CN109504995A - A kind of preparation method of aviation fasteners - Google Patents
A kind of preparation method of aviation fasteners Download PDFInfo
- Publication number
- CN109504995A CN109504995A CN201811459932.7A CN201811459932A CN109504995A CN 109504995 A CN109504995 A CN 109504995A CN 201811459932 A CN201811459932 A CN 201811459932A CN 109504995 A CN109504995 A CN 109504995A
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- Prior art keywords
- coating
- nut
- bolt
- preparation
- nickel
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- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
- C25D11/02—Anodisation
- C25D11/024—Anodisation under pulsed or modulated current or potential
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
- C25D11/02—Anodisation
- C25D11/26—Anodisation of refractory metals or alloys based thereon
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D3/00—Electroplating: Baths therefor
- C25D3/02—Electroplating: Baths therefor from solutions
- C25D3/12—Electroplating: Baths therefor from solutions of nickel or cobalt
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D3/00—Electroplating: Baths therefor
- C25D3/02—Electroplating: Baths therefor from solutions
- C25D3/38—Electroplating: Baths therefor from solutions of copper
- C25D3/40—Electroplating: Baths therefor from solutions of copper from cyanide baths, e.g. with Cu+
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D7/00—Electroplating characterised by the article coated
- C25D7/003—Threaded pieces, e.g. bolts or nuts
Abstract
The present invention relates to a kind of preparation methods of aviation fasteners.The preparation method includes the preparation of matched screw bolt and nut；Anodized is carried out to titanium alloy bolt matrix, anodic oxide coating is formed on the surface of titanium alloy bolt matrix after anodized, prepares molybdenum disulfide coating on anodic oxide coating to get the bolt；Nickel preplating is carried out to stainless steel basal body of nut, forms nickel coating on the surface of stainless steel basal body of nut after nickel preplating；Copper facing is carried out on nickel coating, forms copper coating on the surface of nickel coating after copper facing；Molybdenum disulfide coating is prepared on copper coating to get the nut.The preparation method of aviation fasteners provided by the invention, preparation process is simple, the binding force of coated layer is good on bolt and nut, reasonable lubricating system is separately designed for the screw bolt and nut of unlike material, substantially reduce unsmooth possibility when screw thread pair screws, reliability of the fastener in assembly, maintenance is significantly improved, is improved work efficiency.
Description
Technical field
The invention belongs to the manufacturing fields of fastener, and in particular to a kind of preparation method of aviation fasteners.
Background technique
Fastener is widely distributed aboard, in the fuselage and machine of the typical binary channels aircraft (such as A330/A340) of a frame
On the wing, there are about 400,000 for the quantity of the fasteners such as bolt, nut, rivet of a variety of materials and structure, wherein using relatively broad
Fastener auxiliary connection be titanium alloy bolt and stainless steel supporting plate self-lock nut.
In the maintenance of aircraft I& M, need to install or remove fastener auxiliary connection.In work at this stage
Journey in practice, can greater probability using titanium alloy bolt and stainless steel supporting plate self-lock nut as the typical fasteners auxiliary connection of representative
It is unsmooth that threaded engagement occurs in ground, even bolt thread and nut thread mutually " killing " the phenomenon that, assemble or safeguard to aircraft
Bring certain difficulty.
Summary of the invention
The purpose of the present invention is to provide a kind of preparation methods of aviation fasteners, for solving existing fastener auxiliary connection
The unsmooth problem being easy to appear when screwing.
To achieve the above object, technical solution used by the preparation method of aviation fasteners of the invention is:
A kind of preparation method of aviation fasteners, the preparation including matched screw bolt and nut；
The preparation of bolt is the following steps are included: carry out anodized, anodized to titanium alloy bolt matrix
Form anodic oxide coating on the surface of titanium alloy bolt matrix afterwards, prepared on anodic oxide coating molybdenum disulfide coating to get
The bolt；
The preparation of nut is the following steps are included: to stainless steel basal body of nut progress nickel preplating, in stainless steel spiral shell after nickel preplating
Nickel coating is formed on the surface of female matrix；Copper facing is carried out on nickel coating, forms copper coating on the surface of nickel coating after copper facing；
Molybdenum disulfide coating is prepared on copper coating to get the nut.
