CN107490326A - A kind of method of optical fiber sensing network figuration implantation body structure - Google Patents
A kind of method of optical fiber sensing network figuration implantation body structure Download PDFInfo
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- CN107490326A CN107490326A CN201710627125.0A CN201710627125A CN107490326A CN 107490326 A CN107490326 A CN 107490326A CN 201710627125 A CN201710627125 A CN 201710627125A CN 107490326 A CN107490326 A CN 107490326A
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- optical fiber
- cork
- figuration
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- sensing network
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
- F42B33/001—Devices or processes for assembling ammunition, cartridges or cartridge elements from parts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
- F42B35/02—Gauging, sorting, trimming or shortening cartridges or missiles
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- General Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Optical Transform (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
Abstract
A kind of method of optical fiber sensing network figuration implantation body structure, including step are as follows：Cork layer (2) is first laid in guided missile metal shell (1) outer surface, then the groove (3) that can accommodate fibre optic installations completely is formed by cutting, sensor fibre (4) is applied in fiber grooves (3) one by one, formed and be spaced the optical fiber sensing network (5) that equal, transverse and longitudinal is interlocked, filled the gap of optical fiber (4) and fiber grooves (3) with low elastic modulus glue (6) and be allowed to fixed.Then re-lay one layer of cork on existing cork layer (2) to be protected by sensor fibre (4), to prevent metal shell from damaging optical fiber (4) when being set with thermal protection layer.The method of the present invention has the advantages that to lay that flexible, technique is simple, security is good, will not damaged structure body original structure, can be applied to various structures body, production efficiency can be greatly improved.
Description
Technical field
The present invention relates to a kind of method of optical fiber sensing network figuration implantation body structure.
Background technology
Intelligence structure is a kind of biomimetic features system, and it integrates main structure, sensor, controller and driver, no
Only there is bearing function, moreover it is possible to perceive and handle internal and external environment information, and the physical property by changing structure changes structure
Become, environment is responded, realize structural health self diagnosis, certainly monitoring, the adaptive, vital signs of selfreparing and intelligent work(
Energy.At present, it can be used for that the selection of the sensor of intelligence structure is a lot, conventional has piezoelectric ceramics, resistance-strain silk, super mangneto
Self-adhering film and optical fiber etc., wherein fibre optical sensor have small volume, light weight, intensity height, good bandability, pliability due to it
It is good, not by Electromagnetic Interference, be not required to additional power source, corrosion-resistant, low cost and other advantages, and can easily lay on the surface of the housing
Monitoring grid is formed, is favored by many intelligence structure researchers, gradually forms a new field-optical-fiber intelligent knot
Structure.1979, NASA NASA originated an optical fiber Fiber in Smart Structure and covering plan, in the structural portion of aircraft
Part shell (covering) is implanted into various fiber optic sensors and signal processor and is connected with computer, assigns Flight Vehicle Structure part
Autonomous test, self diagnosis with whole aircraft, from monitoring, self-correcting, adaptively and memory, thinking, judge and take confrontation
The function of measure.The imagination of wherein intelligence structure is：The first step is by fibre optical sensor, processor, signal and power distributing network
And the electronic system of relevant control function is embedded in the covering of aircraft, dynamic monitoring is carried out to Flight Vehicle Structure part, together
When have communication etc. function；Various radio frequencies, infrared and optical sensor are laid in the major part of aircraft by second step
On surface, complete to the monitoring of aircraft physical parameter and wide band sensing and communication, and connected by fiber link and computer
Connect and appropriate counter measure is provided.
