CN106001376B - Aircraft stacking reinforcement structure edge loosens rivet removal device - Google Patents
Aircraft stacking reinforcement structure edge loosens rivet removal device Download PDFInfo
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- CN106001376B CN106001376B CN201610663862.1A CN201610663862A CN106001376B CN 106001376 B CN106001376 B CN 106001376B CN 201610663862 A CN201610663862 A CN 201610663862A CN 106001376 B CN106001376 B CN 106001376B
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- rivet
- aircraft
- lock lever
- check lock
- reinforcement structure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/38—Accessories for use in connection with riveting, e.g. pliers for upsetting; Hand tools for riveting
- B21J15/50—Removing or cutting devices for rivets
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Press Drives And Press Lines (AREA)
- Automatic Assembly (AREA)
Abstract
A kind of aircraft stacking reinforcement structure edge loosens rivet removal device, including：Lower carriage, it is provided with clamping device；Upper bracket, it, which is provided with, is engaged with upper clamping device for by the lower fixture of sheet material horizontal-clamping；Rivet support device, it is vertically arranged on lower carriage, and its upper end is provided with the anvil block being in contact with rivet lower end pier nose portion；And check lock lever, it is vertically arranged on upper bracket, and with rivet support device same axis, check lock lever be axially inside provided with drill bit match drilling.In use, making below the pier nose for the rivet that the anvil block on rivet support device withstands on loosening, check lock lever is also directed to the top of the technique head of the rivet of loosening, the sheet material that aircraft is laminated into reinforcement structure afterwards passes through upper clamping device and lower fixture and clamped.Drill bit, by rivet drilling, is removed along drilling up to it is complete.The dismounting efficiency of rivet is improved, rivet mounting hole aperture will not become big, will not be installed to follow-up rivet and bring hidden danger.
Description
Technical field
Rivet removal device is loosened the present invention relates to a kind of aircraft stacking reinforcement structure edge.
Background technology
There are many stacking reinforcement structures on Boeing 737 airplane, typically by two layers or multilayer aluminium sheet, composite board
Riveting is formed.Because awing there is the working conditions such as vibrations, rain erosion in the region so that the region rivet often occurs
Loosen and then cause structure to be peeled off, influence flight safety.Not yet there are special tooling device and technique to handle the area at present
There is the situation loosened in domain rivet, is removed more by worker by its working experience and skill, because drill bit is cut in drilling process
Cut land and move rivet around mounting hole rotation, often cause rivet mounting hole aperture to become big, be that follow-up rivet is installed and airborne vehicle
Safety belt carrys out hidden danger.
The content of the invention
The present invention loosens riveting to overcome the shortcomings of that above technology improves aircraft stacking reinforcement structure edge there is provided one kind
Nail removes operating efficiency and the machine stacking reinforcement structure edge of precision loosens rivet removal device.
The technical scheme that the present invention overcomes its technical problem to be used is：
A kind of aircraft stacking reinforcement structure edge loosens rivet removal device, including：
Lower carriage, it is provided with clamping device；
Upper bracket, is arranged at the upper end of lower carriage, and it, which is provided with, is engaged with upper clamping device for sheet material level to be pressed from both sides
Tight lower fixture；
Rivet support device, it is vertically arranged on lower carriage, and its upper end is provided with to be in contact with rivet lower end pier nose portion
Anvil block；And
Check lock lever, it is vertically arranged on upper bracket, and with rivet support device same axis, along axle inside the check lock lever
The drilling matched to being provided with drill bit.
Above-mentioned upper clamping device includes being combined on the clamping screw I of four edges of upper bracket vertically, is arranged at clamping spiral shell
The rubber blanket I of the lower end of bar I and the clamping knob wheel I for being arranged at the top of clamping screw I, the lower fixture include vertical rotation
Clamping screw II together in four edges of lower carriage, it is arranged at the rubber blanket II on the top of clamping screw II and is arranged at clamping
Screw rod II pushes up the clamping knob wheel II of lower end.
Above-mentioned check lock lever lower end is along the circumferential direction arranged at intervals with some locking tooth pieces, between each described locking tooth piece
Internal diameter is more than the bolt diameter of rivet, and less than the technique head diameter of rivet.
