CN209656686U - A kind of aircraft wing fatigue crack detection device - Google Patents
A kind of aircraft wing fatigue crack detection device Download PDFInfo
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- CN209656686U CN209656686U CN201822013755.1U CN201822013755U CN209656686U CN 209656686 U CN209656686 U CN 209656686U CN 201822013755 U CN201822013755 U CN 201822013755U CN 209656686 U CN209656686 U CN 209656686U
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- crossbar
- aircraft wing
- column
- bevel gear
- detection device
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Abstract
The utility model discloses a kind of aircraft wing fatigue crack detection devices, including pedestal, support column and column, there are four support legs for the base bottom installation, four support legs are distributed in rectangular uniform, the support foot bottom is equipped with movable pulley, the pedestal is frame structure, one jiao of the base upper surface is equipped with support column, other triangles of the base upper surface are mounted on column, glass plate is installed between the support column and three columns, when needing to detect aircraft wing, aircraft wing is put on a glass, start motor, worm screw rotation, first bevel gear rotation, second bevel gear rotation, to make threaded rod rotate, to keep scanner walker and marking appliance walker mobile, scanner, which opens up, at this time is scanned wing, when finding crackle, marking appliance will be marked to position is changed.
Description
Technical field
The utility model relates to aircraft maintenance field of mechanical technique, specifically a kind of aircraft wing fatigue crack detection dress
It sets.
Background technique
Aircraft is easy in high airflight by external impacts such as hail, dusts storm, and wing is caused the case where pit occur, and machine
The wing is to guarantee the vital component of aircraft flight, it is therefore desirable to its integrality of great care.
The detection mode of aircraft wing is completed generally by artificial at present, i.e., maintenance personal observes machine by eyes
Then the wing not only needs to expend more manpower, but also testing result with hand label, measurement and record, such course of work
It is affected by human factors larger.With the development of science and technology, special detection device is gradually appeared to replace manually examining
Aircraft wing is surveyed, but existing equipment generally can only first check a surface of wing, and it is another then to turn inspection again
Surface, aircraft wing figure itself is excessive, moves relatively difficult, and such detection mode efficiency is not good enough, therefore, this field
Technical staff provides a kind of aircraft wing fatigue crack detection device, to solve the problems mentioned in the above background technology.
Utility model content
The purpose of this utility model is to provide a kind of aircraft wing fatigue crack detection devices, to solve above-mentioned background skill
The problem of being proposed in art.
To achieve the above object, the utility model provides the following technical solutions:
A kind of aircraft wing fatigue crack detection device, including pedestal, support column and column, the base bottom are equipped with
Four support legs, four support legs are distributed in rectangular uniform, and the support foot bottom is equipped with movable pulley, and the pedestal is framework
Structure, one jiao of the base upper surface are equipped with support column, other triangles of the base upper surface are mounted on column, the branch
Glass plate is installed between dagger and three columns, the support column and its first cross is provided between the column in a plane
Bar and second crossbar, the first crossbar and second crossbar are distributed in the two sides up and down of glass plate, set between other two column
It sets there are two third cross bar, two third cross bars are arranged in parallel with first crossbar and second crossbar respectively, and the support column is sky
Heart shell, support column inner cavity centre position are equipped with motor, and the motor is provided with protective shell, the motor axle portion connection
There are worm gear, worm gear connecting worm, the worm screw both ends are arranged with first bevel gear, the first bevel gear rotation connection second
Bevel gear, the second bevel gear are meshed with first bevel gear, and the second bevel gear is arranged with threaded rod, the threaded rod
It is arranged with the first movable block and the second movable block respectively, the third cross bar is hollow shell, the setting of third cross bar inner cavity
There is slide bar, the jack rod sleeve is equipped with the first slide cartridge and the second slide cartridge, linkage flag between first movable block and the second slide cartridge
Instrument walker, connects scanner walker between second movable block and the first slide cartridge, the scanner walker passes through company
Fitting connects first mechanical arm, and the first mechanical arm bottom is equipped with scanner, and the marking appliance walker passes through connector
Second mechanical arm is connected, second mechanical arm bottom blackout has marking appliance.