The preparation method of aviation fasteners provided by the invention, preparation process is simple, the knot of coated layer on bolt and nut
It is good with joint efforts, reasonable lubricating system is separately designed for the screw bolt and nut of unlike material, when substantially reducing screw thread pair and screwing
Unsmooth possibility, significantly improve fastener assembly, maintenance when reliability, improve work efficiency.
To obtain preferable anodic oxidation effect, it is preferred that the anodic oxidation is pulse anodic oxidation.
For the stability and reliability for further increasing pulse-anodization Treatment process, it is preferred that pulse anodic oxidation
Used working solution is composed of the following components: sulfuric acid 300-420g/L, phosphatase 11 0-20g/L, and solvent is water.
Further to obtain fine and close, uniform anodic oxide coating, it is preferred that when pulse-anodization Treatment, working solution
Temperature is 0-10 DEG C, current density 2-10A/dm2, the pulse-anodization Treatment time is 10-30min, voltage 100-
180V；The pulse turn-on time of pulse current be 0.1-2.0ms, the inter-train pause time be 0.5-5.0ms, pulse frequency 1Hz,
Impulse amplitude is 5-25%.
Detailed description of the invention
Fig. 1 is the coating schematic diagram of a layer structure of bolt in the preparation method embodiment 1 of aviation fasteners of the invention；
Fig. 2 is the coating schematic diagram of a layer structure of nut in the preparation method embodiment 1 of aviation fasteners of the invention；
In figure, 1- bolt body, 2- anodic oxide coating, 3- molybdenum disulfide coating, 4- nut body, 5- nickel coating, 6- copper
Coating.
Specific embodiment
Embodiments of the present invention are described further with reference to the accompanying drawing.
The present invention is mainly by preferred, screw thread pair when reducing assembly, maintenance to nut, bolt surface lubricating system
Unsmooth possibility, raising screw reliability.
Related art can refer to the nickel plating on stainless steel basal body of nut surface, copper plating treatment, to obtain preferable table
Face coating effect, it is preferred that the composition of nickel-plating liquid used in Ni-Speed are as follows: NiSO4·7H2O260-320g/L, hydrochloric acid 180-
220g/L, solvent are deionized water；The mass concentration of hydrochloric acid is 36-38%；When nickel preplating, temperature is room temperature；Current density is
5-10A/dm2；When Nickel Plating Treatment, no power 1-4min, electronickelling 4-5min, anode material are NY1 or NY2.
The composition of copper plating bath used in copper facing process are as follows: Cu2CN 35-70g/L, NaCN 12-20g/L, solvent be go from
Sub- water；When copper facing, temperature is 15-40 DEG C, current density 0.5-1.5A/dm2, the processing time is 55-70min, anode material
For T1 or T2.
Feature is had following structure using aviation fasteners prepared by the above method:
Aviation fasteners include matched screw bolt and nut, the bolt include titanium alloy bolt matrix and from inside to outside according to
The secondary anodic oxide coating being arranged on titanium alloy bolt matrix, molybdenum disulfide coating, the nut include stainless steel basal body of nut
Nickel coating, copper coating and the molybdenum disulfide coating being successively set in stainless steel basal body of nut from inside to outside.
It is improved for titanium alloy bolt matrix using the surface treatment scheme of anodic oxidation cooperation molybdenum disulfide coating
The binding force of molybdenum disulfide coating and matrix improves the hardness and wearability of bolt；From improve the lubricity of bolt, hardness and
Set out in terms of the comprehensive performances such as wearability, it is preferred that on the titanium alloy bolt matrix, anodic oxide coating with a thickness of 3-5 μm,
Molybdenum disulfide coating with a thickness of 5-12 μm.
For stainless steel basal body of nut, the lubrication strategies of molybdenum disulfide are applied using nickel preplating, copper facing cooperation, on the one hand can be protected
The binding force of each coated layer structure and matrix is demonstrate,proved, on the other hand, copper coating plasticity is good, can significantly reduce coefficient of friction, reduce and rub
Power is wiped, can cooperate with the good molybdenum disulfide coating of lubricant effect improves the unsmooth problem occurred when screw thread pair screws；From improvement
It sets out in terms of the comprehensive performances such as lubricity, the hardness of nut, it is preferred that in the stainless steel basal body of nut, the thickness of nickel coating
Be 1-3 μm, copper coating with a thickness of 5-8 μm, molybdenum disulfide coating with a thickness of 5-12 μm.
