CN113928589A - Self-supporting strutting arrangement suitable for aircraft is transported all angles - Google Patents
Self-supporting strutting arrangement suitable for aircraft is transported all angles Download PDFInfo
- Publication number
- CN113928589A CN113928589A CN202111133537.1A CN202111133537A CN113928589A CN 113928589 A CN113928589 A CN 113928589A CN 202111133537 A CN202111133537 A CN 202111133537A CN 113928589 A CN113928589 A CN 113928589A
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- cylinder
- caster
- self
- supporting
- full
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/50—Handling or transporting aircraft components
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a self-supporting device suitable for airplane full-angle transportation, which comprises a supporting column (1), wherein at least two airplane wheels (5) are installed at the bottom of the supporting column, the middle part of the supporting column is hinged with the fixed end of an inclined strut (2), and the movable end of the inclined strut and the top of the supporting column are respectively provided with a connecting part for connecting an airplane body (16); the bottom of the pillar is detachably connected with one end of a connecting rod (4), the other end of the connecting rod is detachably connected with the movable end of the inclined strut through a caster device (3), and the caster device and the wheel are installed on the same plane. The invention realizes the functions of self-standing and manual transfer of the airplane supporting device and simultaneously realizes the functions of supporting height adjustment and full-angle steering.
Description
Technical Field
The invention relates to an auxiliary assembly tool for an airplane, in particular to a self-supporting device suitable for full-angle transfer of the airplane.
Background
The airplane needs a large amount of auxiliary tools to support the airplane in the processes of component assembly, general assembly, circulation among different stations and ground test. At present, the auxiliary tool does not have the transferring and steering functions, and is inconvenient for providing support for the airplane in the processes of component assembly, general assembly, circulation among different stations, putting on and off shelves and ground test.
Disclosure of Invention
The invention aims to solve the technical problem that the function of an auxiliary tool in the existing aircraft assembly is insufficient, and provides a self-supporting full-angle transfer aircraft supporting device which can provide support for the aircraft in the processes of component assembly, general assembly, circulation among different stations and ground test.
In order to solve the technical problems, the invention adopts the following technical scheme: a self-supporting device suitable for airplane full-angle transportation comprises a supporting column, wherein at least two airplane wheels are mounted at the bottom of the supporting column, the middle part of the supporting column is hinged with the fixed end of a diagonal brace, and the movable end of the diagonal brace and the top of the supporting column are respectively provided with a connecting part for connecting an airplane body; the bottom of the pillar is detachably connected with one end of a connecting rod, the other end of the connecting rod is detachably connected with the movable end of the inclined strut through a caster device, and the caster device and the airplane wheel are installed on the same plane.
According to the airplane support device, the upright post is arranged, the fixed end of the inclined support is hinged to the middle of the upright post, the movable end of the inclined support is detachably connected with the caster device, the connecting rod is detachably arranged between the caster device and the upright post, and thus the caster device and two airplane wheels arranged at the bottom of the upright post form a stable triangle, so that the airplane support device can realize the functions of self-standing and manual transfer, the airplane can be transferred among component assembly, general assembly and different stations, and the caster device and the airplane wheels can respectively adopt universal wheels in the transfer process, so that the full-angle steering in the transfer process is realized; after the connecting rod and the caster device are disassembled, the airplane body can be supported by the upright post and the inclined support.
Preferably, the caster device comprises a caster finished product, a caster connecting piece and an inclined strut mounting groove, the caster finished product and the wheel are mounted on the same plane, one end of the caster connecting piece is fixedly connected with the upper end of the caster finished product, the other end of the caster connecting piece is provided with a connecting rod interface, and the middle of the caster connecting piece is provided with the inclined strut mounting groove.
Preferably, when the inclined strut is put down, the inclined strut is put into the inclined strut mounting groove, and the inclined strut and the caster device are connected into a whole through the second quick-release pin.
Preferably, the connecting rod is articulated with the caster device through a connecting rod interface, and for convenient disassembly, the pillar is connected with the connecting rod through a first quick-release pin.
Preferably, the pillar comprises an outer cylinder, a middle cylinder and an inner cylinder which are sequentially sleeved from outside to inside, a bearing is arranged between the outer cylinder and the middle cylinder, the middle cylinder and the inner cylinder are in clearance fit, and the middle cylinder and the inner cylinder are detachably connected through a stop shaft. When the outer cylinder is connected with the machine body and the inner cylinder is connected with the machine wheel, the inner cylinder can rotate for 360 degrees around the outer cylinder along with the rotation of the machine wheel.