In order to easy to operate, the head end of above-mentioned check lock lever is provided with check lock lever handwheel.
For the ease of centering, the cross recess with the pier nose matching of rivet is provided with above-mentioned anvil block.
For the ease of being adjusted at the rivet of the loosening of response, it is staggered on above-mentioned upper bracket along front and rear and left and right directions
Some check lock lever chutes, some bulb chutes being staggered along front and rear and left and right directions on the lower carriage are described
Some screws are arranged at intervals with check lock lever chute, the check lock lever is combined in corresponding screw by the end of thread, the riveting
The bottom of nail support meanss is provided with bulb, and the bulb is placed in bulb chute.
For the ease of movement, above-mentioned rivet support device includes outer loop bar and the movable interior bar being plugged in outer loop bar,
Spring is provided between the interior bar and outer loop bar, the interior bar lower end is provided with the limiting block for preventing that it from departing from from outer loop bar
Ring, the head end of the interior bar is connected with anvil block, and the lower end of the outer loop bar is connected with bulb.
For the ease of being adjusted at the rivet of the loosening of response, in addition to for driving upper bracket sliding with respect to before and after lower carriage
Dynamic carriage drive mechanism.
Dovetail groove that above-mentioned carriage drive mechanism includes being arranged at lower carriage upper end, the dovetail for being arranged at upper bracket lower end are led
Rail, the rack for being arranged at along the length direction of dovetail guide dovetail guide lower end, it is rotatablely installed in lower branch by gear drive rod
Gear on frame, the head end of the gear drive rod is provided with gear driving handwheel, and upper bracket is slided by dovetail guide and inserted
In the dovetail groove of lower carriage, and rack and pinion is meshed.
In order to increase adjustment stroke, said gear has two groups, two gears respectively by gear drive rod be rotatablely installed in
The rear and front end of lower carriage, two gears are meshed with rack respectively.
The beneficial effects of the invention are as follows：In use, make the anvil block on rivet support device withstand on loosening rivet pier nose
Lower section, check lock lever is also directed at the top of the technique head of the rivet of loosening, and the sheet material that aircraft is laminated into reinforcement structure afterwards passes through
Upper clamping device and lower fixture are clamped.Drill bit, by rivet drilling, is removed along drilling up to it is complete.Improve rivet
Efficiency is removed, rivet mounting hole aperture will not become big, will not be installed to follow-up rivet and bring hidden danger.
Brief description of the drawings
Fig. 1 is stereochemical structure explosive view of the invention；
Fig. 2 is stereoscopic mechanism schematic diagram of the invention；
Fig. 3 is the structural representation for locking tooth piece of the invention；
Fig. 4 is the structural representation of the anvil block of the present invention；
In figure, the rubber blanket I 7. of 1. lower carriage, 2. upper bracket, 3. dovetail guide, 4. dovetail groove, 5. clamping screw I 6. folder
The gear driving of 12. gear of tight knob wheel I 8. clamping screw, II 9. clamping knob wheel, II 10. rubber blanket, II 11. rack 13.
The check lock lever handwheel of 18. check lock lever of the gear of bar 14. driving handwheel 15. check lock lever chute, 16. screw, 17. bulb chute 19.
20. the cross recess 27. of 25. anvil block of outer 22. interior bar of loop bar 23. bulb, 24. limit baffle ring of drill bit 21. 26. locks tooth piece
28. sheet material.
Embodiment
Below in conjunction with the accompanying drawings 1, accompanying drawing 2, accompanying drawing 3, the present invention will be further described for accompanying drawing 4.
