CN107321898A - A kind of aircraft loosens tubular rivet and removes device - Google Patents
A kind of aircraft loosens tubular rivet and removes device Download PDFInfo
- Publication number
- CN107321898A CN107321898A CN201710778134.XA CN201710778134A CN107321898A CN 107321898 A CN107321898 A CN 107321898A CN 201710778134 A CN201710778134 A CN 201710778134A CN 107321898 A CN107321898 A CN 107321898A
- Authority
- CN
- China
- Prior art keywords
- tubular rivet
- pedestal
- drill bit
- loosens
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- 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
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Soil Working Implements (AREA)
- Drilling And Boring (AREA)
Abstract
A kind of aircraft loosens tubular rivet and removes device, including：Pedestal, triangular prism, drill bit, drive mechanism, connecting rod and adjusting nut.Triangular prism is clamped using air drill when using, pedestal is supported on above aircraft structure by support system, drill bit is set to be inserted perpendicularly into tubular rivet, adjusting nut is screwed afterwards, move up connecting rod, so as to which taper blade tooth knife will be compressed at the flange of tubular rivet lower end, when preventing that bit from cutting, tubular rivet follows rotation.Air drill drives drill bit to rotate in same direction after starting by drive mechanism, constantly rotating adjusting nut makes drill bit length feed simultaneously, realize and cut off the tubular rivet on aircraft structure, it will not be rotated when being cut due to tubular rivet, so as to the fastener hole that will not be worn and torn on origianl structure part, it is ensured that the safety after aircraft maintenance.
Description
Technical field
The present invention relates to aircraft maintenance tool field, and in particular to a kind of aircraft loosens tubular rivet and removes device.
Background technology
In aircraft flight, due to the influence of the factors such as stress deformation, vibrations, friction, alternate load so that connection knot
The tubular rivet of component loosens, and then influences the use safety and service life of aircraft component.
In aircraft maintenance process, typically carried out for the tubular rivet of loosening by the way of replacing is removed.According to existing
Having mode of operation, person typically carries out drilling excision using the fluted drill of drive power apparatus, in this process, due to rivet
Through loosen tubular rivet will along with fluted drill working angles common rotation, cause drilling to fail, it is empty in above process
Heart rivet bar may proceed to the fastener hole worn and torn on origianl structure part so that aperture is further increased, and ultimately results in situation further
Deteriorate, ultimately cause potential safety hazard and then influence the flight safety of aircraft.
The content of the invention
The present invention is in order to overcome the shortcomings of that above technology prevents that tubular rivet follows rotation in drilling process there is provided one kind
Aircraft loosen tubular rivet remove device.
The technical scheme that the present invention overcomes its technical problem to be used is：
A kind of aircraft loosens tubular rivet and removes device, including：
Pedestal, its lower end is provided with support system, and pedestal is supported in above aircraft structure by support system；
Triangular prism, is rotatablely installed in pedestal vertically；
Drill bit, is hollow-core construction, and it is axially inside provided with circular hole, and the drill bit is vertically arranged at pedestal by locking nut
Lower end；
Drive mechanism, is arranged in pedestal, and triangular prism and drill bit are connected by it, and when triangular prism turning, drill bit is same with it
To rotation；
Connecting rod, is plugged in the circular hole in drill bit vertically, and the connecting rod lower end is coaxially installed with taper blade tooth knife, and its upper end is coaxial
Be provided with screw rod and
Adjusting nut, the adjusting nut is located at pedestal upper end, and it is combined on screw rod, when adjusting nut is screwed, drill bit
Corresponding tubular rivet upper end is plugged in, taper blade tooth knife is plugged in the flange of tubular rivet lower end, the taper blade tooth knife
With the flange tight fit of tubular rivet lower end.
If said base include top base triangular in shape, be arranged at top base lower end bottom base triangular in shape and
The dry connecting rod being vertically arranged, the upper and lower ends of the connecting rod are respectively arranged with thread head I and thread head II, and small end passes through spiral shell
Line first I, which is screwed, to be fixed on top base, and its lower end is screwed by thread head II to be fixed on bottom base, is set inside the top base
Triangular cavity triangular in shape is equipped with, air drill is located in triangular cavity.