Preferably, a nut is mounted at the end part of the middle cylinder, a boss is arranged at the end part of the inner cavity of the outer cylinder, the middle cylinder penetrates through the boss and then is in threaded connection with the nut, and the outer diameter of the nut is slightly smaller than the inner diameter of the outer cylinder, so that the outer cylinder and the middle cylinder are fixedly connected through the nut, and therefore the outer cylinder can achieve a supporting function and can also achieve a full-angle steering function when an airplane is towed.
Preferably, the bearing is a thrust bearing, a tight ring of the thrust bearing is connected with the middle cylinder, a loose ring is connected with the outer cylinder, and a first gap is formed between the upper surface of the thrust bearing and the lower surface of the boss to prevent the middle cylinder from moving axially.
Preferably, the bottom of the outer cylinder is provided with a lower end cover, so that the outer cylinder rotates more stably relative to the outer cylinder; a guide sleeve and a lining sleeve are arranged between the middle barrel and the inner barrel, the guide sleeve is fixedly connected to the upper portion of the inner barrel through a stop pin, and the lining sleeve is fixedly connected to the lower portion of the middle barrel through the stop pin, so that the inner barrel can move up and down more stably relative to the middle barrel.
Preferably, the lower part of the middle cylinder extends out of the outer cylinder, the middle cylinder is provided with a first positioning hole, the inner cylinder is provided with at least two second positioning holes along the axial direction of the inner cylinder, and the second positioning holes are connected with the first positioning holes through stop shafts. The requirement of the airplane on different supporting heights of the undercarriage can be met by controlling the hole pitch of the second positioning hole in the inner cylinder. When the inner cylinder is supported at a common height, the stop pin is connected with the second positioning hole at the lower part of the inner cylinder and the first positioning hole on the middle cylinder; when the supporting height of the airplane is required to be raised, the inner cylinder extends outwards, and the stop pin connects the second positioning hole in the upper portion of the inner cylinder with the first positioning hole in the middle cylinder.
Preferably, a second gap is formed between the lower surface of the nut and the upper surface of the boss, so that clamping stagnation caused by friction between the nut and the boss in the steering process (the middle cylinder rotates relative to the outer cylinder) is avoided.
Compared with the prior art, the invention has the beneficial effects that:
1. the invention realizes the function diversification requirement of the airplane supporting device and saves the economic cost and the time cost;
2. the caster device and the inclined support rod and the connecting rod and the upright post are respectively connected by the quick-release pin, and when the supporting state of the device is switched to the transferring state, the additional structure (the caster device and the connecting rod) is conveniently and quickly detached;
3. the invention realizes the telescopic function and the full-angle steering function of the airplane supporting device, and has simple structure and reliable function;
4. the airplane support device is simple in structure and meets the functional requirements in the airplane assembly ground test process.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic side view of the installation of the aircraft support device according to the invention in normal use (in the supported state).
Fig. 2 is a schematic side view of the aircraft support device of the present invention in use in a transfer (transfer state).
Fig. 3 is an isometric view of a caster device.
Fig. 4 is a cross-sectional view of the strut.
Fig. 5 is a sectional view showing an extended state of the strut.
In the figure: 1-pillar, 2-diagonal bar, 3-caster device, 4-connecting rod, 5-wheel, 6-outer cylinder, 7-nut, 8-bearing, 9-middle cylinder, 10-stop pin, 11-guide sleeve, 12-inner cylinder, 13-lower end cover, 14-stop shaft, 15-lining cylinder, 16-body, 17-second quick-release pin, 31-caster finished product, 32-caster connecting piece, 33-diagonal bar installation groove, 34-connecting rod interface, 61-boss, 121-second positioning hole.
Detailed Description
The invention is further described below with reference to specific preferred embodiments, without thereby limiting the scope of protection of the invention.
For convenience of description, the relative positional relationship of the components, such as: the descriptions of the upper, lower, left, right, etc. are described with reference to the layout directions of the drawings in the specification, and do not limit the structure of the present patent.
As shown in fig. 1 to 5, one embodiment of the self-standing support device of the present invention suitable for full-angle airplane transfer comprises a pillar 1, a diagonal brace 2, a caster device 3, and a connecting rod 4.
The strut 1 comprises an outer cylinder 6, a middle cylinder 9 and an inner cylinder 12 which are sequentially sleeved from outside to inside, wherein the outer cylinder 6 is in clearance fit with the middle cylinder 9, and the middle cylinder 9 is in clearance fit with the inner cylinder 12. The upper end part of the inner cavity of the outer cylinder 6 is provided with a boss 61, the upper end of the middle cylinder 9 penetrates through the boss 61, the upper end part of the middle cylinder 9 is provided with threads, and the nut 7 is installed through the threads. The outer diameter of the nut 7 is slightly smaller than the inner diameter of the outer cylinder 6, so that the nut 7 limits one end of the outer cylinder 6. Below the boss 61, outer cylinder 6 with install thrust bearing 8 between the well section of thick bamboo 9, just thrust bearing 8's tight circle with well section of thick bamboo 9 is connected, loose circle with outer cylinder 6 is connected, thrust bearing 8's upper surface with be equipped with first clearance between the lower surface of boss 61. A second gap is formed between the lower surface of the nut 7 and the upper surface of the boss 61, so that clamping stagnation caused by friction between the nut 7 and the boss 61 in the steering process is avoided.