As a further solution of the present invention: the connector includes that the first connection semicircle and second connect semicircle,
The first connection semicircle and the second connection semicircle are rotatablely connected by hinge, and the second connection semicircle is set far from hinge one end
It is equipped with connecting plate, the first connection semicircle is provided with fixed plate far from hinge one end.
The fixed plate offers groove body as a further solution of the present invention, and the groove body inner cavity is provided with
Spring, the spring one end connect limited block, and the limited block is arranged in groove body inner cavity, and the limited block is arranged with cutting, institute
It states connecting plate and cutting corresponding position offers through-hole.
First movable block and the second movable block offer screw thread as a further solution of the present invention,
Hole, first movable block and the second movable block pass through the threaded hole opened up and threaded rod is rotatablely connected.
The worm screw is rotatablely connected by bearing and support column as a further solution of the present invention, threaded rod
It is rotatablely connected respectively with first crossbar and second crossbar by bearing, the slide bar connects by the way that fixing seat and third cross bar are fixed
It connects.
The first crossbar and second crossbar are hollow shell as a further solution of the present invention, and two
Threaded rod is arranged at first crossbar and second crossbar inner cavity.
The first crossbar and second crossbar are opposite with two third cross bars as a further solution of the present invention,
Side is provided with opening.
Compared with prior art, the utility model has the beneficial effects that
1, when needing to detect aircraft wing, aircraft wing is put on a glass, starts motor, worm screw turns
It is dynamic, first bevel gear rotation, second bevel gear rotation, to make threaded rod rotate, to make scanner walker and marking appliance
Walker is mobile, and scanner, which opens up, at this time is scanned wing, and when finding crackle, marking appliance will be marked to position is changed
Note.
2, by the glass plate of setting, so that wing bottom can also be detected by scanner, it is convenient and efficient, pass through the company of setting
Fitting can conveniently replace mechanical arm, save a large amount of time, and the present apparatus is structurally reasonable, and suitable society is widely used.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of aircraft wing fatigue crack detection device；
Fig. 2 is the connection figure of second crossbar and third cross bar in a kind of aircraft wing fatigue crack detection device；
Fig. 3 is a kind of structural schematic diagram of connector in aircraft wing fatigue crack detection device；
Fig. 4 is the partial enlarged view of A in aircraft wing fatigue crack detection device a kind of.
In figure: 1- pedestal, 2- support leg, 3- movable pulley, 4- support column, 5- protective shell, 6- motor, 7- worm screw, 8- first
Bevel gear, 9- second bevel gear, 10- threaded rod, 11- column, 12- first crossbar, the first movable block of 13-, the second activity of 14-
Block, 15- first mechanical arm, 16- scanner, 17- second mechanical arm, 18- marking appliance, 19- second crossbar, 20- glass plate, 21-
Scanner walker, 22- connector, 23- marking appliance walker, the first slide cartridge of 24-, the second slide cartridge of 25-, 26- third cross bar,
27- slide bar, the connection of 28- first semicircle, the connection of 29- second semicircle, 30- hinge, 31- connecting plate, 32- through-hole, 33- fixed plate,
34- groove body, 35- cutting, 36- limited block, 37- spring.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
Please refer to Fig. 1~4, in the utility model embodiment, a kind of aircraft wing fatigue crack detection device, including pedestal
1, support column 4 and column 11,1 bottom of the pedestal installation is there are four support leg 2, and four support legs 2 are distributed in rectangular uniform, institute
It states 2 bottom of support leg and movable pulley 3 is installed, the pedestal 1 is frame structure, and one jiao of 1 upper surface of pedestal is equipped with support
Column 4, other triangles of 1 upper surface of pedestal are mounted on column 11, are equipped with glass between the support column 4 and three columns 11
Glass plate 20, the support column 4 and its first crossbar 12 and second crossbar 19 are provided between the column 11 in a plane, it is described
First crossbar 12 and second crossbar 19 are distributed in the two sides up and down of glass plate 20, and there are two for setting between other two column 11
Three cross bars 26, two third cross bars 26 are arranged in parallel with first crossbar 12 and second crossbar 19 respectively, and the support column 4 is hollow
Shell, 4 inner cavity of support column centre position are equipped with motor 6, and the motor 6 is provided with protective shell 5,6 axle portion of motor
It is connected with worm gear, worm gear connecting worm 7,7 both ends of worm screw are arranged with first bevel gear 8, and the first bevel gear 8 rotates
Second bevel gear 9 is connected, the second bevel gear 9 is meshed with first bevel gear 8, and the second bevel gear 9 is arranged with screw thread
Bar 10, the threaded rod 10 are arranged with the first movable block 13 and the second movable block 14 respectively, and the third cross bar 26 is hollow shell
Body, 26 inner cavity of third cross bar are provided with slide bar 27, and the slide bar 27 is arranged with the first slide cartridge 24 and the second slide cartridge 25, described
Linkage flag instrument walker 23 between first movable block 13 and the second slide cartridge 25, second movable block 14 and the first slide cartridge 24 it
Between connect scanner walker 21, the scanner walker 21 by connector 22 connect first mechanical arm 15, described first
15 bottom of mechanical arm is equipped with scanner 16, and the marking appliance walker 23 connects second mechanical arm 17, institute by connector 22
Stating 17 bottom blackout of second mechanical arm has marking appliance 18.
