CN104976207B - A kind of centering bolt and the method being vulcanized on aircraft mouth frame with this centering bolt - Google Patents
A kind of centering bolt and the method being vulcanized on aircraft mouth frame with this centering bolt Download PDFInfo
- Publication number
- CN104976207B CN104976207B CN201510283343.8A CN201510283343A CN104976207B CN 104976207 B CN104976207 B CN 104976207B CN 201510283343 A CN201510283343 A CN 201510283343A CN 104976207 B CN104976207 B CN 104976207B
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- Prior art keywords
- bolt
- centering
- mouth frame
- circular cone
- shank
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- 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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- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 6
- 239000000084 colloidal system Substances 0.000 claims abstract description 6
- 238000004073 vulcanization Methods 0.000 claims abstract description 5
- 238000007711 solidification Methods 0.000 claims abstract description 4
- 230000008023 solidification Effects 0.000 claims abstract description 4
- 208000004141 microcephaly Diseases 0.000 claims description 9
- 238000005486 sulfidation Methods 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 4
- 230000013011 mating Effects 0.000 claims description 4
- 230000008439 repair process Effects 0.000 claims description 4
- 238000005987 sulfurization reaction Methods 0.000 claims description 4
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 239000004519 grease Substances 0.000 claims description 3
- 235000014676 Phragmites communis Nutrition 0.000 claims 1
- 239000000203 mixture Substances 0.000 claims 1
- 239000003292 glue Substances 0.000 abstract description 9
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000004899 motility Effects 0.000 description 1
- 238000010422 painting Methods 0.000 description 1
- 238000003892 spreading Methods 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B37/00—Nuts or like thread-engaging members
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B43/00—Washers or equivalent devices; Other devices for supporting bolt-heads or nuts
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Heating, Cooling, Or Curing Plastics Or The Like In General (AREA)
- Connection Of Plates (AREA)
Abstract
The bolt the invention discloses one kind is felt relieved, this centering bolt is made up of shank of bolt, special pad, special nut, circular cone centering piece, taper spring piece and nut.The invention also discloses a kind of method that this centering bolt vulcanizes on aircraft mouth frame：Pass through aircraft mouth frame lateral opening this centering threaded screw fasteners bar major part screw rod, circular cone centering face on circular cone centering piece is adjacent to the lateral opening inner side edge of aircraft mouth frame, special pad is enclosed within shank of bolt major part screw rod and is adjacent to aircraft mouth outer frame surface, lid is passed through lateral opening being arranged on the lateral opening interior shank of bolt major part screw rod of aircraft mouth frame, special nut is contained in shank of bolt major part screw head, press conventional vulcanization process gluing on aircraft mouth frame side, special nut is tightened in rotation makes its end face compress lid, the clamping position of circular cone centering piece is subject to variation self-centering, when dismantling this centering bolt and lid after colloid solidification.Make the bondline thickness between lid and mouth frame and glue measures good control it is ensured that lid is sufficiently fitted with mouth frame.
Description
Technical field
The present invention relates to aircraft manufacturing process equipment technology field, especially relate to a kind of centering bolt.The present invention also relates to
And a kind of method that this centering bolt vulcanizes on aircraft mouth frame.
Background technology
Bolt connection is that securing member connects most common method, plain bolt with connector when being connected, due to
A variety of causes actually out-of-flatness or crooked around screw outside connector sometimes, and plain bolt inner portion is one and puts down
Face, when causing to be connected, bolt and connector surface out of plumb, make nut and pad can not fit tightly with connector surface,
Do not reach the requirement installing quality of fit.
There are a lot of mouth frames and the cooperation of lid to install on aircraft, during assembling, require sealing waterproof, the sulfuration of aircraft mouth frame is real
The important assembling link that existing fuselage water resistance requires.When aircraft mouth frame vulcanizes, after the appropriate repair of airplane hatch cover mating surface, lead to
Cross bolt lid cooperation is arranged on aircraft mouth frame, filled up between its involutory surface with glue between airplane hatch cover and mouth frame simultaneously
Gap, after glue is dried, one layer of sulfuric horizon of formation on aircraft mouth frame, this sulfuric horizon coincide with airplane hatch cover, thus reaching
Aircraft mouth frame and the sealing effectiveness of lid.Because its glue spreading method has following defect in existing aircraft mouth frame sulfidation：
（1）In aircraft mouth frame sulfidation, because glue belongs to liquid condition it is impossible to control bondline thickness in advance.Simply people
Work gluing coats aircraft mouth frame surface, by tightening the connector bolt of lid and aircraft mouth frame, so that lid is joined with aircraft mouth frame
Close and install, meet shape requirement as far as possible.