As shown in Figures 1 and 2, a kind of aircraft stacking reinforcement structure edge loosens rivet removal device, including：Lower branch
Frame 1, it is provided with clamping device；Upper bracket 2, is arranged at the upper end of lower carriage 1, and it is provided with is engaged with upper clamping device
For by the lower fixture of the horizontal-clamping of sheet material 28；Rivet support device, it is vertically arranged on lower carriage 1, and its upper end is set
It is equipped with the anvil block 25 being in contact with rivet lower end pier nose portion；And check lock lever 18, it is vertically arranged on upper bracket 2, and and riveting
Support meanss same axis is followed closely, check lock lever 18 is axially inside provided with the drilling matched with drill bit 20.In use, making rivet support
Anvil block 25 on device is withstood on below the pier nose of the rivet of loosening, check lock lever 18 is also aligned the rivet of loosening technique head it is upper
Side, the sheet material 28 that aircraft is laminated to reinforcement structure afterwards is clamped by upper clamping device and lower fixture.Drill bit 20 is along brill
Hole is by rivet drilling, until it is removed completely.The dismounting efficiency of rivet is improved, rivet mounting hole aperture will not become big, will not
Installed to follow-up rivet and bring hidden danger.
Further, upper clamping device includes being combined on the clamping screw I 5 of 2 four edges of upper bracket vertically, set
In the lower end of clamping screw I 5 rubber blanket I 6 and be arranged at the clamping knob wheel I 7 on the top of clamping screw I 5, it is lower to clamp dress
Put including being combined on the clamping screw II 8 of 1 four edges of lower carriage vertically, being arranged at the rubber on the top of clamping screw II 8
Pad II 10 and the clamping knob wheel II 9 for being arranged at the top of clamping screw II 8 lower end.By rotate clamping knob wheel I 7 and
Clamping knob wheel II 9 drives clamping screw I 5 and clamping screw II 8 to rotate respectively, finally realizes rubber blanket I 6 and rubber
Pad II 10 is in contact with the upper plane and lower plane of sheet material 28 respectively, and the horizontal-clamping of sheet material 28 is fixed in realization.Under check lock lever 18
End can along the circumferential direction be arranged at intervals with some locking tooth pieces 27, and the internal diameter between each locking tooth piece 27 is more than the anchor of rivet
Shank diameter, and less than the technique head diameter of rivet.Therefore each locking tooth piece 27 can be wrapped in the technique head periphery of rivet, real
The fixation of existing circumferencial direction, prevents drill bit 20 in drilling, the rivet of loosening follows drill bit 20 to rotate.The head end of check lock lever 18 can
To be provided with check lock lever handwheel 19.Drive check lock lever 18 to rotate by check lock lever handwheel 19 efficiently convenient, improve operation just
Profit.The cross recess 26 with the pier nose matching of rivet can be provided with anvil block 25, it is necessary to the pier of the rivet for the loosening removed
Head is placed in the cross recess 26 of anvil block 25, can preferably be realized centering, be improved the convenience used.
Further, some check lock lever chutes 15 being staggered on upper bracket 2 along front and rear and left and right directions, lower carriage
Some spiral shells are arranged at intervals with some bulb chutes 17 being staggered on 1 along front and rear and left and right directions, check lock lever chute 15
Hole 16, check lock lever 18 is combined in corresponding screw 16 by the end of thread, and the bottom of rivet support device is provided with bulb 23, ball
First 23 are placed in bulb chute 17.Rivet support device can be slided in bulb chute 17 by bulb 23 and quickly navigated to
At the rivet for needing drilling dismounting, and check lock lever 18 can realize quick positioning by screwing in corresponding screw 16, improve
Efficiency.Rivet support device includes outer loop bar 21 and the movable interior bar 22 being plugged in outer loop bar 21, interior bar 22 and outer loop bar
Spring is provided between 21, the lower end of interior bar 22 is provided with the limit baffle ring 24 for preventing that it from departing from from outer loop bar 21, interior bar 22
Head end is connected with anvil block 25, and the lower end of outer loop bar 21 is connected with bulb 23.When needing to move, interior bar 22 is pulled downward on, made
Spring-compressed, while anvil block 25 is not contacted with the pier nose of rivet, can be moved easily, when being moved to specified location, unclamp interior
Interior bar 22 is pushed to anvil block 25 and is in contact with the pier nose of rivet by bar 22, spring.Also include being used to drive upper bracket 2 lower relatively
The carriage drive mechanism that frame 1 slides back and forth, the front and back position of upper bracket 2 and lower carriage 1 can be adjusted by carriage drive mechanism,
The progressive convenience for improving regulation.Further, carriage drive mechanism can be following structure, and it includes being arranged at lower carriage
The dovetail groove 4 of 1 upper end, the dovetail guide 3 for being arranged at the lower end of upper bracket 2, it is arranged at dovetail along the length direction of dovetail guide 3 and leads
The rack 11 of the lower end of rail 3, it is rotatablely installed in the gear 12 on lower carriage 1, the head of gear drive rod 13 by gear drive rod 13
End is provided with gear driving handwheel 14, and upper bracket 2 is slided by dovetail guide 3 and is plugged in the dovetail groove 4 of lower carriage 1, and tooth
Bar 11 is meshed with gear 12.The driving gear drives bar 13 of handwheel 14 is driven to rotate by gear, so that gear 12 is rotated, tooth
Wheel 12, which is rotated, slides dovetail groove 4 of the upper bracket 2 by dovetail guide 3 along lower carriage 1.Gear 12 can have two groups, two
Gear 12 is rotatablely installed in the rear and front end of lower carriage 1 by gear drive rod 13 respectively, two gears 12 respectively with rack 11
It is meshed.The stroke of the slip of rack 11 can so be improved, it is to avoid gear 12 departs from rack 11.
