driven wheel - Google Patents
The coupling device of aircraft landing gear driven wheel Download PDFInfo
- Publication number
- CN104340360B CN104340360B CN201410445297.2A CN201410445297A CN104340360B CN 104340360 B CN104340360 B CN 104340360B CN 201410445297 A CN201410445297 A CN 201410445297A CN 104340360 B CN104340360 B CN 104340360B
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- wheel
- arm
- coupling device
- holding part
- karyomorphism
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- 230000001808 coupling Effects 0.000 title claims abstract description 44
- 238000010168 coupling process Methods 0.000 title claims abstract description 44
- 238000005859 coupling reaction Methods 0.000 title claims abstract description 44
- 238000009434 installation Methods 0.000 claims description 4
- 239000003638 reducing agent Substances 0.000 description 7
- 230000004048 modification Effects 0.000 description 5
- 238000006011 modification reaction Methods 0.000 description 5
- 239000002184 metal Substances 0.000 description 4
- 230000000712 assembly Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000002788 crimping Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000000295 complement Effects 0.000 description 1
- 230000000875 corresponding Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000452 restraining Effects 0.000 description 1
- 230000000630 rising Effects 0.000 description 1
- 238000009738 saturating Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Abstract
The elasticity coupling device (7) between the wheel (3) of the aircraft landing gear motor-driven rotating mechanism (6) coaxial with the wheel includes multiple arms (9), the arm is fixed together in the first inner radial end and the motor-driven rotating mechanism and rotates and be suitable for being connected to the wheel (3) in the opposite outer radial end of arm, and the arm (9) is substantially rigid in the plane perpendicular to the pivot center of the wheel and is flexible in the direction for being generally transverse to the plane.
Description
Technical field
The present invention relates to a kind of bullets between the motor-driven mechanism coaxial with the wheel of the wheel in aircraft landing gear
Property coupling device and it is equipped with the tracker action of wheel and the undercarriage of this coupling device.
Background technology
In order to save fuel, reducing noise, the limitation duration of operation and thus limit aircraft engine, (turbojet is sent out
Motivation, turboprop ...) abrasion etc. the reason for, it has been suggested that make undercarriage motorization of the wheel from them,
So as to make their autonomous on the platform of airport.
The known this motorization for ensureing undercarriage wheel by tracker action, tracker action include engine, retarder
Device and the rotation coupling device between reducer arrangement output terminal and wheel wheel rim, engine is, for example, motor.
Moreover, when aircraft is in ground taxi, since aircraft weight is transferred to by undercarriage leg on wheel shaft, undercarriage
Wheel shaft and wheel bear moderate finite deformation.
Therefore it is required that in wheel --- wheel deforms, and then causes the deformation of wheel shaft --- and and undercarriage leg
Coupling device between the engine/reducer assemblies being connected absorbs these deformations.
To solve the problems, such as this, from a kind of device known to document FR 0959586, wherein, by metal spring by engine/
The driving ring gear of reducer assemblies is connected to wheel rim, and metal spring can absorb displacement or change of the wheel rim compared with ring gear
Shape.
However, this device cannot most preferably transfer torque between driving ring gear and wheel.
The content of the invention
The present invention is intended to provide between a kind of wheel in undercarriage and the coaxial motor-driven mechanism of the wheel
Coupling device, although the wheel shaft of carrying wheel deforms, the coupling device can ensure the motor-driven mechanism and wheel
Between torque optimum transfer, and the coupling device have no substantial effect on wheel assembly or disassembly operation complexity with
And the duration.
For this purpose, it is an object of the invention to provide the automotive vehicles coaxial with the wheel of the wheel in aircraft landing gear
A kind of elastic coupling device between structure, the elasticity coupling device include multiple arms, and the arm is in the first inner radial end
It links together with the motor-driven mechanism and rotates and be suitable for being connected to the wheel at the opposite outer radial end of arm
Son, the arm are substantially rigid in the plane perpendicular to the pivot center of the wheel and are being generally transverse to described put down
There is flexibility in the direction in face.
The apparatus according to the invention is increased the light structures of aircraft weight by unobvious, can ensured in automotive vehicles
Good torque transfers between structure and wheel, while allows due to wheel caused by the deformation for the wheel shaft for being equipped with wheel thereon
Stroke between trip.