The bottom of the outer cylinder 6 is provided with a lower end cover 13, and the outer cylinder 6 and the lower end cover 13 are connected into a whole by a stop pin 10. A guide sleeve 11 and a lining tube 15 are arranged between the middle tube 9 and the inner tube 12, the guide sleeve 11 is fixedly connected to the upper part of the inner tube 12 through a stop pin 10, and the lining tube 15 is fixedly connected to the lower part of the middle tube 9 through the stop pin 10. When the outer cylinder 6 is connected with the machine body 16, and the inner cylinder 12 is connected with the wheel 5, the inner cylinder 12 can rotate 360 degrees around the outer cylinder 6 along with the rotation of the wheel 5.
The lower part of the middle cylinder 9 extends out of the outer cylinder 6, a first positioning hole is formed in the middle cylinder 9, at least two second positioning holes 121 are formed in the inner cylinder 12 along the axial direction of the inner cylinder, at least one of the second positioning holes 121 is aligned with one of the first positioning holes, and a stop shaft 14 penetrates through the second positioning hole and the first positioning hole to realize detachable connection of the middle cylinder 9 and the inner cylinder 12.
The caster device 3 comprises a caster finished product 31 with a braking function, a caster connecting piece 32 and an inclined strut mounting groove 33, one end of the caster connecting piece 32 is fixedly connected with the upper end of the caster finished product 31, the other end of the caster connecting piece 32 is provided with a connecting rod interface 34, and the middle of the caster connecting piece 32 is provided with the inclined strut mounting groove 33.
At least two wheels 5 are mounted at the bottom of an inner cylinder 12 of the strut 1, the middle of the strut 1 is hinged to the fixed end of the inclined strut 2, and the movable end of the inclined strut 2 and the top of the strut 1 are respectively provided with a connecting part for connecting a machine body 16. The bottom of the inner cylinder 12 is detachably connected with one end of a connecting rod 4 through a first quick-release pin, the other end of the connecting rod 4 is detachably connected with a connecting rod interface 34 of the movable end of the inclined strut 2 through a second quick-release pin 17, and the caster finished product 31 and the wheel 5 are installed on the same plane.
As shown in figure 1, when the aircraft supporting device is used for supporting an aircraft body 16, the first quick-release pin and the second quick-release pin are pulled off, the caster wheel devices 3 and the connecting rod 4 are detached, the aircraft body 16 is connected by using the connecting parts of the upright posts 1 and the inclined supports 2, and the aircraft supporting device and the aircraft towing device can be supported together with the other two main supporting devices.
As shown in fig. 2, in order to realize the vertical placement function of the present invention, the connecting portion of the diagonal brace 2 is lowered and connected to the caster device 3 as a support bar, and the connecting rod 4 connects the pillar 1 and the diagonal brace 2 to form a stable triangular structure, so that the center of gravity of the aircraft support device of the present invention falls within the triangular structure, thereby stably standing by itself and realizing the transportation function while keeping the movement stable.
As shown in fig. 5, when the supporting height of the aircraft supporting device of the present invention needs to be adjusted, the stop shaft 14 can be pulled out to make the second positioning hole 121 of the inner cylinder 12 move upwards align with the first positioning hole of the middle cylinder 9, and then the stop shaft 14 is inserted.
The above description is only a specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and those skilled in the art can make many possible variations and modifications to the technical solution of the present invention or modify equivalent embodiments using the technical content disclosed above without departing from the technical solution of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention should fall within the protection scope of the technical scheme of the present invention, unless the technical spirit of the present invention departs from the content of the technical scheme of the present invention.
Claims (9)
1. A self-supporting device suitable for airplane full-angle transportation comprises a supporting column (1), wherein at least two wheels (5) are mounted at the bottom of the supporting column, the middle part of the supporting column is hinged with the fixed end of a diagonal brace (2), and the movable end of the diagonal brace and the top of the supporting column are respectively provided with a connecting part for connecting an airplane body (16); the bottom of the pillar is detachably connected with one end of a connecting rod (4), the other end of the connecting rod is detachably connected with the movable end of the inclined strut through a caster device (3), and the caster device and the wheel are installed on the same plane.
2. A self-supporting support device suitable for aircraft full-angle transportation according to claim 1, wherein the caster device comprises a caster finished product (31), a caster connecting member (32) and a diagonal strut mounting groove (33), the caster finished product and the wheel are mounted on the same plane, one end of the caster connecting member is fixedly connected with the upper end of the caster finished product, the other end of the caster connecting member is provided with a connecting rod interface (34), and the middle part of the caster connecting member is provided with the diagonal strut mounting groove.
