CN111056001A - Combined aircraft wheel - Google Patents
Combined aircraft wheel Download PDFInfo
- Publication number
- CN111056001A CN111056001A CN201911386611.3A CN201911386611A CN111056001A CN 111056001 A CN111056001 A CN 111056001A CN 201911386611 A CN201911386611 A CN 201911386611A CN 111056001 A CN111056001 A CN 111056001A
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- CN
- China
- Prior art keywords
- wheel
- main
- shaft
- aircraft wheel
- aircraft
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C2025/345—Multi-wheel bogies having one or more steering axes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a combined aircraft wheel, which comprises a main girder shaft of the aircraft wheel, wherein one end of the main girder shaft of the aircraft wheel is vertically provided with a wheel shaft sleeve, an inner cavity of the wheel shaft sleeve is embedded with a main axle of the aircraft wheel, a sealing backing ring is embedded between the main axle of the aircraft wheel and the wheel shaft sleeve, two ends of the sealing backing ring are embedded with felt gaskets, two ends of the main axle of the aircraft wheel are sleeved with supporting bearings, an outer axle sleeve of each supporting bearing is sleeved with a first aircraft wheel, the other end of the main girder shaft of the aircraft wheel is provided with a second aircraft wheel, the middle parts of the outer edges of the first aircraft wheel and the second aircraft wheel are embedded with an aircraft wheel end cover, the middle part of the main girder shaft of the aircraft wheel is hinged with a main telescopic shaft, and the middle part of the. According to the invention, a novel structure is adopted, the two-stage folding aircraft wheel is adopted, the rotation of a half of the wheel assembly is realized, the connecting rod crank assembly is adopted, the later maintenance convenience of the whole equipment can be ensured, and the space occupation amount is reduced.
Description
Technical Field
The invention relates to the field of aircraft equipment wheels, in particular to a combined aircraft wheel.
Background
The landing gear is divided into an inextensible landing gear and a retractable landing gear according to the retractable form, the inextensible landing gear can generate great resistance in the flight process to reduce the flight performance, the aircraft flight speed exceeds 250km/h, the retractable landing gear is adopted, the aircraft is stored in the aircraft body or the wings in order to reduce the aerodynamic resistance in the flight process, and the lower surfaces of the wings and the opening of the aircraft body are sealed pneumatically by closing the doors of the landing gear.
Most of the existing aircraft wheels are folded and unfolded in a traditional integrated mode, the space occupied behind the wheel cabins of the aircraft wheels is large, and meanwhile, the speed in the folding and unfolding process is low, so that the sailing efficiency is influenced.
Disclosure of Invention
The invention aims to solve the defects in the prior art and provides a combined aircraft wheel.
In order to achieve the purpose, the invention adopts the following technical scheme: a combined aircraft wheel comprises a wheel main truss shaft, wherein one end of the wheel main truss shaft is vertically provided with a wheel shaft sleeve, an inner cavity of the wheel shaft sleeve is embedded with a wheel main shaft, a sealing backing ring is embedded between the wheel main shaft and the wheel shaft sleeve, two ends of the sealing backing ring are embedded with felt gaskets, two ends of the wheel main shaft are sleeved with supporting bearings, an outer shaft sleeve of each supporting bearing is sleeved with a first wheel, the other end of the wheel main truss shaft is provided with a second wheel, wheel end covers are embedded in the middle parts of the outer edges of the first wheel and the second wheel, a main telescopic shaft is hinged in the middle of the middle part of the side surface of the main telescopic shaft, a main shaft end cover is arranged at the top of the main telescopic shaft, an auxiliary hydraulic cylinder is hinged at the top of the main telescopic shaft, and an auxiliary telescopic rod is embedded in the inner cavity of the auxiliary hydraulic cylinder, the articulated position of main telescopic shaft and auxiliary hydraulic cylinder articulates simultaneously has the load pull rod, the end of load pull rod articulates there is the power connecting rod, the auxiliary telescopic link is kept away from that the one end of main telescopic shaft articulates there is middle part support crank, and the middle part support crank other end articulates the middle part surface at main telescopic shaft, the articulated position gomphosis of middle part support crank and auxiliary telescopic link has connecting pin axle, connecting pin axle has cup jointed passive pull rod, the equal threaded connection in both ends of wheel owner purlin axle has purlin axle end cover.