Possible feature according to the present invention, the arm are connected with wheel hub, and the wheel hub is suitable for being fixed to described
On motor-driven rotating mechanism.The coupling device is so as to as in star-shaped component, being easy to optimize weight and connect with motor-driven mechanism
Be connected together rotation, motor-driven mechanism such as gear.
Another possible feature according to the present invention, the arm, which is suitable for being accepted at its outer radial end, bears against institute
In each holding part for stating the wheel rim of wheel.The particularly simple linked model participates in the weight guided by the motorization of the wheel
Amount limitation and the convenience of the assembly or disassembly of participation wheel.
Another possible feature according to the present invention, the holding part are essentially the groove shapes with U-shaped section, U-shaped
Section is towards one of its end opening；Also, the arm has elongated karyomorphism part at the outer radial end, and the karyomorphism part is fitted
It shares in being accepted in one of described holding part.This feature can be convenient for the engagement of retaining arm and wheel rim, although due to axis
Deformation causes moving to axial for the corresponding holding part on the end and wheel rim of arm.
Another possible feature according to the present invention, the arm is dimensioned, so that rising and falling in the wheel described
In installation site on frame, the arm is by axial tensioning.This feature, which combines previous feature, can limit karyomorphism part accommodating
Stroke and the length of these holding parts is therefore optimized between axial play in portion.
Another possible feature according to the present invention, the length of the holding part are suitable for ensureing to the karyomorphism part
Constraint, but regardless of the wheel camber angle how.This feature ensures that all arms participate in transferring torque, but regardless of the change of wheel shaft
Shape.
Another possible feature according to the present invention, the holding part are disposed in what is be connected with the wheel rim by portion
In crown wheel.Therefore crown wheel can be used together by welding or other means by fixed common wheel with tracker action.
Another possible feature according to the present invention, the holding part and the karyomorphism part are moveable wear parts.
Therefore these wear parts can be replaced, to limit cost
Another possible feature according to the present invention, the arm are foliated.Its structure provides simplicity and light
Property so as to transfer square turn round, although wheel shaft distortion.
Another possible feature according to the present invention, the blade is in its outer radial end than radial direction end inside it
With smaller section.Therefore flexibility desired by blade can easily be given according to its width and/or thickness.
The present invention also aims to provide a kind of aircraft landing gear, at least one wheel, including the machine
The tracker action and coupling device as defined above of the wheel of motivation structure.This undercarriage can limit and one substantially
The increase of the related weight of the motorizations of a or multiple wheels.
Finally, the present invention also aims to provide a kind of aviation for including at least one undercarriage as defined above
Device.
Description of the drawings
From the description of the embodiment being merely given as examples shown in following Figure, other features and advantages of the present invention
Shown, wherein：
- Fig. 1 is the local perspective view of undercarriage, and undercarriage is equipped with the tracker action of wheel；
- Fig. 2 is the perspective view similar to Fig. 1, and wheel rim is shown with the first plane；
- Fig. 3 is partial sectional view of the mechanism shown in Fig. 1 and 2 along the plane comprising engine axis and axle axis；
- Fig. 4 is that topside wheel rim and the coupling device between topside wheel rim and tracker action have the saturating of part removal
View；
- Fig. 5 is plan view, shows the coupling device of Fig. 4 and the output gear of tracker action；With
- Fig. 6 is local perspective view, shows the part of coupling device.
Specific embodiment
Referring to the drawings, the pillar 1 of aircraft (not shown) undercarriage (not shown in detail) is being taken turns in its end bearing wheel shaft 2
Wheel rim 3 is installed, the tire of wheel rim 3 has been not shown on axis 2.
Wheel motor-driven component including motor 4 and reducer arrangement 5 is installed on wheel shaft 2.As modification, motor 4
It can be fluid pressure motor.
Reducer arrangement 5 will not be discussed in detail.It can be common type well known by persons skilled in the art.It is alternatively such as
The type with oscillating structural member described in patent application EP-2 527 249.Reducer arrangement 5 has output gear 6, in electricity
When motivation 4 rotates, output gear can be driven around wheel shaft 2 and be rotated.