Realize optical fiber intelligent structure health monitoring, it is necessary on structure large area laying optical fiber sensor, with optical fiber
Using more and more, the associated methods of fibre optical sensor and structure are particularly important the engineering of intelligence structure.It is a large amount of external
The method that scientific research personnel also covered or be implanted into aircraft nacelle using Fibre Optical Sensor grid realizes that the monitoring to configuration state is retouched
Optical fiber intelligent structure monitoring method has been stated, but has not done more detailed statement for the associated methods of sensor and structure.Award
Power number is ZL201410048814.2 patent《A kind of method of the pre-buried fibre optical sensor of aircraft nacelle》In, using flying
The method of the direct cutting in device nacelle metal surface, it is implanted into though realizing figuration of the fibre optical sensor on structure surface, it is golden
It is complicated to belong to grooving processes, long construction period, and have certain damage to the surface of structure, it is of limited application.
The content of the invention
The technical problems to be solved by the invention are：Overcome the deficiencies in the prior art, the present invention propose that a kind of optical fiber perceives
The method that network figuration is implanted into body structure, the continuous optical fiber sensing network bag of large area is formed in missile airframe body structure surface
Network, there is real-time detection function, realize the comprehensive monitoring to missile airframe configuration state, such as mechanical property, temperature characterisitic and damage
Condition of the injury condition etc..
To achieve the above object, the present invention takes following technical scheme：A kind of optical fiber sensing network figuration is implanted into body knot
The method of structure, including step are as follows：
Step 1：Cork sheet is pasted onto to the metal housing surface of guided missile, by cutting out splicing, makes cork that gold be completely covered
Belong to surface of shell and form cork layer, cutting off cork layer according to the path of setting forms fiber grooves；
Step 2：Sensor fibre is applied in fiber grooves one by one, is formed and is spaced the optical networking that equal, transverse and longitudinal is interlocked
Network；
Step 3：The gap between sensor fibre and fiber grooves is filled using low elastic modulus glue so that low elasticity mould
Amount glue exceeds cork layer outer surface, stands the gap for making low elastic modulus glue be fully infiltrated into fiber grooves and sensor fibre；
Step 4：The low elastic modulus glue beyond cork layer outer surface is struck off with scraper plate, standing makes outside low elastic modulus glue
Surface cure；
Step 5：One layer of cork is re-layed on existing cork layer and forms the cork layer protected for sensor fibre.
The cork sheet is formed by being suppressed after phellem chip colloidal sol, and in taping process, every piece of cork sheet angle of bend is not
More than 45 °.
The cork layer is adhesively fixed by epoxy glue or acrylate glue with metal housing surface.
The gross thickness of the cork layer is 3 millimeters, wherein, the cork thickness degree for being machined with fiber grooves is 2 millimeters, is used for
The cork thickness degree of sensor fibre protection is 1 millimeter.
The sensor fibre is point type fibre optical sensor or distributed fiberoptic sensor.
Any two neighboring sensor optical fiber spacing are adjusted according to measurement accuracy requirement in the fiber optic network, and spacing is got over
Small corresponding measurement accuracy is higher.
The low elastic modulus glue is silicon rubber, and Elastic Modulus Values scope is:1.5MPa~2.2MPa.
The present invention compared with prior art the advantages of be：
(1) the cork layer used in method of the invention is formed by phellem bits colloidal sol compacting, has very high heat-insulated resistance
Characteristic is fired, is a kind of high-speed aircraft outer layer heat-barrier material well, improves security of system and reliability；On cork layer
Fluting, opposing metallic structure surface are directly slotted, and construction is more
(2) two layers of cork that method of the invention is successively laid on guided missile metal shell formed a sensor fibre with it is embedding
Enter the interlayer of cork, sensor fibre is protected inside it completely, can prevent metal shell from being damaged when being set with thermal protection layer
Hinder optical fiber, compared to the scheme directly slotted on metal shell, this mode can not reduce the premise of body structure intensity
Improve system reliability.
(3) fixed form of fibre optical sensor of the present invention is as laying in missile airframe Surface Machining fiber grooves
Passage, every sensor fibre is fixed in corresponding groove, is easy to the laying of sensor fibre, while can ensure that sensor fibre exists
It is not damaged by during missile flight.
