CN112478196B - Airplane bolt fastening and detecting method - Google Patents
Airplane bolt fastening and detecting method Download PDFInfo
- Publication number
- CN112478196B CN112478196B CN202011333510.2A CN202011333510A CN112478196B CN 112478196 B CN112478196 B CN 112478196B CN 202011333510 A CN202011333510 A CN 202011333510A CN 112478196 B CN112478196 B CN 112478196B
- Authority
- CN
- China
- Prior art keywords
- silica gel
- color
- rope
- waterproof layer
- layer
- 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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Links
- 238000000034 method Methods 0.000 title claims abstract description 9
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 31
- 239000000741 silica gel Substances 0.000 claims description 31
- 229910002027 silica gel Inorganic materials 0.000 claims description 31
- 230000008859 change Effects 0.000 claims description 10
- 229920001684 low density polyethylene Polymers 0.000 claims description 5
- 239000004702 low-density polyethylene Substances 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- 230000009467 reduction Effects 0.000 claims description 2
- 239000007921 spray Substances 0.000 claims description 2
- 229960001866 silicon dioxide Drugs 0.000 claims 8
- 238000001514 detection method Methods 0.000 abstract description 9
- 230000007547 defect Effects 0.000 abstract description 3
- 229910000831 Steel Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- 239000004698 Polyethylene Substances 0.000 description 2
- 239000003595 mist Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- -1 polyethylene Polymers 0.000 description 2
- 229920000573 polyethylene Polymers 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 238000005491 wire drawing Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000002427 irreversible effect Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
-
- 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
- B64F5/60—Testing or inspecting aircraft components or systems
-
- 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
- F16B39/00—Locking of screws, bolts or nuts
- F16B39/01—Locking of screws, bolts or nuts specially adapted to prevent loosening at extreme temperatures
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
- Electric Cable Installation (AREA)
Abstract
The invention belongs to the field of airplane detection, and particularly relates to a bolt fastening and detecting method. The invention aims to overcome the defect that the nut adopting the anti-loosening rope fastening device still needs to be manually detected for a long time, and further provides an airplane bolt fastening and detecting method, so that a detector can quickly judge whether the nut is loosened.
Description
Technical Field
The invention belongs to the field of airplane detection, and particularly relates to a novel fastening material.
Background
Fastening and locking devices are often adopted on airplanes to connect a plurality of nuts, so that the nuts are restricted mutually, and the purposes of locking mutually and preventing loosening are achieved. Common fastening locking device is anti-loosening rope promptly, and its accessible adopts clockwise and anticlockwise fastening direction to adjacent nut interval for when certain nut takes place to become flexible, its adjacent nut can receive along the power of adjacent nut fastening direction more, this has just played the restriction effect to tending to produce the nut that becomes flexible.
The anti-loosening rope commonly used in the prior art is made of metal, however, the airplane often generates large jolts in the flying process, so that the nut is loosened, and a great force can be brought to the anti-loosening rope instantly, so that the anti-loosening rope deforms. The deformation of the metal material is often unrecoverable, that is, once the nut has rotated, the loosening condition is generated, and the nut cannot be recovered by itself. Therefore, even if the nuts processed by the fastening and locking device are adopted, frequent detection is still required by detection personnel to ensure flight safety.
The existing detection method is that the anti-loosening rope between every two nuts is manually shifted and matched with a force measuring device, and whether the nuts are loosened or not is judged by observing whether the anti-loosening rope deforms or not; or the nut is turned by one by manpower, which is time-consuming and labor-consuming.
Aiming at the defect that the nut adopting the anti-loosening rope fastening device still needs to be manually detected for a long time in the prior art, the invention provides the anti-loosening rope special for fastening the bolt of the airplane, so that the detection time is greatly shortened.
Disclosure of Invention
The invention aims to overcome the defect that the nut adopting the anti-loosening rope fastening device still needs to be manually detected for a long time, and further provides an airplane bolt fastening detection method, so that a detector can quickly judge whether the nut is loosened.