Existing titanium alloy for fastening piece material can be used in bolt matrix, from the intensity for improving bolt, titanium alloy spiral shell
Titanium alloy used in bolt matrix is Ti6Al4V, which after heat treatment can reach σb>=1100MPa, τb≥670MPa。
Conventional fasteners stainless steel material can be used in basal body of nut, goes out in terms of the hardness of raising nut, bearing capacity
Hair, it is preferred that the model A286 of stainless steel used in stainless steel basal body of nut, the type stainless steel material after heat treatment hardness
Not less than 30HRC, meet the bearing capacity of 900MPa grade.Nut can be the self-locking nut of various specifications and model.
Following embodiment is illustrated by taking typical airline fastener auxiliary connection as an example, wherein model/specification of nut is
HB7364/MJ6 × 1, model/specification of bolt are HB6563/6 × 24.
The preparation method embodiment 1 of aviation fasteners of the invention, preparing respectively including screw bolt and nut, wherein spiral shell
Bolt is prepared using following steps:
1) titanium alloy bolt body is successively carried out to oil removing, pickling pretreatment, then carries out pulse-anodization Treatment, arteries and veins
Rush working solution used in anodized to consist of the following compositions: sulfuric acid 370g/L, phosphatase 11 5g/L, solvent are deionization
Water；Sulfuric acid, phosphoric acid are commercially available finished product, and the mass concentration of sulfuric acid is 98%, and the mass concentration of phosphoric acid is 85%；Pulse anodic oxidation
When processing, the temperature of working solution is 5 DEG C, current density 6A/dm2, the pulse-anodization Treatment time is 20min, and voltage is
140V；The pulse turn-on time of pulse current is 1.0ms, and the inter-train pause time is 2.0ms, pulse frequency 1Hz, impulse amplitude
It is 15%；Anodic oxidation bolt is obtained after pulse-anodization Treatment.
2) molybdenum disulfide coating is prepared on anodic oxidation bolt with molybdenum disulfide coating, is carried out for the first time with spraying method
Coating is placed at room temperature for coating surface drying after coating for the first time, is then placed in baking oven and is carried out precuring；Is carried out after precuring
Then secondary coating carries out final solidification, after reaching curing time, take out product, that is, complete the preparation of molybdenum disulfide coating.
Molybdenum disulfide coating is commercially available conventional products, and selection Shenyang Hangda Technology Co., Ltd produces model in embodiment
The molybdenum disulfide coating of HD7352 can refer to coating using process specification and determine the technological parameters such as spray parameters, curing time.
Nut is prepared using following steps:
A) nut body is subjected to oil removing, pickling, activation, cleaning pretreatment, then carries out nickel preplating；Nickel preplating process institute
The composition of nickel-plating liquid are as follows: NiSO4·7H2O 260g/L, hydrochloric acid 180g/L, solvent are deionized water；The mass concentration of hydrochloric acid
It is 38%；When nickel preplating, temperature is room temperature；Current density is 5A/dm2；When Nickel Plating Treatment, no power 1min, electronickelling 4min,
Anode material is NY1；It is washed after nickel preplating, is dry, obtaining nickel plating nut；
B) nickel plating nut is subjected to copper facing, the composition of copper plating bath used in copper facing process are as follows: Cu2CN 35g/L, NaCN
12g/L, solvent are deionized water；When copper facing, temperature is 25 DEG C, current density 0.5A/dm2, the processing time is 70min, sun
Pole material T1；It washed, dried after copper facing, obtain plating copper nut；
C) molybdenum disulfide coating is prepared on plating copper nut with molybdenum disulfide coating, first time painting is carried out with spraying method
It covers, is placed at room temperature for after coating for the first time to coating surface drying, be then placed in baking oven and carry out precuring；Second is carried out after precuring
Then secondary coating carries out final solidification, after reaching curing time, take out product, that is, complete the preparation of molybdenum disulfide coating.Two
Molybdenum sulfide coating is commercially available conventional products, and selection Shenyang Hangda Technology Co., Ltd produces model HD7352 in embodiment
Molybdenum disulfide coating, can refer to coating using process specification and determine the technological parameters such as spray parameters, curing time.