Above-mentioned drive mechanism includes the groove being arranged in pedestal and is rotatablely installed in the gear I in groove, gear II
And gear III, the gear I is meshed with gear II, and the gear II is meshed with gear III, the gear III and the warp
Nut is coaxially connected, and the triangular prism and gear I are coaxially connected.
Above-mentioned support system includes N number of pipe, the thread head III and thread head IV that are respectively arranged at pipe upper and lower ends, pin
Axle and the rubber feet that bearing pin lower end is installed on by screw II, tapered sleeve are plugged in pipe, and bearing pin is passed through and inserted after tapered sleeve
In pipe, spring housing is loaded in pipe, and its upper end is in contact with pipe, and its lower end is in contact with bearing pin, and spiro cap is loaded on pin
On the outside of axle and it is combined on thread head IV, the pipe upper end is combined on pedestal lower end vertically by thread head III, when nut revolves
When tight, tapered sleeve fixes bearing pin locking, and N is the natural number more than or equal to 3.
For the ease of regulation, above-mentioned adjusting nut is triangle nut.
In order to improve the convenience of operation, in addition to the support that is clipped between top base and bottom base and it is horizontally mounted
In the handle on support.
In order to improve security, in addition to it is fixed on by screw I capping of groove upper end, the capping is by groove upper end
Closed at opening.
It is horizontally disposed on above-mentioned connecting rod to have circular hole for the ease of installing.
The beneficial effects of the invention are as follows：Triangular prism is clamped using air drill when using, pedestal is supported by support system
Above aircraft structure, drill bit is inserted perpendicularly into tubular rivet, adjusting nut is screwed afterwards, move up connecting rod, so as to bore
Shape blade tooth knife will be compressed at the flange of tubular rivet lower end, and when preventing that bit from cutting, tubular rivet follows rotation.Air drill is opened
Drill bit is driven to rotate in same direction by drive mechanism after dynamic, while constantly rotating adjusting nut makes drill bit length feed, realizing to fly
Tubular rivet excision on machine structural member, will not rotate when being cut due to tubular rivet, so as to will not wear and tear on origianl structure part
Fastener hole, it is ensured that the safety after aircraft maintenance.
Brief description of the drawings
Fig. 1 is dimensional structure diagram of the invention；
Fig. 2 is stereochemical structure exploded perspective view of the invention；
In figure, the bottom base of 1. top base, 2. adjusting nut, 3. connecting rod, 4. triangular cavity, 5. thread head, I 6. thread head II 7.
8. the gear III of I 15. gear of the groove 11. of 9. handle of support 10. capping 12. triangular prism, 13. screw, I 14. gear II 16.
17. the rubber feet of 23. spring of pipe 18. thread head, III 19. thread head, IV 20. tapered sleeve, 21. nut, 22. bearing pin 24.
25. the taper blade tooth knife 32. of 30. connecting rod of screw II 26. locking nut, 27. drill bit, 28. aircraft structure, 29. screw rod 31.
The circular hole of tubular rivet 33..
Embodiment
Below in conjunction with the accompanying drawings 1, the present invention will be further described for accompanying drawing 2.
