CN108974390B - Plane horizontal wing test bracket - Google Patents
Plane horizontal wing test bracket Download PDFInfo
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- CN108974390B CN108974390B CN201810963270.0A CN201810963270A CN108974390B CN 108974390 B CN108974390 B CN 108974390B CN 201810963270 A CN201810963270 A CN 201810963270A CN 108974390 B CN108974390 B CN 108974390B
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- supporting plate
- lifting
- wing
- rod
- horizontal wing
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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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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Handcart (AREA)
Abstract
The invention discloses an aircraft horizontal wing test bracket which comprises a lifting mechanism, a driving mechanism, a bracket mechanism and a moving mechanism, wherein the lifting mechanism is positioned above the moving mechanism, the bracket mechanism is positioned above the lifting mechanism, and the driving mechanism is arranged on the lifting mechanism and used for driving the bracket mechanism. The invention successfully solves the problems of large wing span, large volume, heavy weight, inconvenience and flexibility in movement, low fine adjustment precision of the crane lifting height and the like in the wing installation process, ensures the installation angle for restoring the wing installation, and effectively solves the problems of up-and-down fine adjustment in wing lifting and prevention of structural and functional damage of a fuselage or a wing caused by collision of the wing with the fuselage due to inertia.
Description
Technical Field
The invention relates to a horizontal wing test bracket of an airplane, and belongs to the technical field of airplane wing installation and debugging equipment.
Background
The wing is used as one of important parts in the disassembly process of the airplane, is connected by adopting a multi-stage web plate, a cross beam and a skin, has upper and lower chord horizontal supports, purlins, braces, pull rods and other accessory supports, and is interpenetrated with various hydraulic and electric action equipment. When the wings are disassembled and reinstalled, the wings have the characteristics of large span, large volume and heavy weight, so that how to ensure correct wing erection angles and wing dihedral angles when the wings are hoisted becomes important technical indexes and efficiency indexes for reinstalling and installing the wings.
The existing wing installation method is that multiple persons are adopted to pull from four directions to prevent the wings from colliding with a fuselage, then connecting parts of all the wings and the fuselage are dismantled, and the wings are installed by a method of crane lifting and manual fine adjustment. This method requires a lot of manpower input due to the removal of a large number of parts and the heavy weight of the wing during the pulling and fine adjustment, and cannot accurately ensure the angle required for installation, so that the efficiency and quality are not satisfactory.
Disclosure of Invention
Aiming at the defects, the invention provides a horizontal wing test bracket of an airplane.
The invention is realized by the following technical scheme: the utility model provides an experimental bracket of aircraft horizontal wing, includes elevating system, actuating mechanism, bracket mechanism and moving mechanism, elevating system is located moving mechanism's top, bracket mechanism is located elevating system's top, actuating mechanism sets up on elevating system for drive bracket mechanism, its characterized in that: the lifting mechanism comprises a supporting plate, a main supporting seat, a main supporting rod, an auxiliary connecting seat, an auxiliary supporting rod, a lifting supporting seat, a lifting connecting seat, a lifting rod, a walking motor, a gear and a rack, wherein the main supporting rod is movably connected with the supporting plate through the main supporting seat; the bracket mechanism comprises a supporting plate, a connecting rod and a spring, the supporting plate is movably connected to the upper end of the main support rod, the connecting rod is fixed to one side of the supporting plate, one end of the spring is connected with the supporting plate, and the other end of the spring is connected with the main support rod; the driving mechanism comprises a driving motor, a driving wheel and a traction rope, the driving motor is fixed on the main support rod, the driving wheel is arranged at the power output end of the driving motor, one end of the traction rope is fixedly connected with the driving wheel, and the other end of the traction rope is fixedly connected with the connecting rod; the moving mechanism comprises a cab, a steering wheel and moving wheels, the cab is arranged above the supporting plate, the moving wheels are arranged below the supporting plate, and the square discs are arranged in the cab and used for controlling the moving wheels.
The electric bicycle further comprises a center console, wherein the center console is arranged in the cab and is respectively used for controlling the walking motor and the driving motor.
The upper plane of the supporting plate is in the shape of a downward sunken arc, and a cushion block is arranged on the supporting plate.