（2）Because its gluing process glue amount is uncontrollable, lead to aircraft mouth frame sulfuric horizon surface quality poor.According to existing painting
Adhesive process method, after glue forms dry glue-line, sulfuric horizon thickness is indefinite, leads to produce between lid and fuselage skin larger
Jump, it is impossible to meet aircraft theory shape requirement, for reaching fuselage appearance requirement, must adopt lid straightening method to realize profile
Jump requires, and school shape process can produce certain impact to aircraft surfaces quality.
Content of the invention
Goal of the invention：In order to solve plain bolt in bolt when being connected with connector and connector surface out of plumb
Problem, and not enough in order to solve present in existing aircraft mouth frame sulfidation, the invention provides a kind of centering bolt
And the method being vulcanized on aircraft mouth frame with this centering bolt.
Inventive technique scheme：
A kind of centering bolt, by shank of bolt, special pad, special nut, circular cone centering piece, taper spring piece and nut group
Become it is characterised in that：Described shank of bolt is the different cylindrical screw rod of two diameter, and described special pad external diameter is than common
Pad is bigger, and the requirement of its two sides is parallel, and described special nut external diameter is more bigger than plain nut, in the requirement of its biend and its screw thread
Heart line is vertical, and described circular cone centering piece is circular cone thin-walled shape, and described cone shaped spring piece is circular cone thin-walled bar ribbed, its coning angle
Slightly larger than the coning angle of circular cone centering piece, the top of described circular cone centering piece and taper spring piece is small circular plane, wherein
The heart all has circular hole, and described circular cone centering piece and taper spring piece stack and be set in shank of bolt microcephaly's spiral shell by circular hole thereon
On bar, described nut is arranged on compression taper spring piece and circular cone centering piece on shank of bolt microcephaly's screw rod, by described taper spring
The elastic force of piece holds out against circular cone centering piece so as to top small circular plane is close in the intermediate step of shank of bolt.Described centering bolt
When installing and using, its major part screw diameter requires to be slightly less than the hole of connector, the major part screw rod of described centering threaded screw fasteners bar
Through the hole of connector first and connector second, circular cone centering face on described centering bolt circular cone centering piece is adjacent to connector first
In the hole side, is set in, described special pad, the outer surface being adjacent to connected piece second on shank of bolt major part screw rod, described spy
Nut processed is arranged on shank of bolt major part screw rod, rotation tighten special nut make its end face compress special pad and connector first and
Connector second, the clamping position of described circular cone centering piece is subject to variation energy self-centering, i.e. adjust automatically shank of bolt and connector
Second surface is vertical.
A kind of method that this centering bolt vulcanizes on aircraft mouth frame, installs lid in aircraft mouth with described centering bolt
Vulcanize on frame, the thickness d of sulfuric horizon be design requirement value it is characterised in that：It comprises the following steps：
1）. it is lateral opening straight that the shank of bolt major part screw diameter of the centering bolt selected during sulfuration requires to be slightly less than aircraft mouth frame
Footpath, the lateral opening quantity of root Ju aircraft mouth frame determines the quantity of required centering bolt, the thickness root Ju design of described special pad
The thickness d of sulfuric horizon selects；
2）. with nut, circular cone centering piece and taper spring piece are fixed on shank of bolt microcephaly's spiral shell of described centering bolt
On bar；
3）. described centering threaded screw fasteners bar major part screw rod is passed through aircraft mouth frame lateral opening from interior of aircraft, by described circular cone
On centering piece, circular cone centering face is adjacent to the lateral opening inner side of aircraft mouth frame, special pad is enclosed within shank of bolt major part screw rod and is adjacent to aircraft
Mouth outer frame surface；
4）. described aircraft mouth frame all lateral opening all carry out above-mentioned operation after, coat after the installation mating surface repair of lid
Grease；
5）. described lid is arranged on the lateral opening interior shank of bolt major part screw rod of aircraft mouth frame by lateral opening, special spiral shell
Mother is contained in shank of bolt major part screw head；
6）. press conventional vulcanization process gluing on described aircraft mouth frame side；
7）. described special nut is tightened in rotation makes its end face compress lid, the clamping position stress of described circular cone centering piece
Change adjust automatically shank of bolt vertical with aircraft mouth frame and lid, make described centering bolt clamping aircraft mouth frame, special pad, glue
Body and lid；
8）. when dismantling described centering bolt and lid after colloid solidification, realize the sulfidation of aircraft mouth frame.