Claims (9)
1. a kind of aircraft stacking reinforcement structure edge loosens rivet removal device, it is characterised in that including：
Lower carriage（1）, it is provided with clamping device；
Upper bracket（2）, it is arranged at lower carriage（1）Upper end, it, which is provided with, is engaged with upper clamping device for by sheet material（28）
The lower fixture of horizontal-clamping；
Rivet support device, it is vertically arranged at lower carriage（1）On, its upper end is provided with what is be in contact with rivet lower end pier nose portion
Anvil block（25）；And
Check lock lever（18）, it is vertically arranged at upper bracket（2）On, and, the check lock lever coaxial with rivet support device（18）It is interior
Portion is axially disposed to be had and drill bit（20）The drilling of matching, the upper clamping device includes being combined on upper bracket vertically（2）Four
The clamping screw I of edge（5）, be arranged at clamping screw I（5）The rubber blanket I of lower end（6）And it is arranged at clamping screw I（5）
The clamping knob wheel I on top（7）, the lower fixture including being combined on lower carriage vertically（1）The clamping spiral shell of four edges
Bar II（8）, be arranged at clamping screw II（8）The rubber blanket II on top（10）And it is arranged at clamping screw II（8）Push up lower end
Clamping knob wheel II（9）.
2. aircraft stacking reinforcement structure edge according to claim 1 loosens rivet removal device, it is characterised in that：It is described
Check lock lever（18）Lower end is along the circumferential direction arranged at intervals with some locking tooth pieces（27）, each described locking tooth piece（27）Between
Internal diameter is more than the bolt diameter of rivet, and less than the technique head diameter of rivet.
3. aircraft stacking reinforcement structure edge according to claim 1 loosens rivet removal device, it is characterised in that：It is described
Check lock lever（18）Head end be provided with check lock lever handwheel（19）.
4. aircraft stacking reinforcement structure edge according to claim 1 loosens rivet removal device, it is characterised in that：It is described
Anvil block（25）In be provided with cross recess with the matching of the pier nose of rivet（26）.
5. aircraft stacking reinforcement structure edge as claimed in any of claims 1 to 4 loosens rivet removal device, its
It is characterised by：The upper bracket（2）On be staggered some check lock lever chutes along front and rear and left and right directions（15）, the lower branch
Frame（1）On be staggered some bulb chutes along front and rear and left and right directions（17）, the check lock lever chute（15）Middle interval is set
It is equipped with some screws（16）, the check lock lever（18）Corresponding screw is combined on by the end of thread（16）In, the rivet support
The bottom of device is provided with bulb（23）, the bulb（23）It is placed in bulb chute（17）In.
6. aircraft stacking reinforcement structure edge according to claim 5 loosens rivet removal device, it is characterised in that：It is described
Rivet support device includes outer loop bar（21）And activity is plugged in outer loop bar（21）In interior bar（22）, the interior bar（22）With
Outer loop bar（21）Between be provided with spring, the interior bar（22）Lower end, which is provided with, prevents it from outer loop bar（21）Middle disengaging it is spacing
Baffle ring（24）, the interior bar（22）Head end and anvil block（25）It is connected, the outer loop bar（21）Lower end and bulb（23）It is connected.