The auxiliary connecting seat is positioned above the lifting connecting seat.
The connecting points of the springs and the supporting plate and the connecting rods are respectively positioned on two sides of the supporting plate.
And a sliding block is fixed on the walking motor and is movably connected with the supporting plate.
The bottom of slider is provided with T type arch, be provided with on the backup pad with T type protruding T type recess that matches.
The diameter of the drive wheel is much larger than the diameter of the connecting rod.
The invention has the advantages that the walking motor is driven by the central control console, moves in the direction away from the cab, continuously lifts the main support rod by the auxiliary support rod, and stops driving the walking motor when the supporting plate is contacted with the wing; through well accuse platform drive driving motor, because the shrink elasticity of spring is great, it can pull layer board counter-clockwise movement, and the diameter of drive wheel is far greater than the diameter of connecting rod, thereby the fine setting of layer board is realized to the accessible drive wheel, guarantee the accurate butt joint of wing and aircraft fuselage, the problem of not high grade because wing span is big in the wing installation process has been successfully solved to inconvenient nimble removal, crane hoisting height fine setting precision is not high, the erection angle of wing reinstallation has been guaranteed, the problem of the wing structural and functional damage is caused to the fuselage because of inertia clash to the wing about when effectively having solved wing hoist and mount and having prevented the wing.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic view of a connection structure of the driving mechanism and the carriage mechanism of the present invention.
Fig. 3 is a schematic structural diagram of the driving mechanism of the present invention.
Fig. 4 is a schematic structural diagram of the lifting mechanism of the present invention.
Fig. 5 is a schematic structural view of the walking motor and the supporting plate of the present invention.
FIG. 6 is a schematic structural diagram of a moving mechanism according to the present invention.
Fig. 7 is a schematic structural diagram of the pallet of the present invention.
In the figure, 1, a lifting mechanism, 2, a driving mechanism, 3, a bracket mechanism, 4, a moving mechanism, 5, a supporting plate, 6, a main supporting seat, 7, a main supporting rod, 8, a secondary connecting seat, 9, a secondary supporting rod, 10, a lifting supporting seat, 11, a lifting connecting seat, 12, a lifting rod, 13, a traveling motor, 14, a gear, 15, a rack, 16, a supporting plate, 17, a connecting rod, 18, a spring, 19, a driving motor, 20, a driving wheel, 21, a traction rope, 22, a cab, 23, a steering wheel, 24, a moving wheel, 25, a central console, 26, a cushion block, 27, a sliding block, 28, a T-shaped bulge, 29, a T-shaped groove, 30 and a wing.
Detailed Description
The invention is realized by the following technical scheme:
the utility model provides an experimental bracket of aircraft horizontal wing, includes elevating system 1, actuating mechanism 2, bracket mechanism 3 and moving mechanism 4, elevating system 1 is located moving mechanism 4's top, bracket mechanism 3 is located elevating system 1's top, actuating mechanism 2 sets up on elevating system 1 for drive bracket mechanism 3, its characterized in that: the lifting mechanism 1 comprises a supporting plate 5, a main supporting seat 6, a main supporting rod 7, an auxiliary connecting seat 8, an auxiliary supporting rod 9, a lifting supporting seat 10, a lifting connecting seat 11, a lifting rod 12, a walking motor 13, a gear 14 and a rack 15, wherein the main supporting rod 7 is movably connected with the supporting plate 5 through the main supporting seat 6, the lifting rod 12 is movably connected with the supporting plate 5 through a lifting supporting seat 10, the lifting rod 12 is movably connected with the main supporting rod 7 through the lifting connecting seat 11, the walking motor 13 is arranged at the lower end of the auxiliary supporting rod 9, the gear 14 is arranged at the power output end of the walking motor 13, the rack 15 is fixed on the supporting plate 5, and the gear 14 is meshed with the rack 15; the bracket mechanism 3 comprises a supporting plate 16, a connecting rod 17 and a spring 18, wherein the supporting plate 16 is movably connected to the upper end of the main supporting rod 7, the connecting rod 17 is fixed on one side of the supporting plate 16, one end of the spring 18 is connected with the supporting plate 16, and the other end of the spring 18 is connected with the main supporting rod 7; the driving mechanism 2 comprises a driving motor 19, a driving wheel 20 and a traction rope 21, the driving motor 19 is fixed on the main support rod 7, the driving wheel 20 is arranged at the power output end of the driving motor 19, one end of the traction rope 21 is fixedly connected with the driving wheel 20, and the other end of the traction rope 21 is fixedly connected with the connecting rod 17; the moving mechanism 4 comprises a cab 22, a steering wheel 23 and moving wheels 24, the cab 22 is arranged above the supporting plate 5, the moving wheels 24 are arranged below the supporting plate 5, and the square disc 23 is arranged in the cab and used for controlling the moving wheels 24.