The beneficial effect of the invention：Bolt and company when a kind of present invention centering bolt solves sometimes bolt connection fixation
Fitting surface off plumb problem, improves the hard-wired quality of fit of bolt connection, has stronger navigability, general
Property, motility.And provide a kind of new aircraft mouth frame vulcanization process, when so that aircraft mouth frame is vulcanized between lid and aircraft mouth frame
Bondline thickness and glue measures good control it is ensured that lid is sufficiently fitted it is ensured that lid is correct with aircraft mouth frame
Installation site, improve the sealing of lid and aircraft mouth frame, reach aircraft power profile with the jump of edge skin simultaneously
Code requirement, improves aircraft surfaces quality.Improve production operation efficiency, shorten manufacturing cycle, thus improve
The economic benefit of enterprise.
Brief description
Fig. 1 is the mounting structure schematic diagram of present invention centering bolt；
Fig. 2 is the mounting structure schematic diagram that this centering bolt of the present invention vulcanizes on aircraft mouth frame；
In figure：1- shank of bolt, the special pad of 2-, 3- special nut, 4- circular cone centering piece, 5- taper spring piece, 6- nut,
7- aircraft mouth frame, 8- lid, 9- sulfuric horizon.
Specific embodiment
Below in conjunction with the accompanying drawings and specific embodiment is described in further detail to the present invention.
As shown in Figure 1, a kind of centering bolt, by shank of bolt 1, special pad 2, special nut 3, circular cone centering piece 4,
Taper spring piece 5 and nut 6 form, and described shank of bolt 1 is the different cylindrical screw rod of two diameter, described special pad
2 external diameters are more bigger than conventional pads, and the requirement of its two sides is parallel, and described special nut 3 external diameter is more bigger than plain nut, and its biend will
Ask vertical with its thread center's line, described circular cone centering piece 4 is circular cone thin-walled shape, its coning angle is 100 degree of -120 degree, described circle
Cone spring leaf 5 is circular cone thin-walled bar ribbed, and its coning angle is slightly larger than the coning angle of circular cone centering piece 4, described circular cone centering piece 4 He
The top of taper spring piece 5 is small circular plane, and its center all has circular hole, described circular cone centering piece 4 and taper spring piece 5
Stack and be set on shank of bolt 1 microcephaly's screw rod by circular hole thereon, described nut 6 is arranged on shank of bolt 1 microcephaly's screw rod
Compression taper spring piece 5 and circular cone centering piece 4, the elastic force by described taper spring piece 5 holds out against circular cone centering piece 4 so as to top
Small circular plane is close in the intermediate step of shank of bolt 1.When described centering bolt is installed and used, its major part screw diameter requires slightly
Less than the hole of connector, the shank of bolt 1 major part screw rod of described centering bolt is passed through the hole of connector first and connector second, by institute
State the in the hole side that circular cone centering face on centering bolt circular cone centering piece 4 is adjacent to connector first, described special pad 2 is set in spiral shell
The outer surface of connected piece second is adjacent on tightening latch 1 major part screw rod, described special nut 3 is arranged on shank of bolt 1 major part screw rod,
Special nut 3 is tightened in rotation makes its end face compress special pad 2 and connector first and connector second, bolt circular cone centering piece of feeling relieved
4 clamping position is subject to variation energy self-centering, and that is, adjust automatically shank of bolt 1 is vertical with connector second surface.