Output gear 6 is couple to wheel rim 3 by coupling device 7.
Coupling device 7 is the component of preferably metal, and star is presented in the plane.The component of the metal includes middle body
Or wheel hub 8 and a certain number of arms 9, middle body or wheel hub it is disk-shaped or as modification in bowl-type, at its center place have with
XX ' is the opening of axis, for particularly by wheel shaft 2, seeing in the plane, arm is in the radial direction of the axis compared with middle body 8
Side upwardly extends.In the embodiment shown in fig. 5, coupling device 7 has 9 arms.
Middle body 8 is in the adjacent place of its inner circumference 10 by crimping, welding or any other suitable mode is coaxially solid
Determine to output gear 6, suitable for operationally ensureing to transfer engine torque between gear 6 and coupling device 7.
Gear 6 is rotationally placed in by bearing 11 on wheel shaft 2.Wheel rim 3 is rotationally placed in wheel by bearing 12 and 13
On axis 2.
The arm 9 of coupling device is blade, and blade is made into integration with middle body 8.It sees in the plane, arm or blade 9 are at it
Bottom be wider, arm or blade are connected in bottom with middle body 8, and arm or blade pass through its end and connect wheel rim
3.Arm 9 can be carried out from their bottom to shrinking for their end along such as Fig. 6 curve side profiles 14 represented.As modification,
Arm can have substantially trapezoidal shape or any other suitable shape with flat sides set.The thickness of arm 9 is from one end to another
One end is not required consistent, can located continuously or discontinuously be changed.
The material of arm 9 and the size on width and thickness are selected such that arm has：
- there is greatly rigidity in the plane perpendicular to the axis X X ' of coupling 7 on arbitrary point, so as in gear 6
Torque is transferred between wheel rim 3,
- it is vertical with the plane perpendicular to axis X X ' and along other directions transverse to the suitable of the plane perpendicular to axis X X '
When flexibility, so as to absorbing the deformation of wheel shaft 2 and wheel 3 in aircraft taxi.
As shown in figure 3, arm 9 comprising axis X X's ' and arm end by fore-and-aft plane in there is bending profile,
The recess portion of profile is bent towards the end side for receiving wheel rim 3 of wheel shaft 2.The volume of the radian along braking mechanism (not shown) be or
More or less it will be evident that it is more or less it will be evident that in institute to be particularly the radian along its larger protruding portion outside volume
It states in volume, protruding portion is contained between wheel shaft 2 and the inside profile being open towards output gear 6 of wheel rim 3.
In order to ensure the connection between coupling device 7 and wheel rim 3, arm 9 has the drum for forming karyomorphism part 15 in its end
Go out part.The karyomorphism part has substantially trapezoidal profile or as modification in lateral cross section (in plane of axis X X ')
Has bossed profile.Preferably, the length (considering the section on the axial plane comprising axis X X ') that karyomorphism part 15 has
The generally higher than thickness of arm 9.As modification, karyomorphism part 15 can be hemispheric.
The profile of arm 9 and the profile of karyomorphism part 15 are preferably chosen to, and make the rib of karyomorphism part 15 or exterior radial surface 16
It is basically parallel to axis X X '.For this purpose, if it is necessary, arm is carried at it has reversed bending section near end of karyomorphism part 15
Point.
Karyomorphism part 15 be suitable for it is each be accepted in a holding part 17 of the groove shape with U-shaped section, U-shaped cut
The opening in face radially refers to the axis towards wheel rim 3, in installation site of the wheel rim on wheel shaft 2, the axis and coupling device of wheel rim 3
7 and wheel shaft 2 axis X X ' overlap.Holding part 17 parallel to wheel rim 3 axis orientation and when wheel rim 3 be mounted on wheel shaft 2 on
When, holding part its towards being opening on the end of coupling device 7.Conversely, holding part 17 is to close in its opposite end
's.
Holding part 17 and karyomorphism part 15 are as much.Holding part 17 is wearing piece, is carried on the circular crown for being fixed to wheel rim 3
On gear 18.The axial length of ring gear 18 is chosen so as to be convenient for the radian of arm 9 being limited in and braking mechanism and retarder dress
The 5 related constraint of volume is put mutually in compatible scope.The diameter of ring gear 18 is suitable, so that holding part 17 is substantially and core
Shape part 15 aligns and can be received by the translational motion of wheel rim 3 when wheel rim is mounted on wheel shaft 2 on desired Angle Position
Karyomorphism part 15.