As a further description of the above technical solution:
the passive pull rod, the power connecting rod and the middle supporting crank are all triangular hollow structures, the middle hollow regular triangle of the passive pull rod, the power connecting rod and the middle supporting crank is provided with a solid connecting part in an extending mode, and the corner of the triangle is provided with a solid connecting part in an extending mode.
As a further description of the above technical solution:
one ends of the passive pull rod, the auxiliary telescopic rod and the middle support crank are connected through pin shafts, and the other ends of the passive pull rod, the auxiliary telescopic rod and the middle support crank are respectively in pin joint with the surfaces of the wheel main truss shaft and the wheel main telescopic shaft.
As a further description of the above technical solution:
the maximum adjustable angle of the main servo motor is one hundred degrees, the main servo motor is decelerated through a worm and gear reducer, and the maximum torque output by the reducer is not lower than fifteen kilonewtons.
As a further description of the above technical solution:
the thickness of the felt gasket is larger than that of the sealing gasket ring, the felt gasket and the sealing gasket ring are embedded between the wheel shaft sleeve and the wheel main shaft, and after the installation is completed, the thicknesses of the felt gasket and the sealing gasket ring are consistent.
As a further description of the above technical solution:
the sealing gasket ring and the main shaft of the airplane wheel are in transition connection, and the sealing gasket ring and the sleeve of the airplane wheel are in clearance connection.
As a further description of the above technical solution:
the maximum moving stroke of the main telescopic shaft is 1800 mm.
As a further description of the above technical solution:
the maximum moving stroke of the auxiliary telescopic rod is 1750 mm.
According to the invention, a novel structure is used, the aircraft wheels are folded in two stages, the servo motor is arranged in the middle of the aircraft wheels, and the moment is amplified and decelerated through the speed reducer, so that half of the aircraft wheel assembly is rotated, meanwhile, the connecting rod crank assembly is adopted, the later maintenance convenience of the whole equipment can be ensured, the worm and gear speed reducer can realize stable rotation performance, larger moment is output, the total weight of the whole aircraft wheels is ensured not to be improved, the occupied space after folding and unfolding is greatly reduced, the two stages are folded and unfolded simultaneously, and the folding and unfolding speed of the whole aircraft wheels is improved.
Drawings
Fig. 1 is a main structural diagram of a combined aircraft wheel according to the present invention;
fig. 2 is a front view of a combined aircraft wheel according to the invention;
fig. 3 is a wheel structure diagram of a combined aircraft wheel according to the invention;
fig. 4 is a partial enlarged view of fig. 3-a.
Illustration of the drawings:
1. a wheel main truss shaft; 2. a first wheel; 3. a truss shaft end cap; 4. an airplane wheel end cover; 5. a wheel axle sleeve; 6. a main servo motor; 7. a main telescopic shaft; 8. a passive tie rod; 9. connecting a pin shaft; 10. a second wheel; 11. a power link; 12. a bearing pull rod; 13. a main shaft end cover; 14. an auxiliary telescopic rod; 15. a middle support crank; 16. a support bearing; 17. a main shaft of the airplane wheel; 18. a felt washer; 19. a sealing gasket ring; 20. and an auxiliary hydraulic cylinder.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention; the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; furthermore, unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, as they may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1-4, a combined aircraft wheel comprises a wheel main truss shaft 1, one end of the wheel main truss shaft 1 is vertically provided with a wheel shaft sleeve 5, an inner cavity of the wheel shaft sleeve 5 is embedded with a wheel main shaft 17, a sealing backing ring 19 is embedded between the wheel main shaft 17 and the wheel shaft sleeve 5, two ends of the sealing backing ring 19 are embedded with felt gaskets 18, two ends of the wheel main shaft 17 are sleeved with supporting bearings 16, an outer shaft sleeve of the supporting bearings 16 is sleeved with a first wheel 2, the other end of the wheel main truss shaft 1 is provided with a second wheel 10, the outer edge middle parts of the first wheel 2 and the second wheel 10 are embedded with wheel end covers 4, the middle part of the wheel main truss shaft 1 is hinged with a main telescopic shaft 7, the side surface middle part of the main telescopic shaft 7 is embedded with a main servo motor 6, the top of the main telescopic shaft 7 is provided with a main shaft end cover 13, the top of the main telescopic shaft 7 is hinged with an auxiliary hydraulic cylinder 20, and the inner cavity of the, main telescopic shaft 7 and the articulated position of auxiliary hydraulic cylinder 20 articulate simultaneously has load pull rod 12, the end of load pull rod 12 articulates there is power connecting rod 11, auxiliary telescopic rod 14 keeps away from that the one end of main telescopic shaft 7 articulates there is middle part support crank 15, and the middle part support crank 15 other end articulates the middle part surface at main telescopic shaft 7, the articulated position gomphosis of middle part support crank 15 and auxiliary telescopic rod 14 has connecting pin axle 9, connecting pin axle 9 has cup jointed passive pull rod 8, the equal threaded connection in both ends of wheel owner purlin axle 1 has purlin axle end cover 3.