The electric vehicle further comprises a center console 25, wherein the center console 25 is arranged in the cab 22 and is respectively used for controlling the walking motor 13 and the driving motor 19.
The upper plane of the supporting plate 16 is a downward-concave arc shape, and a cushion block 26 is arranged on the supporting plate 16.
The sub-connecting base 8 is positioned above the lifting connecting base 11.
The connection point of the spring 18 to the support plate 16 and the connecting rod 17 are located on both sides of the support plate 16.
A sliding block 27 is fixed on the walking motor 12, and the sliding block 27 is movably connected with the supporting plate 5.
The bottom end of the sliding block 27 is provided with a T-shaped bulge 28, and the supporting plate 5 is provided with a T-shaped groove 29 matched with the T-shaped bulge 28.
The diameter of the driving wheel 20 is much larger than the diameter of the connecting rod 17.
The working principle is as follows: the test carriage is moved to the bottom of the airplane wing 30 by driving the moving wheel 24 via the steering wheel 23, and the test carriage is stopped by fixing the moving wheel 24 via the brake. Then, the walking motor 13 is driven through the central console 25, the walking motor 13 moves in the direction away from the cab, the main supporting rod 7 is continuously lifted through the auxiliary supporting rod 10, and the driving of the walking motor 13 is stopped when the supporting plate 16 is in contact with the wing 30; the driving motor 19 is driven by the central control console 25, the spring 18 has larger contraction elasticity and can pull the supporting plate 16 to move anticlockwise, and the diameter of the driving wheel 20 is far larger than that of the connecting rod 17, so that fine adjustment of the supporting plate can be realized through the driving wheel 20, accurate butt joint of the wing and the airplane body is ensured, the problems of large wing span, large size, large weight, inconvenience in flexible movement, low fine adjustment precision of the crane lifting height, and the like in the wing installation process are successfully solved, the installation angle for restoring installation of the wing is ensured, and the problems of up-and-down fine adjustment during wing lifting and structural and functional damage of the airplane body or the wing due to inertial collision of the wing are effectively solved.
It will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in the embodiments described above without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims.
Claims (8)
1. The utility model provides an experimental bracket of aircraft horizontal wing, includes elevating system, actuating mechanism, bracket mechanism and moving mechanism, elevating system is located moving mechanism's top, bracket mechanism is located elevating system's top, actuating mechanism sets up on elevating system for drive bracket mechanism, its characterized in that: the lifting mechanism comprises a supporting plate, a main supporting seat, a main supporting rod, an auxiliary connecting seat, an auxiliary supporting rod, a lifting supporting seat, a lifting connecting seat, a lifting rod, a walking motor, a gear and a rack, wherein the main supporting rod is movably connected with the supporting plate through the main supporting seat; the bracket mechanism comprises a supporting plate, a connecting rod and a spring, the supporting plate is movably connected to the upper end of the main support rod, the connecting rod is fixed to one side of the supporting plate, one end of the spring is connected with the supporting plate, and the other end of the spring is connected with the main support rod; the driving mechanism comprises a driving motor, a driving wheel and a traction rope, the driving motor is fixed on the main support rod, the driving wheel is arranged at the power output end of the driving motor, one end of the traction rope is fixedly connected with the driving wheel, and the other end of the traction rope is fixedly connected with the connecting rod; the moving mechanism comprises a cab, a steering wheel and moving wheels, the cab is arranged above the supporting plate, the moving wheels are arranged below the supporting plate, and the square discs are arranged in the cab and used for controlling the moving wheels.