Preferably, the size of karyomorphism part 15 and holding part 17 is selected as so that is accepted in holding part 17 in karyomorphism part
There are certain intervals when middle.Arm 9 is good when the gap is convenient for the assembling of wheel and bears to deform when wheel shaft 2 is in aircraft taxi
Running.
When wheel is assembled on wheel shaft 2, the coupling between wheel rim 3 and gear 6 is easy to carry out, except wheel
The angle of rim 3, which is positioned to assure that, aligns holding part 17 with karyomorphism part 15 outside, without other complement operations.Once wheel rim 3 passes through
It is required that crimping be installed on wheel shaft 2, thus karyomorphism part 15 is placed in holding part 17.
The feature of the geometry of coupling device 7 and the feature of mechanism are selected as so that in the position of installation wheel
In, arm 9 is in prestress state.The prestress of arm 9 is negligible compared with that should clamp the active force of wheel
's.In this way, it is that each position of the wheel and wheel of each type on undercarriage defines the folder to be applied in a manner of mandatory
The form of holding force is not altered.
In operation, when driving wheel rim 3 via reducer arrangement 5 and coupling device 7 by motor 4, wheel obtains
Certain camber angle, camber angle depend on the deformation extent of wheel shaft 2.The camber angle can be highlighted by the deformation of wheel in itself.
Despite the presence of the camber angle, the prestress of arm 9 and the elastic and elongated shape of karyomorphism part 15 and holding part 17
It can ensure that the end of some arms 9 does not depart from outside holding part 17 and enduringly keeps between output gear 6 and wheel rim 3
Mechanical attachment globality.
The deformation that arm 9 is born in operation does not involve the torque transmission between gear 6 and wheel rim 3.In fact, it is put down in diameter
In face, arm 9 is minimum deformable and very big rigidity is therefore presented.
In view of the size and their manufacturing tolerance of related different mechanical parts, transferred when lacking torque, only from geometry
Impossible from the point of view of shaped angles is that all karyomorphism parts 15 are born against in their holding part 17：The only one of karyomorphism part 15 can
It bears against in its holding part 17.However, even if very big rigidity is presented in arm 9 on diametral plane, mechanical system is not infinitely rigid
And be constantly present micro-strain under the action of restraining force.In operation, these micro-strains of arm can ensure own
Karyomorphism part 15 is born against in their own holding part and the therefore all participation of arms 9 torques transmission.
Connection between wheel and coupling device 7 does not influence to dismantle the customary operation of wheel：After unscrewing, by taking turns
It is moved on axis 2 and removes wheel, this causes karyomorphism part 15 to be withdrawn into outside holding part 17.
Holding part 17 and karyomorphism part 15 are interchangeable removable wearing piece.
Claims (15)
1. the elasticity coupling between a kind of wheel in aircraft landing gear motor-driven rotating mechanism (6) coaxial with the wheel
Device, which is characterized in that the elasticity coupling device includes multiple arms (9), and the arm is suitable at the first inner radial end
Side is fixed together with the motor-driven rotating mechanism (6) and rotates and be suitable for being connected in the opposite outer radial end of arm
The wheel is connected to, the arm (9) is substantially rigid in the plane perpendicular to the pivot center of the wheel and in base
This is flexible in the direction of the plane.
2. elasticity coupling device according to claim 1, which is characterized in that the arm (9) is connected with wheel hub (8),
The wheel hub is suitable for being fixed on the motor-driven rotating mechanism (6).
3. according to the elastic coupling device described in any one in claim 1 and 2, which is characterized in that the arm (9) is suitble to use
In each holding part (17) that the wheel rim (3) for bearing against the wheel is accepted at its outer radial end.
4. elasticity coupling device according to claim 3, which is characterized in that the holding part (17) essentially has U-shaped
The groove shapes in section, U-shaped section is in one of the end of holding part opening；Also, the arm (9) has at the outer radial end
There is elongated karyomorphism part (15), the karyomorphism part is suitable for being accepted in one of described holding part (17).