In the embodiment, the coating schematic diagram of a layer structure of bolt as shown in Figure 1, include bolt body 1 and from inside to outside according to
The secondary anodic oxide coating 2 and molybdenum disulfide coating 3 being arranged on bolt body 1, bolt body 1 are titanium alloy ti6al4v material,
Anodic oxide coating 2 with a thickness of 4 μm, molybdenum disulfide coating 3 with a thickness of 8 μm.Coating schematic diagram of a layer structure such as Fig. 2 institute of nut
Show, nickel coating 5, copper coating 6 and the molybdenum disulfide being successively set on nut body 4 including nut body 4 and from inside to outside apply
Layer 3, nut body 4 are A286 material, nickel coating 5 with a thickness of 2 μm, copper coating 6 with a thickness of 7 μm, molybdenum disulfide coating 3
With a thickness of 8 μm.
The preparation method embodiment 2 of aviation fasteners of the invention, preparing respectively including screw bolt and nut, wherein spiral shell
Bolt is prepared using following steps:
1) titanium alloy bolt body is successively carried out to oil removing, pickling pretreatment, then carries out pulse-anodization Treatment, arteries and veins
Rush working solution used in anodized to consist of the following compositions: sulfuric acid 300g/L, phosphatase 11 0g/L, solvent are deionization
Water；Sulfuric acid, phosphoric acid are commercially available finished product, and the mass concentration of sulfuric acid is 98%, and the mass concentration of phosphoric acid is 85%；Pulse anodic oxidation
When processing, the temperature of working solution is 0 DEG C, current density 3A/dm2, the pulse-anodization Treatment time is 10min, and voltage is
120V；The pulse turn-on time of pulse current is 0.5ms, and the inter-train pause time is 1.0ms, pulse frequency 1Hz, impulse amplitude
It is 10%；Anodic oxidation bolt is obtained after pulse-anodization Treatment.
2) molybdenum disulfide coating is prepared on anodic oxidation bolt with molybdenum disulfide coating.
Nut is prepared using following steps:
A) nut body is subjected to oil removing, pickling, activation, cleaning pretreatment, then carries out nickel preplating；Nickel preplating process institute
The composition of nickel-plating liquid are as follows: NiSO4·7H2O 320g/L, hydrochloric acid 220g/L, solvent are deionized water；The mass concentration of hydrochloric acid
It is 38%；When nickel preplating, temperature is room temperature；Current density is 10A/dm2；When Nickel Plating Treatment, no power 4min, electronickelling
4min, anode material NY2；It is washed after nickel preplating, is dry, obtaining nickel plating nut；
B) nickel plating nut is subjected to copper facing, the composition of copper plating bath used in copper facing process are as follows: Cu2CN 70g/L, NaCN
20g/L, solvent are deionized water；When copper facing, temperature is 40 DEG C, current density 1.5A/dm2, the processing time is 55min, sun
Pole material is T2；It washed, dried after copper facing, obtain plating copper nut；
C) molybdenum disulfide coating is prepared on plating copper nut with molybdenum disulfide coating.
In the embodiment, anodic oxide coating that bolt includes bolt body and is successively set on bolt body from inside to outside
With molybdenum disulfide coating, bolt body is titanium alloy ti6al4v material, anodic oxide coating with a thickness of 3 μm, molybdenum disulfide coating
With a thickness of 6 μm.Nickel coating, the copper coating and two that nut includes nut body and is successively set on nut body from inside to outside
Vulcanize molybdenum coating, nut body is A286 material, nickel coating with a thickness of 1 μm, copper coating with a thickness of 5 μm, molybdenum disulfide applies
Layer with a thickness of 6 μm.