(4) sensor fibre that the present invention uses has the advantages of good environmental adaptability, reliability is high, meets to fly in aircraft
The requirement used under the mal-conditions such as high temperature, vibration during row.
(5) present invention proposes the method in guided missile metal housing surface laying sensor fibre, can be in aircraft casing table
Face forms all standing and equally distributed optical fiber sensing network, and can be met by precalculating suitable sensor fibre spacing
Measurement accuracy requirement.
Brief description of the drawings
Fig. 1 is the structural representation that the method for the present invention is formed.
Fig. 2 is the cork Rotating fields sectional view of the present invention.
Embodiment
The method of the present invention is further described with reference to accompanying drawing.
As shown in figure 1, a kind of method of optical fiber sensing network figuration implantation body structure, comprises the following steps：
Step 1：Rectangle cork sheet is pasted onto the surface of guided missile metal shell 1, by cutting out splicing, cork is covered completely
The surface of lid metal shell 1 forms cork layer 2, and the cork layer 2 that particular path is then cut off according to design drawing is formed and can accommodated completely
The fiber grooves 3 that sensor fibre 4 is laid.
Step 2：Sensor fibre 4 is applied in fiber grooves 3 one by one, concrete operations are as follows, in each fiber grooves 3
Interior patch double faced adhesive tape, 2 millimeters of double faced adhesive tape bandwidth, 10 millimeters of length, the double faced adhesive tape at 10 cms patch one, sensor fibre 4 is applied
Being located in fiber grooves 3 makes sensor fibre 4 fully be contacted with double faced adhesive tape, and laid processes sensor fibre 4 does not allow recessed beyond optical fiber
Groove 3.Longitudinal fiber grooves 3 are first laid, secondly horizontal fiber grooves 3, form and are spaced the fiber optic network that equal, transverse and longitudinal is interlocked
5。
Step 3：Sensor fibre 4 and fiber grooves 3, the somewhat mistake of low elastic modulus glue 6 are filled using low elastic modulus glue 6
Amount, beyond the outer surface of cork layer 2,15 minutes or so are stood, low elastic modulus glue 6 is fully infiltrated into fiber grooves 3 and sense light
The gap of fibre 4, then strikes off unnecessary low elastic modulus glue 6 with scraper plate, and continuing to stand 1 hour or so makes low elastic modulus glue 6
Outer surface solidifies, and coats the quarter turn or so of all surfaces of metal shell 1 every time, and coating in four times is completed.
Step 4：After the solidification of whole low elastic modulus glue 6, one layer of 2 pairs of cork layer is re-layed on existing cork layer 2
Sensor fibre 4 is protected by, to prevent metal shell 1 from damaging sensor fibre 4 when being set with thermal protection layer.Realize sensor fibre
Figuration on the surface of missile case 1 is implanted into, while is connected with real-time watch device inside body, forms body surface damage position
Monitoring system.
The present invention is realized in the pre-buried sensor fibre in the surface of missile case 1, while is connected with real-time watch device inside body,
Body surface damage position monitoring system is formed, due to optical fiber strong antijamming capability, so the system is used with very high reliable
Property.
Rectangle cork sheet is formed by being suppressed after tiny phellem chip colloidal sol, have higher vibration damping, protection against the tide, it is heat-insulated,
The characteristic such as fire-retardant, corrosion-resistant, it is suitable as the intermediate medium of guided missile metal shell and thermal protection shield.
Cork layer 2 is that rectangle cork sheet forms in the surface loop of body metal shell 1 around splicing laying, passes through epoxy glue or third
Olefin(e) acid glue is adhesively fixed with surface of shell.Body surface curvature radius is more than cork sheet extreme flexion radius, and every block of cork sheet is curved
Bent angle is no more than 45 °, so as to ensure that cork layer screen resilience is significantly less than the bonding force of glue, ensure cork process of deployment and after
Do not fracture, do not tilt in continuous work.