The connector 22 includes the first connection semicircle 28 and the second connection semicircle 29, the first connection semicircle 28 and the
Two connection semicircles 29 are rotatablely connected by hinge 30, and the second connection semicircle 29 is provided with connecting plate far from 30 one end of hinge
31, the first connection semicircle 28 is provided with fixed plate 33 far from 30 one end of hinge.
The fixed plate 33 offers groove body 34, and 34 inner cavity of groove body is provided with spring 37, and described 37 one end of spring connects
Limited block 36 is connect, the limited block 36 is arranged in 34 inner cavity of groove body, and the limited block 36 is arranged with cutting 35, the connecting plate 31
Through-hole 32 is offered with 35 corresponding position of cutting.
First movable block 13 and the second movable block 14 offer threaded hole, and first movable block 13 and second is living
Motion block 14 passes through the threaded hole opened up and threaded rod 10 is rotatablely connected.
The worm screw 7 is rotatablely connected by bearing and support column 4, threaded rod 10 by bearing respectively with first crossbar 12 and
Second crossbar 19 is rotatablely connected, and the slide bar 27 is fixedly connected by fixing seat with third cross bar 26.
The first crossbar 12 and second crossbar 19 are hollow shell, and two threaded rods 10 are arranged at first crossbar 12
With 19 inner cavity of second crossbar.
The first crossbar 12 and second crossbar 19 and two 26 opposite sides of third cross bar are provided with opening.
The working principle of the utility model is:
The utility model relates to a kind of aircraft wing fatigue crack detection device, when needing to detect to aircraft wing
When, aircraft wing is placed on glass plate 20, motor 6 is started, worm screw 7 rotates, and first bevel gear 8 rotates, and 9 turns of second bevel gear
Dynamic, so that threaded rod 10 be made to rotate, to keep scanner walker 21 and marking appliance walker 23 mobile, scanner 16 is opened at this time
If being scanned to wing, when finding crackle, marking appliance 18 will be marked to position is changed, and pass through the glass plate of setting
20, so that wing bottom can also be detected by scanner 16, it is convenient and efficient, it, can conveniently more by the connector 22 of setting
Mechanical arm is changed, a large amount of time is saved, the present apparatus is structurally reasonable, and suitable society is widely used.
The preferable specific embodiment of the above, only the utility model, but the protection scope of the utility model is not
It is confined to this, anyone skilled in the art is within the technical scope disclosed by the utility model, practical according to this
Novel technical solution and its utility model design are subject to equivalent substitution or change, should all cover the protection model in the utility model
Within enclosing.