The preparation method embodiment 3 of aviation fasteners of the invention, preparing respectively including screw bolt and nut, wherein spiral shell
Bolt is prepared using following steps:
1) titanium alloy bolt body is successively carried out to oil removing, pickling pretreatment, then carries out pulse-anodization Treatment, arteries and veins
Rush working solution used in anodized to consist of the following compositions: sulfuric acid 420g/L, phosphoric acid 20g/L, solvent are deionization
Water；Sulfuric acid, phosphoric acid are commercially available finished product, and the mass concentration of sulfuric acid is 98%, and the mass concentration of phosphoric acid is 85%；Pulse anodic oxidation
When processing, the temperature of working solution is 10 DEG C, current density 10A/dm2, the pulse-anodization Treatment time is 30min, voltage
For 180V；The pulse turn-on time of pulse current is 2.0ms, and the inter-train pause time is 5.0ms, pulse frequency 1Hz, pulse width
Degree is 25%；Anodic oxidation bolt is obtained after pulse-anodization Treatment.
2) molybdenum disulfide coating is prepared on anodic oxidation bolt with molybdenum disulfide coating.
Nut is prepared using following steps:
A) nut body is subjected to oil removing, pickling, activation, cleaning pretreatment, then carries out nickel preplating；Nickel preplating process institute
The composition of nickel-plating liquid are as follows: NiSO4·7H2O 300g/L, hydrochloric acid 200g/L, solvent are deionized water；The mass concentration of hydrochloric acid
It is 38%；When nickel preplating, temperature is room temperature；Current density is 7A/dm2；When Nickel Plating Treatment, no power 2min, electronickelling 5min,
Anode material is NY1；It is washed after nickel preplating, is dry, obtaining nickel plating nut；
B) nickel plating nut is subjected to copper facing, the composition of copper plating bath used in copper facing process are as follows: Cu2CN 55g/L, NaCN
16g/L, solvent are deionized water；When copper facing, temperature is 30 DEG C, current density 1.0A/dm2, the processing time is 65min, sun
Pole material is T1；It washed, dried after copper facing, obtain plating copper nut；
C) molybdenum disulfide coating is prepared on plating copper nut with molybdenum disulfide coating.
In the embodiment, anodic oxide coating that bolt includes bolt body and is successively set on bolt body from inside to outside
With molybdenum disulfide coating, bolt body is titanium alloy ti6al4v material, anodic oxide coating with a thickness of 5 μm, molybdenum disulfide coating
With a thickness of 12 μm.Nut include nut body and be successively set on nut body from inside to outside nickel coating, copper coating and
Molybdenum disulfide coating, nut body are A286 material, nickel coating with a thickness of 3 μm, copper coating with a thickness of 8 μm, molybdenum disulfide
Coating with a thickness of 12 μm.
Comparative example 1
The aviation fasteners of comparative example, bolt, the specification of nut, basic material are same as Example 1, and difference is only that,
Bolt includes bolt body, and molybdenum disulfide coating is provided only on bolt body, and bolt body is titanium alloy ti6al4v material,
Molybdenum disulfide coating with a thickness of 12 μm.Nut includes nut body, and molybdenum disulfide coating, nut are provided only on nut body
Ontology be A286 material, molybdenum disulfide coating with a thickness of 12 μm.
Test example
This test example detects the connection reliability of the fastener auxiliary connection of each embodiment and comparative example, is assembled using aircraft existing
The pneumtic impact wrench of the common same model in field carries out installation test and screws reliability to evaluate it, and the results are shown in Table 1.
The connection reliability of the fastener auxiliary connection of each embodiment and comparative example of table 1
| Project | Embodiment 1 | Embodiment 2 | Embodiment 3 | Comparative example 1 |
| It tests installation number (part) | 100 | 100 | 100 | 100 |
| Repeated disassembled and assembled number | 10 | 10 | 10 | 10 |
| The mounting torque (Nm) of application is tightened every time | 7.0 | 7.0 | 7.0 | 7.0 |
| It installs revolving speed (r/min) | 150 | 150 | 150 | 150 |
| Bolt, nut " kill " quantity (part) | 0 | 0 | 0 | 3 |
| Bolt, nut " kill " ratio (%) | 0 | 0 | 0 | 3% |
| Unsmooth quantity (part) | 0 | 1 | 0 | 14 |
| Unsmooth ratio (%) | 0 | 1% | 0 | 14% |
| Unqualified (unsmooth plus kill) ratio (%) | 0 | 1% | 0 | 17% |
By the testing result of table 1 it is found that the screw bolt and nut using embodiment matches, assembly, maintenance are substantially reduced
When screw thread pair unsmooth possibility, effectively increase installation, the maintenance reliability of fastener.