2. An aircraft horizontal wing test carrier as claimed in claim 1, wherein: the electric bicycle further comprises a center console, wherein the center console is arranged in the cab and is respectively used for controlling the walking motor and the driving motor.
3. An aircraft horizontal wing test carrier as claimed in claim 1, wherein: the upper plane of the supporting plate is in the shape of a downward sunken arc, and a cushion block is arranged on the supporting plate.
4. An aircraft horizontal wing test carrier as claimed in claim 1, wherein: the auxiliary connecting seat is positioned above the lifting connecting seat.
5. An aircraft horizontal wing test carrier as claimed in claim 1, wherein: the connecting points of the springs and the supporting plate and the connecting rods are respectively positioned on two sides of the supporting plate.
6. An aircraft horizontal wing test carrier as claimed in claim 1, wherein: and a sliding block is fixed on the walking motor and is movably connected with the supporting plate.
7. An aircraft horizontal wing test carrier as claimed in claim 6, wherein: the bottom of slider is provided with T type arch, be provided with on the backup pad with T type protruding T type recess that matches.
8. An aircraft horizontal wing test carrier as claimed in claim 1, wherein: the diameter of the driving wheel is larger than that of the connecting rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810963270.0A CN108974390B (en) | 2018-08-22 | 2018-08-22 | Plane horizontal wing test bracket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810963270.0A CN108974390B (en) | 2018-08-22 | 2018-08-22 | Plane horizontal wing test bracket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108974390A CN108974390A (en) | 2018-12-11 |
| CN108974390B true CN108974390B (en) | 2020-04-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810963270.0A Active CN108974390B (en) | 2018-08-22 | 2018-08-22 | Plane horizontal wing test bracket |
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| CN (1) | CN108974390B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110356584B (en) * | 2019-06-28 | 2021-06-22 | 西安航空学院 | Adjusting method for aircraft wing assembly |
| CN114527008B (en) * | 2022-01-14 | 2024-03-15 | 成都飞机工业（集团）有限责任公司 | Device and method for simulating loading of folding gravity load of aircraft wing |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200948884Y (en) * | 2006-09-19 | 2007-09-19 | 成都飞机设计研究所 | Wing drop tank bracket car |
| CN105151318A (en) * | 2015-09-28 | 2015-12-16 | 山东太古飞机工程有限公司 | Auxiliary bracket for airplane wing installation |
| CN205076752U (en) * | 2015-07-22 | 2016-03-09 | 成都航空职业技术学院 | Detachable aircraft wing bracket |
| CN206068194U (en) * | 2016-08-28 | 2017-04-05 | 深圳市劲拓自动化设备股份有限公司 | Can Omni-mobile wing mounting platform |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10377288B2 (en) * | 2013-03-27 | 2019-08-13 | International Automated Systems, Inc. | Reinforced universal aircraft mule |
-
2018
- 2018-08-22 CN CN201810963270.0A patent/CN108974390B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200948884Y (en) * | 2006-09-19 | 2007-09-19 | 成都飞机设计研究所 | Wing drop tank bracket car |
| CN205076752U (en) * | 2015-07-22 | 2016-03-09 | 成都航空职业技术学院 | Detachable aircraft wing bracket |
| CN105151318A (en) * | 2015-09-28 | 2015-12-16 | 山东太古飞机工程有限公司 | Auxiliary bracket for airplane wing installation |
| CN206068194U (en) * | 2016-08-28 | 2017-04-05 | 深圳市劲拓自动化设备股份有限公司 | Can Omni-mobile wing mounting platform |
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| Publication number | Publication date |
|---|---|
| CN108974390A (en) | 2018-12-11 |
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Effective date of registration: 20210420 Address after: No.198, Jianghai West Road, Haian Town, Haian City, Nantong City, Jiangsu Province Patentee after: Hengcheng Aviation Technology (Nantong) Co.,Ltd. Address before: 448000 Jingmen province Hubei city Zhanghe District Aviation Industrial Park No. 1 love to fly Patentee before: ALOONG AIRCRAFT (JINGMEN) Co.,Ltd. |