A kind of aircraft loosens tubular rivet and removes device, including：Pedestal, its lower end is provided with support system, and pedestal passes through
Support system is supported in the top of aircraft structure 28；Triangular prism 12, is rotatablely installed in pedestal vertically；Drill bit 27, is hollow knot
Structure, it is axially inside provided with circular hole, and drill bit 27 is vertically arranged at pedestal lower end by locking nut 26；Drive mechanism, if
It is placed in pedestal, triangular prism 12 is connected by it with drill bit 27, when triangular prism 12 is rotated, drill bit 27 rotates in same direction with it；
Connecting rod 30, is plugged in the circular hole in drill bit 27 vertically, and the lower end of connecting rod 30 is coaxially installed with taper blade tooth knife 31, and its upper end is coaxial
Screw rod 29 and adjusting nut 2 are provided with, adjusting nut 2 is located at pedestal upper end, and it is combined on screw rod 29, works as adjusting nut
2 when screwing, and drill bit 27 is plugged in the corresponding upper end of tubular rivet 32, and taper blade tooth knife 31 is plugged in turning over for the lower end of tubular rivet 32
In side, taper blade tooth knife 31 and the flange tight fit of the lower end of tubular rivet 32.Triangular prism 12 is clamped using air drill when using, will
Pedestal is supported on the top of aircraft structure 28 by support system, drill bit 27 is inserted perpendicularly into tubular rivet 32, screws afterwards
Adjusting nut 2, moves up connecting rod 30, so that taper blade tooth knife 31 will be compressed at the flange of the lower end of tubular rivet 32, prevents drill bit
During 27 rotary cutting, tubular rivet 32 follows rotation.Air drill drives drill bit 27 to rotate in same direction after starting by drive mechanism, simultaneously
Continuous rotating adjusting nut 2 makes the length feed of drill bit 27, and realization cuts off the tubular rivet 32 on aircraft structure 28, due to sky
Heart rivet 32 will not rotate when cutting, so that the fastener hole that will not be worn and torn on origianl structure part, it is ensured that the peace after aircraft maintenance
Entirely.
Pedestal can be following structure, and it includes top base 1 triangular in shape, is arranged at the triangular in shape of the lower end of top base 1
Bottom base 7 and some connecting rods 3 being vertically arranged, the upper and lower ends of connecting rod 3 are respectively arranged with thread head I 5 and thread head II
6, the upper end of connecting rod 3 is screwed by thread head I 5 to be fixed on top base 1, its lower end is screwed by thread head II 6 be fixed under
On pedestal 7, top base 1 is internally provided with triangular cavity 4 triangular in shape, and air drill is located in triangular cavity 4.Top base 1 is some
Connecting rod 3 and bottom base 7 constitute tower structure, and not only stability is high, at the same it is lightweight, save manufacturing cost.
Drive mechanism can be following structure, and it includes being arranged at the groove 10 in pedestal and is rotatablely installed in groove 10
Interior gear I 14, gear II 15 and gear III 16, gear I 14 is meshed with gear II 15, gear II 15 and gear III
16 are meshed, gear III 16 with it is coaxially connected through nut 26, triangular prism 12 and gear I 14 are coaxially connected.When air drill clamps three
When the driving triangular prism 12 of prism 12 is rotated, gear I 14 is rotated, and gear II 15 plays a part of idle pulley, makes gear III 16 and tooth
The direction of rotation for taking turns I 14 is identical, therefore realizes that drill bit 27 is identical with the direction of rotation of triangular prism 12.
Support system can be following structure, and it includes N number of pipe 17, is respectively arranged at the screw thread of the upper and lower ends of pipe 17
First III 18 and thread head IV 19, bearing pin 22 and the rubber feet 24 that the lower end of bearing pin 22 is installed on by screw II 25, tapered sleeve
20 are plugged in pipe 17, and bearing pin 22 is plugged in pipe 17 after passing through tapered sleeve 20, and spring 23 is set in pipe 17, its upper end
It is in contact with pipe 17, its lower end is in contact with bearing pin 22, nut 21 is set in the outside of bearing pin 22 and is combined on thread head IV 19
On, the upper end of pipe 17 is combined on pedestal lower end vertically by thread head III 18, when nut 21 is screwed, and tapered sleeve 20 is by bearing pin 22
Locking is fixed, and N is the natural number more than or equal to 3.In use, nut 21 is unclamped, rubber feet 24 and the table of aircraft structure 28
Face is contacted, and because bearing pin 22 can stretch in relative pipe 17, therefore whole device conveniently is adjusted into horizontal level, is made drill bit
27 with the same axis of tubular rivet 32.It is after being adjusted in place, nut 21 is locked, so that tapered sleeve 20 locks the position of bearing pin 22 admittedly
It is fixed.Its compression spring 23 when 22 slid inward of bearing pin, can be pushed away when bearing pin 22 needs protruding by the elastic force of spring 23
Move its Rapid reset.