Claims (4)
1. a kind of preparation method of aviation fasteners, which is characterized in that the preparation including matched screw bolt and nut；
The preparation of bolt the following steps are included: carry out anodized to titanium alloy bolt matrix, after anodized
Anodic oxide coating is formed on the surface of titanium alloy bolt matrix, prepares molybdenum disulfide coating on anodic oxide coating to get described
Bolt；
The preparation of nut is the following steps are included: to stainless steel basal body of nut progress nickel preplating, in stainless steel nut base after nickel preplating
Nickel coating is formed on the surface of body；Copper facing is carried out on nickel coating, forms copper coating on the surface of nickel coating after copper facing；In copper
Molybdenum disulfide coating is prepared on coating to get the nut.
2. the preparation method of aviation fasteners as described in claim 1, which is characterized in that the anodic oxidation is pulsed anode
Oxidation.
3. the preparation method of aviation fasteners as claimed in claim 2, which is characterized in that work used in pulse anodic oxidation
It is composed of the following components to make liquid: sulfuric acid 300-420g/L, phosphatase 11 0-20g/L, solvent are water.
4. the preparation method of aviation fasteners as claimed in claim 2, which is characterized in that when pulse-anodization Treatment, work
The temperature for making liquid is 0-10 DEG C, current density 2-10A/dm2, the pulse-anodization Treatment time is 10-30min, and voltage is
100-180V；The pulse turn-on time of pulse current is 0.1-2.0ms, and the inter-train pause time is 0.5-5.0ms, and pulse frequency is
1Hz, impulse amplitude 5-25%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811459932.7A CN109504995B (en) | 2018-11-30 | 2018-11-30 | Preparation method of aviation fastener |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811459932.7A CN109504995B (en) | 2018-11-30 | 2018-11-30 | Preparation method of aviation fastener |
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| Publication Number | Publication Date |
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| CN109504995A true CN109504995A (en) | 2019-03-22 |
| CN109504995B CN109504995B (en) | 2020-07-28 |
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| CN201811459932.7A Active CN109504995B (en) | 2018-11-30 | 2018-11-30 | Preparation method of aviation fastener |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3568746A (en) * | 1967-02-06 | 1971-03-09 | Amerace Esna Corp | Self-locking threaded fastener |
| CN202140403U (en) * | 2011-07-12 | 2012-02-08 | 航天精工有限公司 | Clamping sleeve thread connection component capable of preventing looseness and seizure |
| CN104818501A (en) * | 2015-04-27 | 2015-08-05 | 模德模具(东莞)有限公司 | Nickel-Teflon coating machining process applied to screws and nuts |
| CN106086990A (en) * | 2016-08-04 | 2016-11-09 | 北京工业大学 | A kind of method of the immobilized molybdenum bisuphide of porous titania thin films |
| JP2017155325A (en) * | 2016-03-04 | 2017-09-07 | 張家港阿斯恩表面工程科技有限公司 | Method of manufacturing slack-stopping washer for bolt and nut |
-
2018
- 2018-11-30 CN CN201811459932.7A patent/CN109504995B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3568746A (en) * | 1967-02-06 | 1971-03-09 | Amerace Esna Corp | Self-locking threaded fastener |
| CN202140403U (en) * | 2011-07-12 | 2012-02-08 | 航天精工有限公司 | Clamping sleeve thread connection component capable of preventing looseness and seizure |
| CN104818501A (en) * | 2015-04-27 | 2015-08-05 | 模德模具(东莞)有限公司 | Nickel-Teflon coating machining process applied to screws and nuts |
| JP2017155325A (en) * | 2016-03-04 | 2017-09-07 | 張家港阿斯恩表面工程科技有限公司 | Method of manufacturing slack-stopping washer for bolt and nut |
| CN106086990A (en) * | 2016-08-04 | 2016-11-09 | 北京工业大学 | A kind of method of the immobilized molybdenum bisuphide of porous titania thin films |
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| Publication number | Publication date |
|---|---|
| CN109504995B (en) | 2020-07-28 |
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