The above purpose of the invention is realized by the following technical scheme:
a method for fastening and detecting bolts of an airplane comprises the steps that anti-loosening ropes are connected in series to a plurality of bolts needing to be fastened outside the airplane, and forces in opposite directions of the anti-loosening ropes are applied to adjacent bolts, so that the bolts are restricted with each other;
the anti-loosening rope comprises a rope-shaped rigid locking body, a color-changing silica gel layer and a transparent waterproof layer;
the surface of the rope-shaped rigid locking layer body is provided with a groove along the axial direction of the rope-shaped rigid locking layer body;
the color-changing silica gel layer is arranged in the groove;
the transparent waterproof layer is hermetically covered on the allochroic silica gel layer so that the allochroic silica gel layer is isolated from the atmosphere; the elongation at break of the transparent waterproof layer is reduced along with the temperature reduction;
when the bolt fastening condition is detected, the area to be detected is in a humidity environment which is enough to enable the color-changing silica gel to change color, then the color-changing silica gel is observed, and if the color-changing silica gel changes color, the bolt is judged to be loosened.
Preferably, the elongation at break of the transparent waterproof layer material is less than 0.5% at a temperature of less than-30 ℃.
Optionally, the transparent waterproof layer is low density polyethylene.
Optionally, when the airplane is detected before taking off, the change of the allochroic silica gel is observed after water spray is applied to the area to be detected.
A preparation method of a special anti-loosening rope for fastening an airplane bolt comprises the following steps,
s1, obtaining a linear metal body with a groove on the surface, wherein the groove is axially arranged along the metal body;
s2, filling the groove with allochroic silica gel;
and S3, packaging the color-changing silica gel layer by using a transparent waterproof layer, so that the color-changing silica gel is not in contact with the atmosphere.
Optionally, the groove is filled with powdered allochroic silica gel.
The transparent waterproof layer can be made of low-density polyethylene.
The technical scheme of the invention has the following beneficial effects:
the aircraft often will pass low temperature cloud cover when the flight, and air humidity is great, takes place to become flexible when the nut, when leading to locking rope to take place deformation, the waterproof layer that locking rope outside covered takes place irreversible fracture, and at this moment, allochroic silica gel no longer with atmosphere isolated, but absorbs water and discolours, becomes pink by blue, and the change naked eye of this kind of colour is visible. Like this, when the measurement personnel detected, only need with the naked eye observation can to can lock the rope position of preventing loosing who takes place deformation fast, just so can in time change in order to guarantee flight safety, and can also save a large amount of check-out time.
Of course, if the airplane is detected before flying, the spraying device can be used for spraying water mist to the anti-loosening rope area, and if the anti-loosening rope deforms to cause the waterproof layer to break, the allochroic silica gel can immediately generate visible color change. Because the requirement of the allochroic silica gel on the environment is higher when the allochroic silica gel is kept dry, the color change can be observed at any time in an air humid area if the waterproof layer is broken, so that the anti-loosening rope can be replaced in time.
Detailed Description
The technical solutions of the present invention will be described clearly and completely below, and it should be apparent that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The embodiment provides an aircraft bolt fastening detection method, specifically,
the anti-loosening rope special for fastening the airplane is adopted, bolts needing to be fastened are connected in series, adjacent bolts are guaranteed to be restrained by reverse force during series connection, and one side of the anti-loosening rope containing the allochroic silica gel layer faces towards the observable direction.
The anti-loosening rope used in the embodiment comprises a rope-shaped rigid locking main body, wherein the surface of the rigid locking main body is provided with a groove along the axial direction, a color-changing silica gel layer arranged in the groove, and a transparent waterproof layer covered in a sealing manner.
Specifically, the steel wire is used as a main body, a groove along the length direction is formed in the surface of the steel wire, dry powdery allochroic silica gel is densely filled in the groove, and a transparent low-density polyethylene film is covered on the groove.