The driven pull rod 8, the power connecting rod 11 and the middle supporting crank 15 are all triangular hollow structures, the middle parts of the driven pull rod 8, the power connecting rod 11 and the middle supporting crank 15 are hollow regular triangles, the corners of the triangles are all extended with solid connecting parts, on the premise of ensuring that the whole force transmission structure can realize better torque transmission, the whole weight of the equipment is reduced as much as possible, one ends of the driven pull rod 8, the auxiliary telescopic rod 14 and the middle supporting crank 15 are connected by adopting pin shafts, the other ends of the driven pull rod 8, the auxiliary telescopic rod 14 and the middle supporting crank 15 are respectively connected to the surfaces of the wheel main truss shaft 1 and the main telescopic shaft 7 in a pin joint mode, the mutual interference of the connecting structures is avoided, meanwhile, the self-use movement after the connecting rod is ensured, the maximum adjustable angle of the main servo motor 6 is one hundred degrees, and the main servo motor 6 is decelerated through a worm gear, the maximum torque output by the speed reducer is not lower than fifteen kilonewtons, the full extraction capacity of the wheel assembly of the first wheel 2 is guaranteed, the thickness of the felt gasket 18 is larger than that of the sealing gasket ring 19, the felt gasket 18 and the sealing gasket ring 19 are embedded between the wheel shaft sleeve 5 and the wheel main shaft 17, after installation is completed, the felt gasket 18 and the sealing gasket ring 19 are consistent in thickness, the full lubrication of the whole wheel in use is guaranteed, meanwhile, interference of the external environment is avoided, transition connection is adopted between the sealing gasket ring 19 and the wheel main shaft 17, gap connection is adopted between the sealing gasket ring 19 and the wheel shaft sleeve 5, the full operation and sealing of the whole device are guaranteed, the maximum moving stroke of the main telescopic shaft 7 is 1800mm, the maximum moving stroke of the auxiliary telescopic rod 14 is 1750mm, and the connecting rod mechanism is guaranteed to move.
The working principle is as follows: when the aircraft wheel is used, firstly, the equipment is completely assembled, then the wheel component is installed on a control main body of the aircraft through a power connecting rod 11, when the aircraft wheel is folded, the power connecting rod 11 rotates anticlockwise to drive a bearing pull rod 12 and an auxiliary hydraulic cylinder 20 to rotate, so that an auxiliary telescopic rod 14 is driven, a connecting pin shaft 9 at the connecting position of a middle supporting crank 15 and a driven pull rod 8 moves upwards to drive a second aircraft wheel 10 to fold upwards, then a main servo motor 6 is controlled to rotate through an electric control component to drive a first aircraft wheel 2 arranged at one end of a main girder shaft 1 of the aircraft wheel to move upwards, so that the first aircraft wheel 2 and a second aircraft wheel 10 are respectively folded, the space occupation of the whole undercarriage component is reduced, when the undercarriage is put down, the whole step runs reversely, when the undercarriage is touched, the first aircraft wheel 2 and the second aircraft wheel 10 fix an aircraft wheel main shaft 17 through an axle sleeve 5 fixed at two ends of the main girder shaft 1 of the aircraft wheel, meanwhile, the felt washer 18 and the sealing washer 19 have better lubrication on the main shaft 17 of the airplane wheel.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes, modifications, equivalents, and improvements may be made without departing from the spirit and scope of the invention.