Claims (7)
1. a kind of aircraft wing fatigue crack detection device, including pedestal (1), support column (4) and column (11), feature exists
In pedestal (1) the bottom installation is there are four support leg (2), and four support legs (2) are distributed in rectangular uniform, the support leg
(2) bottom is equipped with movable pulley (3), and the pedestal (1) is frame structure, and one jiao of pedestal (1) upper surface is equipped with support
Column (4), other triangles of pedestal (1) upper surface are mounted on column (11), the support column (4) and three columns (11) it
Between be equipped with glass plate (20), the support column (4) and its be provided with first crossbar between the column (11) in a plane
(12) and second crossbar (19), the first crossbar (12) and second crossbar (19) are distributed in the two sides up and down of glass plate (20),
Setting is there are two third cross bar (26) between other two column (11), two third cross bars (26) respectively with first crossbar (12)
It is arranged in parallel with second crossbar (19), the support column (4) is hollow shell, position installation among support column (4) inner cavity
Have motor (6), the motor (6) is provided with protective shell (5), and motor (6) axle portion is connected with worm gear, worm gear connecting worm
(7), worm screw (7) both ends are arranged with first bevel gear (8), and the first bevel gear (8) is rotatablely connected second bevel gear
(9), the second bevel gear (9) is meshed with first bevel gear (8), and the second bevel gear (9) is arranged with threaded rod (10),
The threaded rod (10) is arranged with the first movable block (13) and the second movable block (14) respectively, and the third cross bar (26) is hollow
Shell, third cross bar (26) inner cavity are provided with slide bar (27), and the slide bar (27) is arranged with the first slide cartridge (24) and second
Slide cartridge (25), linkage flag instrument walker (23) between first movable block (13) and the second slide cartridge (25), described second is living
Scanner walker (21) are connected between motion block (14) and the first slide cartridge (24), the scanner walker (21) passes through connector
(22) first mechanical arm (15) are connected, first mechanical arm (15) bottom is equipped with scanner (16), the marking appliance walking
Frame (23) has marking appliance by connector (22) connection second mechanical arm (17), second mechanical arm (17) the bottom blackout
(18)。
2. a kind of aircraft wing fatigue crack detection device according to claim 1, which is characterized in that the connector
It (22) include the first connection semicircle (28) and the second connection semicircle (29), first connection semicircle (28) and second connect semicircle
(29) it is rotatablely connected by hinge (30), second connection semicircle (29) is provided with connecting plate far from hinge (30) one end
(31), first connection semicircle (28) is provided with fixed plate (33) far from hinge (30) one end.
3. a kind of aircraft wing fatigue crack detection device according to claim 2, which is characterized in that the fixed plate
(33) it offers groove body (34), groove body (34) inner cavity is provided with spring (37), and described spring (37) one end connects limited block
(36), the limited block (36) is arranged in groove body (34) inner cavity, and the limited block (36) is arranged with cutting (35), the connecting plate
(31) through-hole (32) are offered with cutting (35) corresponding position.
4. a kind of aircraft wing fatigue crack detection device according to claim 1, which is characterized in that first activity
Block (13) and the second movable block (14) offer threaded hole, first movable block (13) and the second movable block (14) by opening
If threaded hole and threaded rod (10) be rotatablely connected.
5. a kind of aircraft wing fatigue crack detection device according to claim 1, which is characterized in that the worm screw (7)
Be rotatablely connected by bearing and support column (4), threaded rod (10) by bearing respectively with first crossbar (12) and second crossbar
(19) it is rotatablely connected, the slide bar (27) is fixedly connected by fixing seat with third cross bar (26).
6. a kind of aircraft wing fatigue crack detection device according to claim 1, which is characterized in that the first crossbar
(12) and second crossbar (19) is hollow shell, and two threaded rods (10) are arranged at first crossbar (12) and second crossbar
(19) inner cavity.
7. a kind of aircraft wing fatigue crack detection device according to claim 1, which is characterized in that the first crossbar
(12) and second crossbar (19) and two third cross bar (26) opposite sides are provided with opening.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822013755.1U CN209656686U (en) | 2018-12-03 | 2018-12-03 | A kind of aircraft wing fatigue crack detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822013755.1U CN209656686U (en) | 2018-12-03 | 2018-12-03 | A kind of aircraft wing fatigue crack detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209656686U true CN209656686U (en) | 2019-11-19 |
Family
ID=68517601
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822013755.1U Active CN209656686U (en) | 2018-12-03 | 2018-12-03 | A kind of aircraft wing fatigue crack detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209656686U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114660259A (en) * | 2022-03-17 | 2022-06-24 | 中国民用航空飞行学院 | Airplane wing fatigue crack detection device |
-
2018
- 2018-12-03 CN CN201822013755.1U patent/CN209656686U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114660259A (en) * | 2022-03-17 | 2022-06-24 | 中国民用航空飞行学院 | Airplane wing fatigue crack detection device |
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