Of course, in practical application, other rigid rope-shaped materials capable of achieving the locking function can be adopted, and the arrangement of the groove can accommodate enough allochroic silica gel to achieve the visual effect. In this embodiment, the low-density polyethylene film with a covering thickness of 300 μm is used, and may be replaced with other transparent shell plastic materials satisfying the requirements of better ductility at normal temperature and reduced elongation at break at low temperature. Just so can reach when carrying out the bolt-up operation under the normal temperature, the waterproof layer remains intact, guarantees allochroic silica gel and atmospheric isolated performance, and under the low temperature environment of aircraft flight at high altitude, in case the bolt leads to becoming flexible and drive when preventing that the rope takes place to deform because of jolting etc. in case, the waterproof layer fracture for allochroic silica gel layer and steam contact, and take place to change colour, play the display action.
The anti-loosening rope provided by the embodiment is prepared by the following steps:
first, a wire anti-loosening rope for an existing aircraft is obtained. And (3) obtaining a groove on the steel wire by adopting a wire drawing die with a grooving function. For example using a diamond wire drawing die.
The obtained groove is densely filled with powdery allochroic silica gel, polyethylene glue is used for smearing the two sides of the groove, a layer of polyethylene film is covered on the groove, the groove is placed in a vacuum oven, and the temperature is kept at 90 ℃ for 3min, so that the anti-loosening rope provided by the embodiment can be obtained.
When detecting, the detection personnel only need utilize the naked eye to observe whether have the circumstances of discolouing to take place on the anti-loosening rope, can judge whether the bolt takes place to become flexible and fix a position fast. Certainly, in a particularly dry area, when the airplane is detected before taking off, the water mist treatment can be firstly carried out on the area to be detected so as to enable the anti-loosening rope connected with the loose bolt to change color.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are intended to be within the scope of the invention.
Claims (3)
1. An airplane bolt fastening and detecting method is characterized by comprising the following steps,
the anti-loosening rope is connected in series to a plurality of bolts needing to be fastened outside the airplane, and the adjacent bolts are subjected to opposite forces of the anti-loosening ropes, so that the anti-loosening ropes are restricted with each other;
the anti-loosening rope comprises a rope-shaped rigid locking body, a color-changing silica gel layer and a transparent waterproof layer;
the surface of the rope-shaped rigid locking layer body is provided with a groove along the axial direction of the rope-shaped rigid locking layer body;
the color-changing silica gel layer is arranged in the groove;
the transparent waterproof layer is hermetically covered on the allochroic silica gel layer, so that the allochroic silica gel layer is isolated from the atmosphere;
the transparent waterproof layer has enough ductility at normal temperature, so that the transparent waterproof layer is kept intact when bolt fastening operation is carried out, the breaking elongation of the transparent waterproof layer is reduced along with temperature reduction, and when the temperature is lower than minus 30 ℃, the breaking elongation of the transparent waterproof layer material is less than 0.5%;
when the bolt fastening condition is detected, the area to be detected is in a humidity environment which is enough to enable the color-changing silica gel to change color, then the color-changing silica gel is observed, and if the color-changing silica gel changes color, the bolt is judged to be loosened.
2. The aircraft bolt fastening and detecting method of claim 1, wherein the transparent waterproof layer is low density polyethylene.
3. The aircraft bolt fastening and detecting method according to claim 1, characterized in that when the aircraft is detected before taking off, the change of the allochroic silicagel is observed after water spray is applied to the area to be detected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011333510.2A CN112478196B (en) | 2020-11-24 | 2020-11-24 | Airplane bolt fastening and detecting method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011333510.2A CN112478196B (en) | 2020-11-24 | 2020-11-24 | Airplane bolt fastening and detecting method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112478196A CN112478196A (en) | 2021-03-12 |
| CN112478196B true CN112478196B (en) | 2021-07-06 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011333510.2A Active CN112478196B (en) | 2020-11-24 | 2020-11-24 | Airplane bolt fastening and detecting method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112478196B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113297711B (en) * | 2021-07-28 | 2022-01-07 | 广东电网有限责任公司中山供电局 | Structure optimization method and device for passive loosening early warning bolt |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN112478196A (en) | 2021-03-12 |
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