5. elasticity coupling device according to claim 3, which is characterized in that the arm (9) is dimensioned, so that in institute
It states in installation site of the wheel on the aircraft landing gear, the arm is by axial tensioning.
6. elasticity coupling device according to claim 4, which is characterized in that the length of the holding part (17) is suitable for
Ensure constraint to the karyomorphism part (15), but regardless of the wheel camber angle how.
7. elasticity coupling device according to claim 3, which is characterized in that the holding part is disposed in and the wheel rim
(3) in the ring gear (18) being connected.
8. elasticity coupling device according to claim 4, which is characterized in that the holding part (17) and the karyomorphism part
(15) wear parts are moveable.
9. according to the elastic coupling device described in any one in claim 1 and 2, which is characterized in that the arm (9) is blade
Shape.
10. elasticity coupling device according to claim 9, which is characterized in that the blade is in its outer radial end ratio
Radial direction end has smaller section inside it.
11. a kind of wheel of aircraft landing gear, which is characterized in that the wheel is suitable for being connected to according to claim
The arm (9) of elastic coupling device (7) in 1 to 10 described in any one.
12. wheel according to claim 11, which is characterized in that the wheel is configured with holding part (17), described accommodating
Portion is each suitable for receiving an outer radial end of the arm (9) of the elastic coupling device.
13. wheel according to claim 12, which is characterized in that the wheel has the ring for carrying the holding part (17)
The ring gear (18) of shape.
14. a kind of aircraft landing gear, the machine of the wheel at least one wheel and including motor-driven rotating mechanism (6)
Dynamic device (4,5), which is characterized in that the aircraft landing gear is included according to any one in claim 1 to 10
Elastic coupling device.
15. a kind of aircraft, which is characterized in that the aircraft includes at least one aircraft according to claim 14
Undercarriage.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1357609 | 2013-07-31 | ||
| FR1357609A FR3009276B1 (en) | 2013-07-31 | 2013-07-31 | DEVICE FOR COUPLING A MOTORIZED WHEEL OF AN AIRCRAFT LANDING TRAIN |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104340360A CN104340360A (en) | 2015-02-11 |
| CN104340360B true CN104340360B (en) | 2018-06-01 |
Family
ID=
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5219314A (en) * | 1990-08-10 | 1993-06-15 | Caterpillar Inc. | Flexible driving transmitting coupling |
| CN101734373A (en) * | 2008-11-04 | 2010-06-16 | 梅西耶-布加蒂公司 | Wheel bar and a wheel specially adapted therefor |
| CN102107732A (en) * | 2009-12-24 | 2011-06-29 | 梅西耶-布加蒂公司 | Aircraft wheel-and-brake set fitted with rotary drive device |
| CN102795337A (en) * | 2011-05-20 | 2012-11-28 | 梅西耶-布加蒂-道提公司 | Device for rotational coupling of a crown gear to a wheel and aircraft landing gear provided with such a device |
| CN103043210A (en) * | 2011-10-14 | 2013-04-17 | 梅西耶-布加蒂-道提公司 | Connection device for a motor reduction unit of an aircraft wheel, allowing for selective drive by the motor reduction unit |
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5219314A (en) * | 1990-08-10 | 1993-06-15 | Caterpillar Inc. | Flexible driving transmitting coupling |
| CN101734373A (en) * | 2008-11-04 | 2010-06-16 | 梅西耶-布加蒂公司 | Wheel bar and a wheel specially adapted therefor |
| CN102107732A (en) * | 2009-12-24 | 2011-06-29 | 梅西耶-布加蒂公司 | Aircraft wheel-and-brake set fitted with rotary drive device |
| CN102795337A (en) * | 2011-05-20 | 2012-11-28 | 梅西耶-布加蒂-道提公司 | Device for rotational coupling of a crown gear to a wheel and aircraft landing gear provided with such a device |
| CN103043210A (en) * | 2011-10-14 | 2013-04-17 | 梅西耶-布加蒂-道提公司 | Connection device for a motor reduction unit of an aircraft wheel, allowing for selective drive by the motor reduction unit |
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