Further, adjusting nut 2 is triangle nut, convenient to be screwed by spanner.It can also include being clipped on top base 1
Support 8 between bottom base 2 and the handle 9 being horizontally installed on support 8.When operated, operating personnel can be with hand-held hand
The position of handle 9, therefore whole device can be helped surely, improve stability during operation.It can also include consolidating by screw I 13
Due to the capping 11 of the upper end of groove 10, capping 11 will be closed at the upper end open of groove 10.11 are covered by gear I 14, gear II
15 and gear III 16 be enclosed in groove 10, prevent transmission mechanism it is exposed cause danger generation.It is preferred that, along water on connecting rod 3
Square to being provided with circular hole 33.During installing connecting rods 3, it is possible to use in instrument insertion circular hole 33, facilitate swivel link 3, make its spiral shell
Line first I 5 and thread head II 6 are quickly and easily screwed in corresponding screw, improve the efficiency of assembling.
Claims (8)
1. a kind of aircraft, which loosens tubular rivet, removes device, it is characterised in that including：
Pedestal, its lower end is provided with support system, and pedestal is supported in aircraft structure by support system（28）Top；
Triangular prism（12）, it is rotatablely installed vertically in pedestal；
Drill bit（27）, it is hollow-core construction, it is axially inside provided with circular hole, the drill bit（27）Pass through locking nut（26）It is perpendicular
Directly it is arranged at pedestal lower end；
Drive mechanism, is arranged in pedestal, and it is by triangular prism（12）With drill bit（27）Drive connection, works as triangular prism（12）Rotate
When, drill bit（27）Rotate in same direction with it；
Connecting rod（30）, drill bit is plugged in vertically（27）In circular hole in, the connecting rod（30）Lower end is coaxially installed with taper sword tooth
Knife（31）, its upper end is coaxially arranged with screw rod（29）And
Adjusting nut（2）, the adjusting nut（2）Positioned at pedestal upper end, and it is combined on screw rod（29）On, work as adjusting nut
（2）When screwing, drill bit（27）It is plugged in corresponding tubular rivet（32）Upper end, taper blade tooth knife（31）It is plugged in tubular rivet
（32）In the flange of lower end, the taper blade tooth knife（31）With tubular rivet（32）The flange tight fit of lower end.
2. aircraft according to claim 1, which loosens tubular rivet, removes device, it is characterised in that：The pedestal includes being in three
Angular top base（1）, be arranged at top base（1）The bottom base triangular in shape of lower end（7）And some companies being vertically arranged
Bar（3）, the connecting rod（3）Upper and lower ends be respectively arranged with thread head I（5）And thread head II（6）, connecting rod（3）Upper end passes through
Thread head I（5）Screw and be fixed on top base（1）On, its lower end passes through thread head II（6）Screw and be fixed on bottom base（7）On, institute
State top base（1）It is internally provided with triangular cavity triangular in shape（4）, air drill is positioned at triangular cavity（4）In.
3. aircraft according to claim 1, which loosens tubular rivet, removes device, it is characterised in that：The drive mechanism includes
It is arranged at the groove in pedestal（10）And be rotatablely installed in groove（10）Interior gear I（14）, gear II（15）And gear III
（16）, the gear I（14）With gear II（15）It is meshed, the gear II（15）With gear III（16）It is meshed, the tooth
Wheel III（16）With described through nut（26）It is coaxially connected, the triangular prism（12）With gear I（14）It is coaxially connected.
4. aircraft according to claim 1, which loosens tubular rivet, removes device, it is characterised in that：The support system includes
N number of pipe（17）, be respectively arranged at pipe（17）The thread head III of upper and lower ends（18）And thread head IV（19）, bearing pin（22）With
And pass through screw II（25）It is installed on bearing pin（22）The rubber feet of lower end（24）, tapered sleeve（20）It is plugged in pipe（17）It is interior, pin
Axle（22）Through tapered sleeve（20）After be plugged in pipe（17）In, spring（23）It is set in pipe（17）In, its upper end and pipe
（17）It is in contact, its lower end and bearing pin（22）It is in contact, nut（21）It is set in bearing pin（22）Outside and it is combined on thread head IV
（19）On, the pipe（17）Upper end passes through thread head III（18）Pedestal lower end is combined on vertically, works as nut（21）When screwing, cone
Set（20）By bearing pin（22）Locking is fixed, and N is the natural number more than or equal to 3.