3. A self-supporting support device suitable for use in full-angle airplane transfer according to claim 1, wherein said struts are connected to said connecting rods by first quick release pins and said diagonal struts are connected to said caster devices by second quick release pins.
4. The self-supporting device suitable for aircraft full-angle transportation of claim 1, wherein the pillar comprises an outer cylinder (6), a middle cylinder (9) and an inner cylinder (12) which are sequentially sleeved from outside to inside, a bearing (8) is installed between the outer cylinder and the middle cylinder, the middle cylinder and the inner cylinder are in clearance fit, the middle cylinder and the inner cylinder are detachably connected through a stop shaft (14), the outer cylinder is connected with the machine body, the inner cylinder is connected with the wheel, and the inner cylinder rotates around the outer cylinder for 360 degrees along with the rotation of the wheel.
5. The self-supporting device suitable for aircraft full-angle transportation of claim 4, wherein a nut (7) is mounted at the end of the middle cylinder, a boss is arranged at the end of the inner cavity of the outer cylinder, the middle cylinder is in threaded connection with the nut after passing through the boss, and the outer diameter of the nut is slightly smaller than the inner diameter of the outer cylinder.
6. A self-supporting support device suitable for aircraft full angle of transport according to claim 5, wherein the bearing is a thrust bearing, and wherein the tight loop of the thrust bearing is connected with the middle cylinder, the loose loop is connected with the outer cylinder, and a first gap is provided between the upper surface of the thrust bearing and the lower surface of the boss.
7. A self-standing support device suitable for aircraft full angle transportation according to claim 4, wherein a lower end cover (13) is installed at the bottom of the outer cylinder, a guide sleeve (11) and a lining cylinder (15) are arranged between the middle cylinder and the inner cylinder, the guide sleeve is fixedly connected to the upper part of the inner cylinder through a stop pin (10), and the lining cylinder is fixedly connected to the lower part of the middle cylinder through the stop pin (10).
8. A self-standing support device adapted for full angular transfer of aircraft according to claim 4, wherein the lower portion of the middle tube extends out of the outer tube, and the middle tube is provided with a first positioning hole, and the inner tube is provided with at least two second positioning holes along the axial direction thereof, and the second positioning holes are connected with the first positioning holes through stop shafts (14).
9. A self-standing support apparatus adapted for full angular transfer of an aircraft according to claim 5, wherein a second gap is provided between a lower surface of the nut and an upper surface of the boss.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111133537.1A CN113928589B (en) | 2021-09-27 | 2021-09-27 | Self-supporting support device suitable for full-angle transportation of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111133537.1A CN113928589B (en) | 2021-09-27 | 2021-09-27 | Self-supporting support device suitable for full-angle transportation of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113928589A true CN113928589A (en) | 2022-01-14 |
| CN113928589B CN113928589B (en) | 2023-06-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111133537.1A Active CN113928589B (en) | 2021-09-27 | 2021-09-27 | Self-supporting support device suitable for full-angle transportation of aircraft |
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| CN (1) | CN113928589B (en) |
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| US20200339250A1 (en) * | 2019-04-23 | 2020-10-29 | Goodrich Corporation | Integral bracket manifold for landing gear assemblies |
| CN112874762A (en) * | 2021-03-02 | 2021-06-01 | 中航飞机起落架有限责任公司 | Stay bar assembly of undercarriage and assembling method thereof |
| CN113071658A (en) * | 2021-04-15 | 2021-07-06 | 北京北摩高科摩擦材料股份有限公司 | Aircraft nose landing gear |
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2021
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2848528A1 (en) * | 2002-12-12 | 2004-06-18 | Alkan Sa | Method for mounting landing gear on aircraft comprises surrounding gear by two half porticos having rolling beam in upper guide rails, beams guiding displacement of crab and falls with cables fixed to gear rear and front crosspiece |
| US20060060700A1 (en) * | 2004-09-10 | 2006-03-23 | Anderton John M | Landing gear support |
| CN201272482Y (en) * | 2008-09-18 | 2009-07-15 | 朱江 | Special ox cart for dismounting airplane wheel |
| US20130056584A1 (en) * | 2011-09-02 | 2013-03-07 | Airbus Operations Gmbh | Method for mounting an aircraft component and aircraft assembly |
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| US20170106972A1 (en) * | 2015-10-19 | 2017-04-20 | Mitsubishi Aircraft Corporation | Dolly for handling landing gear of aircraft, and method for attaching and detaching landing gear using the same |
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|---|---|
| CN113928589B (en) | 2023-06-06 |
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