Claims (8)
1. The utility model provides a combined aircraft wheel, includes main purlin axle (1) of wheel, its characterized in that, main purlin axle (1) one end of wheel is equipped with wheel axle sleeve (5) perpendicularly, the inner chamber gomphosis of wheel axle sleeve (5) has wheel main shaft (17), the gomphosis has sealed backing ring (19) between wheel main shaft (17) and wheel axle sleeve (5), the both ends gomphosis of sealed backing ring (19) has felt packing ring (18), support bearing (16) have been cup jointed at the both ends of wheel main shaft (17), the outer axle sleeve of support bearing (16) has cup jointed first wheel (2), the other end of main purlin axle (1) of wheel is equipped with second wheel (10), the outer fringe middle part gomphosis of first wheel (2) and second wheel (10) has wheel end cover (4), the middle part of main wheel purlin axle (1) articulates there is main telescopic shaft (7), the side surface middle part gomphosis of main telescopic shaft (7) has main servo motor (6), the top of main telescopic shaft (7) is equipped with main shaft end cover (13), the top of main telescopic shaft (7) articulates there is auxiliary hydraulic cylinder (20), the inner chamber gomphosis of auxiliary hydraulic cylinder (20) has auxiliary telescopic link (14), main telescopic shaft (7) and auxiliary hydraulic cylinder (20) articulated position articulates there is load pull rod (12) simultaneously, the end of load pull rod (12) articulates there is power connecting rod (11), the one end that auxiliary telescopic link (14) kept away from main telescopic shaft (7) articulates there is middle part support crank (15), and the middle part support crank (15) other end articulates the middle part surface of main telescopic shaft (7), the articulated position gomphosis of middle part support crank (15) and auxiliary telescopic link (14) has connecting pin axle (9), connecting pin axle (9) have cup jointed passive pull rod (8), both ends of the main truss shaft (1) of the airplane wheel are in threaded connection with truss shaft end covers (3).
2. The combined type aircraft wheel according to claim 1, characterized in that the passive tie rod (8), the power connecting rod (11) and the middle supporting crank (15) are all triangular hollow structures, and the passive tie rod (8), the power connecting rod (11) and the middle supporting crank (15) are respectively provided with a regular triangle in the middle hollow, and the corners of the triangle are extended with solid connecting parts.
3. A modular aircraft wheel according to claim 1, characterised in that one end of the passive tie rod (8), the auxiliary telescopic rod (14) and the middle support crank (15) are connected by a pin, and the other end of the passive tie rod (8), the auxiliary telescopic rod (14) and the middle support crank (15) are respectively pinned to the surface of the wheel main truss shaft (1) and the main telescopic shaft (7).
4. A modular aircraft wheel according to claim 1, characterised in that the maximum adjustable angle of the main servo motor (6) is one hundred degrees and the main servo motor (6) is decelerated by a worm gear reducer outputting a maximum torque not lower than fifteen kilo newtons.
5. A combined aircraft wheel according to claim 1, characterised in that the felt washer (18) has a thickness greater than the thickness of the sealing grommet (19), and the felt washer (18) and the sealing grommet (19) are fitted between the wheel axle sleeve (5) and the wheel main shaft (17), the felt washer (18) and the sealing grommet (19) having a uniform thickness after the mounting is completed.
6. A modular aircraft wheel according to claim 1, characterised in that a transition connection is used between the sealing grommet (19) and the wheel spindle (17), and a clearance connection is used between the sealing grommet (19) and the wheel hub sleeve (5).
7. A modular aircraft wheel according to claim 1, characterised in that the maximum travel of the main telescopic shaft (7) is 1800 mm.
8. A modular aircraft wheel according to claim 1, characterised in that the maximum travel of the auxiliary telescopic rod (14) is 1750 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911386611.3A CN111056001A (en) | 2019-12-29 | 2019-12-29 | Combined aircraft wheel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911386611.3A CN111056001A (en) | 2019-12-29 | 2019-12-29 | Combined aircraft wheel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111056001A true CN111056001A (en) | 2020-04-24 |
Family
ID=70304436
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911386611.3A Withdrawn CN111056001A (en) | 2019-12-29 | 2019-12-29 | Combined aircraft wheel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111056001A (en) |
-
2019
- 2019-12-29 CN CN201911386611.3A patent/CN111056001A/en not_active Withdrawn
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20200424 |