As shown in Fig. 2 cork layer 2, its gross thickness is added by two layers of the thickness of cork 2 and formed, wherein processing fiber grooves
The thickness of cork layer 2 is 2 millimeters, and the thickness of cork layer 2 for protecting sensor fibre is 1 millimeter, therefore the gross thickness of cork layer 2 is 3 millimeters.
The fixed form of every sensor fibre 4 is：First, in the groove 3 of body cork layer processing particular path, then will
Sensor fibre 4 is embedded in cork groove.The gap between groove 3 and optical fiber 4 is filled using low elastic modulus glue 6.Then exist
One layer of cork 2 is re-layed on existing cork layer 2, sensor fibre 4 is protected by, to prevent housing in suit thermal protection layer
When damage optical fiber.
The size of sensor fibre 4 that the size of fiber grooves 3 is accommodated by it is determined, it is necessary to ensure that sensor fibre 4 enters completely
Enter groove, it is contemplated that transverse and longitudinal interlock the optical fiber crosspoint of 4 peak of sensor fibre two should be fibre diameter twice 1.8 millimeters,
So the depth of fiber grooves 3 should be slightly above this value, it is defined as 2 millimeters.Meanwhile in order to prevent because gap is too small and low elasticity mould
Fiber grooves 3 can not be filled up completely with the amount surface tension effects of glue 6, the width of fiber grooves 3 needs to ensure that glue can be smooth
Flow into and fill groove and whole gaps of optical fiber, determined by testing, simple optical fiber groove 3 disclosure satisfy that this desired minimum
Width value is 2 millimeters.
Sensor fibre 4 is point type fibre optical sensor or distributed fiberoptic sensor.Any two adjacent biographies in fiber optic network 5
Photosensitive fine 4 spacing can be adjusted according to measurement accuracy requirement, and the smaller corresponding measurement accuracy of spacing is higher.
Sensor fibre 4, it is contemplated that sensor fibre 4 is not damaged by the procedures of establishment, therefore selects polytetrafluoroethylene (PTFE) external protection
Tight set type optical fiber, 0.9 millimeter of diameter, both ensure that sensor fibre 4 had certain intensity, and made placement sensor fibre 4 again
Width, the depth value relative ideal of fiber grooves 3.
The low elastic modulus glue 6 is silicon rubber (single-component room-temperature-vulsilicone silicone rubber GD414), Elastic Modulus Values scope
For:1.5MPa~2.2MPa.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (7)
- A kind of 1. method of optical fiber sensing network figuration implantation body structure, it is characterised in that as follows including step：Step 1：Cork sheet is pasted onto to metal shell (1) surface of guided missile, by cutting out splicing, cork (2) is completely covered Metal shell (1) surface forms cork layer (2), and cutting off cork layer (2) according to the path of setting forms fiber grooves (3)；Step 2：Sensor fibre (4) is applied in fiber grooves (3) one by one, is formed and is spaced the optical networking that equal, transverse and longitudinal is interlocked Network (5)；Step 3：Use the gap between low elastic modulus glue (6) filling sensor fibre (4) and fiber grooves (3) so that low bullet Property modulus glue (6) exceed cork layer (2) outer surface, standing makes low elastic modulus glue (6) be fully infiltrated into fiber grooves (3) and sensing The gap of optical fiber (4)；Step 4：The low elastic modulus glue (6) beyond cork layer (2) outer surface is struck off with scraper plate, standing makes low elastic modulus glue (6) outer surface solidifies；Step 5：One layer of cork is re-layed on existing cork layer (2) and forms the cork layer protected for sensor fibre (3) (2)。
- A kind of 2. method of optical fiber sensing network figuration implantation body structure according to claim 1, it is characterised in that：Institute State cork sheet to be formed by suppressing after phellem chip colloidal sol, in taping process, every piece of cork sheet angle of bend is no more than 45 °.
- 3. a kind of method of optical fiber sensing network figuration implantation body structure according to claim 1 or 2, its feature exist In：The cork layer (2) is fixed by epoxy glue or acrylate glue with metal shell (1) surface bonding.