5. aircraft as claimed in any of claims 1 to 4, which loosens tubular rivet, removes device, it is characterised in that：Institute
State adjusting nut（2）For triangle nut.
6. aircraft according to claim 2, which loosens tubular rivet, removes device, it is characterised in that：Also include being clipped on base
Seat（1）With bottom base（2）Between support（8）And it is horizontally installed to support（8）On handle（9）.
7. aircraft according to claim 3, which loosens tubular rivet, removes device, it is characterised in that：Also include passing through screw I
（13）It is fixed on groove（10）The capping of upper end（11）, the capping（11）By groove（10）Closed at upper end open.
8. aircraft according to claim 2, which loosens tubular rivet, removes device, it is characterised in that：The connecting rod（3）Upper edge
It is horizontally arranged to have circular hole（33）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710778134.XA CN107321898B (en) | 2017-09-01 | 2017-09-01 | Device is demolishd to not hard up hollow rivet of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710778134.XA CN107321898B (en) | 2017-09-01 | 2017-09-01 | Device is demolishd to not hard up hollow rivet of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107321898A true CN107321898A (en) | 2017-11-07 |
| CN107321898B CN107321898B (en) | 2023-07-07 |
Family
ID=60204208
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710778134.XA Active CN107321898B (en) | 2017-09-01 | 2017-09-01 | Device is demolishd to not hard up hollow rivet of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107321898B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110202528A (en) * | 2019-07-04 | 2019-09-06 | 山东太古飞机工程有限公司 | Auxiliary mould is removed in the spray of aircraft engine tail |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6203253B1 (en) * | 1998-11-24 | 2001-03-20 | Jamie A. Perrault | Rivet drill-out guide |
| CN101554706A (en) * | 2009-05-21 | 2009-10-14 | 南昌航空大学 | Precise grinding clamp for cutting tool |
| CN102500738A (en) * | 2011-11-18 | 2012-06-20 | 哈尔滨飞机工业集团有限责任公司 | Blind rivet disassembling tool and disassembling method |
| CN106001376A (en) * | 2016-08-15 | 2016-10-12 | 山东太古飞机工程有限公司 | Detaching device of loosened rivet on edge of aircraft laminate reinforcing structure |
| CN106180813A (en) * | 2016-08-26 | 2016-12-07 | 山东太古飞机工程有限公司 | Aircraft thin plate counter sink topping machanism |
| CN207272085U (en) * | 2017-09-01 | 2018-04-27 | 山东太古飞机工程有限公司 | A kind of aircraft loosens tubular rivet and removes device |
-
2017
- 2017-09-01 CN CN201710778134.XA patent/CN107321898B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6203253B1 (en) * | 1998-11-24 | 2001-03-20 | Jamie A. Perrault | Rivet drill-out guide |
| CN101554706A (en) * | 2009-05-21 | 2009-10-14 | 南昌航空大学 | Precise grinding clamp for cutting tool |
| CN102500738A (en) * | 2011-11-18 | 2012-06-20 | 哈尔滨飞机工业集团有限责任公司 | Blind rivet disassembling tool and disassembling method |
| CN106001376A (en) * | 2016-08-15 | 2016-10-12 | 山东太古飞机工程有限公司 | Detaching device of loosened rivet on edge of aircraft laminate reinforcing structure |
| CN106180813A (en) * | 2016-08-26 | 2016-12-07 | 山东太古飞机工程有限公司 | Aircraft thin plate counter sink topping machanism |
| CN207272085U (en) * | 2017-09-01 | 2018-04-27 | 山东太古飞机工程有限公司 | A kind of aircraft loosens tubular rivet and removes device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110202528A (en) * | 2019-07-04 | 2019-09-06 | 山东太古飞机工程有限公司 | Auxiliary mould is removed in the spray of aircraft engine tail |
| CN110202528B (en) * | 2019-07-04 | 2023-11-17 | 山东太古飞机工程有限公司 | Auxiliary fixture for removing tail spray of aircraft engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107321898B (en) | 2023-07-07 |
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