7. aircraft stacking reinforcement structure edge as claimed in any of claims 1 to 4 loosens rivet removal device, its
It is characterised by：Also include being used to drive upper bracket（2）With respect to lower carriage（1）The carriage drive mechanism slid back and forth.
8. aircraft stacking reinforcement structure edge according to claim 7 loosens rivet removal device, it is characterised in that：It is described
Carriage drive mechanism includes being arranged at lower carriage（1）The dovetail groove of upper end（4）, be arranged at upper bracket（2）The dovetail guide of lower end
（3）, along dovetail guide（3）Length direction be arranged at dovetail guide（3）The rack of lower end（11）, pass through gear drive rod（13）
It is rotatablely installed in lower carriage（1）On gear（12）, the gear drive rod（13）Head end be provided with gear driving handwheel
（14）, upper bracket（2）Pass through dovetail guide（3）Slip is plugged in lower carriage（1）Dovetail groove（4）In, and rack（11）With tooth
Wheel（12）It is meshed.
9. aircraft stacking reinforcement structure edge according to claim 8 loosens rivet removal device, it is characterised in that：It is described
Gear（12）There are two, two gears（12）Pass through gear drive rod respectively（13）It is rotatablely installed in lower carriage（1）Front and rear two
End, two gears（12）Respectively with rack（11）It is meshed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610663862.1A CN106001376B (en) | 2016-08-15 | 2016-08-15 | Aircraft stacking reinforcement structure edge loosens rivet removal device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610663862.1A CN106001376B (en) | 2016-08-15 | 2016-08-15 | Aircraft stacking reinforcement structure edge loosens rivet removal device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106001376A CN106001376A (en) | 2016-10-12 |
| CN106001376B true CN106001376B (en) | 2017-10-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610663862.1A Active CN106001376B (en) | 2016-08-15 | 2016-08-15 | Aircraft stacking reinforcement structure edge loosens rivet removal device |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107321898B (en) * | 2017-09-01 | 2023-07-07 | 山东太古飞机工程有限公司 | Device is demolishd to not hard up hollow rivet of aircraft |
| CN107377691B (en) * | 2017-09-01 | 2023-04-07 | 山东太古飞机工程有限公司 | A marking-out device of bending fast for aircraft sheet metal |
| CN107738759B (en) * | 2017-11-13 | 2023-12-01 | 山东太古飞机工程有限公司 | Booster for dismounting and mounting aircraft engine fairing |
| CN107738223B (en) * | 2017-11-13 | 2023-11-10 | 山东太古飞机工程有限公司 | Auxiliary assembly and disassembly tool for fairing of first-stage stator blade of aircraft engine |
| CN108941428A (en) * | 2018-07-28 | 2018-12-07 | 江西省东龙实业股份有限公司 | A kind of fast-dialing wheel rivet punching |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2796578B1 (en) * | 1999-07-19 | 2001-11-23 | Alstom | TOOL FOR DISASSEMBLING RIVETS AND CORRESPONDING METHOD FOR DISASSEMBLING RIVETS |
| US20070071562A1 (en) * | 2005-09-23 | 2007-03-29 | Spitznagel Max W | Drill motor assembly for drilling out rivets |
| JP2012152818A (en) * | 2011-01-28 | 2012-08-16 | Sanyo Electric Co Ltd | Device for caulking rivet, and method for removing rivet |
| CN103878287A (en) * | 2014-02-21 | 2014-06-25 | 山东太古飞机工程有限公司 | Auxiliary remover for rivet with head |
| CN205111336U (en) * | 2015-11-11 | 2016-03-30 | 湖北大运汽车有限公司 | Drilling frock clamp assembly of rotatory many orientation locking |
| CN205851778U (en) * | 2016-08-15 | 2017-01-04 | 山东太古飞机工程有限公司 | Aircraft stacking reinforcement structure edge loosens rivet removal device |
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2016
- 2016-08-15 CN CN201610663862.1A patent/CN106001376B/en active Active
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| Publication number | Publication date |
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| CN106001376A (en) | 2016-10-12 |
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