- A kind of 4. method of optical fiber sensing network figuration implantation body structure according to claim 3, it is characterised in that：Institute The gross thickness for stating cork layer (2) is 3 millimeters, wherein, cork layer (2) thickness for being machined with fiber grooves (3) is 2 millimeters, is used for Cork layer (2) thickness of sensor fibre (3) protection is 1 millimeter.
- 5. a kind of method of optical fiber sensing network figuration implantation body structure according to claim 1 or 2, its feature exist In：The sensor fibre (4) is point type fibre optical sensor or distributed fiberoptic sensor.
- 6. a kind of method of optical fiber sensing network figuration implantation body structure according to claim 1 or 2, its feature exist In：Any two neighboring sensor optical fiber (4) spacing is adjusted according to measurement accuracy requirement in the fiber optic network (5), spacing Smaller corresponding measurement accuracy is higher.
- 7. a kind of method of optical fiber sensing network figuration implantation body structure according to claim 1 or 2, its feature exist In：The low elastic modulus glue (6) is silicon rubber, and Elastic Modulus Values scope is:1.5MPa~2.2MPa.
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| CN201710627125.0A CN107490326B (en) | 2017-07-28 | 2017-07-28 | A kind of method of optical fiber sensing network figuration implantation body structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108917806A (en) * | 2018-07-03 | 2018-11-30 | 中国电子科技集团公司第十四研究所 | Fiber-optic grating sensor built-in process based on carbon fiber honeycomb sandwich construction |
| CN109519714A (en) * | 2018-11-23 | 2019-03-26 | 重庆大学 | Intelligent pipeline insulating layer with tiny leakage self-diagnostic function |
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| CN1598626A (en) * | 2004-07-28 | 2005-03-23 | 南京航空航天大学 | Fibre-optical intelligent sandwich in intelligent material and structure and manufacturing technique |
| US7212696B2 (en) * | 2004-02-18 | 2007-05-01 | The Boeing Company | Fiber optic damage detection system for composite pressure vessels |
| CN102361589A (en) * | 2009-03-25 | 2012-02-22 | 住友电气工业株式会社 | Optical fiber sheet and body motion sensor |
| CN103162876A (en) * | 2011-12-08 | 2013-06-19 | 西安金和光学科技有限公司 | Optic fiber monitoring device for shell component stress |
| CN103837333A (en) * | 2014-02-12 | 2014-06-04 | 北京航天时代光电科技有限公司 | Method for embedding optical fiber sensors in aircraft cabin |
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2017
- 2017-07-28 CN CN201710627125.0A patent/CN107490326B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7212696B2 (en) * | 2004-02-18 | 2007-05-01 | The Boeing Company | Fiber optic damage detection system for composite pressure vessels |
| CN1598626A (en) * | 2004-07-28 | 2005-03-23 | 南京航空航天大学 | Fibre-optical intelligent sandwich in intelligent material and structure and manufacturing technique |
| CN102361589A (en) * | 2009-03-25 | 2012-02-22 | 住友电气工业株式会社 | Optical fiber sheet and body motion sensor |
| CN103162876A (en) * | 2011-12-08 | 2013-06-19 | 西安金和光学科技有限公司 | Optic fiber monitoring device for shell component stress |
| CN103837333A (en) * | 2014-02-12 | 2014-06-04 | 北京航天时代光电科技有限公司 | Method for embedding optical fiber sensors in aircraft cabin |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108917806A (en) * | 2018-07-03 | 2018-11-30 | 中国电子科技集团公司第十四研究所 | Fiber-optic grating sensor built-in process based on carbon fiber honeycomb sandwich construction |
| CN109519714A (en) * | 2018-11-23 | 2019-03-26 | 重庆大学 | Intelligent pipeline insulating layer with tiny leakage self-diagnostic function |
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| CN107490326B (en) | 2019-06-18 |
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