As shown in Figure 2, a kind of method that this centering bolt vulcanizes on aircraft mouth frame, with this centering bolt installing port
Lid 8 is vulcanized on aircraft mouth frame 7, and the thickness d of sulfuric horizon 9 is design requirement value, and it comprises the following steps：
1）. it is lateral opening straight that the shank of bolt 1 major part screw diameter of the centering bolt selected during sulfuration requires to be slightly less than aircraft mouth frame 7
Footpath, the lateral opening quantity of root Ju aircraft mouth frame 7 determines the quantity of required centering bolt, the thickness root Ju design of this special pad 2
The thickness d of sulfuric horizon 9 selects；
2）. with nut 6, circular cone centering piece 4 and taper spring piece 5 are fixed on the shank of bolt 1 of described centering bolt
On microcephaly's screw rod；
3）. described centering threaded screw fasteners bar 1 major part screw rod is passed through aircraft mouth frame 7 lateral opening from interior of aircraft, by described circle
On cone centering piece 4, circular cone centering face is adjacent to the lateral opening inner side of aircraft mouth frame 7, and special pad 2 is enclosed within patch on shank of bolt 1 major part screw rod
Tight aircraft mouth frame 7 outer surface；
4）. described aircraft mouth frame 7 all lateral opening all carry out above-mentioned operation after, applying after the installation mating surface repair of lid 8
Upper grease；
5）. described lid 8 is arranged on the lateral opening interior shank of bolt 1 major part screw rod of aircraft mouth frame 7 by lateral opening, special
Nut 3 is contained in shank of bolt 1 major part screw head；
6）. press conventional vulcanization process gluing on described aircraft mouth frame 7 side；
7）. described special nut 3 is tightened in rotation makes its end face compress lid 8, and the clamping position of described circular cone centering piece 4 is subject to
Variation adjust automatically shank of bolt 1 is vertical with aircraft mouth frame 7 and lid 8, makes described centering bolt clamping aircraft mouth frame 7, special
Pad 2, colloid and lid 8；
8）. when dismantling described centering bolt and lid 8 after colloid solidification, realize the sulfidation of aircraft mouth frame 7.
Claims (4)
1. a kind of centering bolt, by shank of bolt (1), special pad (2), special nut (3), circular cone centering piece (4), circular cone bullet
Reed (5) and nut (6) composition it is characterised in that：Described shank of bolt (1) is the different cylindrical screw rod of two diameter,
Described special pad (2) external diameter is more bigger than conventional pads, and the requirement of its two sides is parallel, and described special nut (3) external diameter is than common spiral shell
Female bigger, the requirement of its biend is vertical with its thread center's line, and described circular cone centering piece (4) is circular cone thin-walled shape, described circular cone
Spring leaf (5) is circular cone thin-walled bar ribbed, and the top of described circular cone centering piece (4) and taper spring piece (5) is small circular and puts down
Face, its center all has circular hole, and described circular cone centering piece (4) and taper spring piece (5) stack sheathed by circular hole thereon
On shank of bolt (1) microcephaly's screw rod, described nut (6) be arranged on shank of bolt (1) microcephaly's screw rod compression taper spring piece (5) and
Circular cone centering piece (4), the elastic force by described taper spring piece (5) holds out against circular cone centering piece (4) so as to top small circular plane is tight
In the intermediate step of patch shank of bolt (1).
2. a kind of centering bolt described in a Ju claim 1 it is characterised in that：Described circular cone centering piece coning angle be 100 degree-
120 degree, the coning angle of described taper spring piece (5) is slightly larger than the coning angle of circular cone centering piece (4).
3. a kind of centering bolt described in a Ju claim 1 it is characterised in that：The card of described centering bolt circular cone centering piece (4)
Tight position is subject to variation energy self-centering.
4. the method that the centering bolt described in a kind of use claim 1,2 or 3 vulcanizes on aircraft mouth frame, with this centering bolt peace
Dress lid (8) is vulcanized on aircraft mouth frame (7), the thickness d of sulfuric horizon (9) be design requirement value it is characterised in that：It wraps
Include following steps：
1）. it is lateral opening straight that shank of bolt (1) the major part screw diameter requirement of the centering bolt selected during sulfuration is slightly less than aircraft mouth frame (7)
Footpath, the lateral opening quantity of root Ju aircraft mouth frame (7) determines the quantity of required centering bolt, the thickness root Ju design institute of special pad (2)
The thickness d needing sulfuric horizon (9) selects；
2）. with nut (6), circular cone centering piece (4) and taper spring piece (5) are fixed on the shank of bolt of described centering bolt
(1) on microcephaly's screw rod；
3）. described centering threaded screw fasteners bar (1) major part screw rod is passed through aircraft mouth frame (7) lateral opening from interior of aircraft, by described circle
Cone centering piece (4) upper circular cone centering face is adjacent to the lateral opening inner side of aircraft mouth frame (7), and special pad (2) is enclosed within shank of bolt (1) major part
Aircraft mouth frame (7) outer surface is adjacent on screw rod；
4）. described aircraft mouth frame (7) all lateral opening all carry out above-mentioned operation after, applying after the installation mating surface repair of lid (8)
Upper grease；
5）. described lid (8) is arranged on lateral opening interior shank of bolt (1) the major part screw rod of aircraft mouth frame (7) by lateral opening, special
Nut (3) processed is contained in shank of bolt (1) major part screw head；
6）. press conventional vulcanization process gluing on described aircraft mouth frame (7) side；
7）. described special nut (3) is tightened in rotation makes its end face compress lid (8), the clamping position of described circular cone centering piece (4)
Vertical with aircraft mouth frame (7) and lid (8) by variation adjust automatically shank of bolt (1), make described centering bolt clamping aircraft mouth
Frame (7), special pad (2), colloid and lid (8)；
8）. when dismantling described centering bolt and lid (8) after colloid solidification, realize the sulfidation of aircraft mouth frame (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510283343.8A CN104976207B (en) | 2015-05-29 | 2015-05-29 | A kind of centering bolt and the method being vulcanized on aircraft mouth frame with this centering bolt |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510283343.8A CN104976207B (en) | 2015-05-29 | 2015-05-29 | A kind of centering bolt and the method being vulcanized on aircraft mouth frame with this centering bolt |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104976207A CN104976207A (en) | 2015-10-14 |
| CN104976207B true CN104976207B (en) | 2017-03-08 |
Family
ID=54273034
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510283343.8A Active CN104976207B (en) | 2015-05-29 | 2015-05-29 | A kind of centering bolt and the method being vulcanized on aircraft mouth frame with this centering bolt |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104976207B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736553A (en) * | 2016-04-08 | 2016-07-06 | 常州长江玻璃有限公司 | Self-locking connecting structure of hasp and connecting bar of emergency escape window |
| CN106194961A (en) * | 2016-09-23 | 2016-12-07 | 江西洪都航空工业集团有限责任公司 | A kind of below deck equipment that is applicable to hangs the nut installed |
| CN109421940B (en) * | 2017-08-22 | 2022-01-25 | 成都飞机工业（集团）有限责任公司 | Method for pressing sealing rubber gasket on opening frame of sealed oil tank |
| CN110281434A (en) * | 2018-03-19 | 2019-09-27 | 成都飞机工业（集团）有限责任公司 | A kind of rubber mat vulcanization in situ method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB192273A (en) * | 1922-01-23 | 1923-02-01 | Edward Ramsay Green | Improvements in or relating to devices for centering and setting up work in machine tools |
| CN201908925U (en) * | 2010-12-02 | 2011-07-27 | 贵州航太精密制造有限公司 | Quick release lock used on airplane hatch cover |
| CN102359466A (en) * | 2011-09-16 | 2012-02-22 | 贵州航太精密制造有限公司 | Stopper ring used on quick-release fastener |
| CN104265745A (en) * | 2014-09-11 | 2015-01-07 | 贵州航太精密制造有限公司 | High-intensity quick-disassembly fastener for airplane covering cap |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2348903A1 (en) * | 1973-09-28 | 1975-04-24 | Siemens Ag | Device for centering bolt in slot - comprises washer with tabs for engaging ends of slot |
-
2015
- 2015-05-29 CN CN201510283343.8A patent/CN104976207B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB192273A (en) * | 1922-01-23 | 1923-02-01 | Edward Ramsay Green | Improvements in or relating to devices for centering and setting up work in machine tools |
| CN201908925U (en) * | 2010-12-02 | 2011-07-27 | 贵州航太精密制造有限公司 | Quick release lock used on airplane hatch cover |
| CN102359466A (en) * | 2011-09-16 | 2012-02-22 | 贵州航太精密制造有限公司 | Stopper ring used on quick-release fastener |
| CN104265745A (en) * | 2014-09-11 | 2015-01-07 | 贵州航太精密制造有限公司 | High-intensity quick-disassembly fastener for airplane covering cap |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104976207A (en) | 2015-10-14 |
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