CN107490326B - 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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- CN107490326B CN107490326B CN201710627125.0A CN201710627125A CN107490326B CN 107490326 B CN107490326 B CN 107490326B CN 201710627125 A CN201710627125 A CN 201710627125A CN 107490326 B CN107490326 B CN 107490326B
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- cork
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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
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- 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)
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Abstract
A kind of method of optical fiber sensing network figuration implantation body structure, it comprises the following steps that and is first laid with cork layer (2) 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 to one by one in fiber grooves (3), it is formed and is spaced equal, the staggered optical fiber sensing network (5) of transverse and longitudinal, fill the gap of optical fiber (4) and fiber grooves (3) with low elastic modulus glue (6) and be allowed to fixed.Then it re-lays one layer of cork on existing cork layer (2) sensor fibre (4) is protected, to prevent metal shell from damaging optical fiber (4) when being set with thermal protection layer.Method of the invention have many advantages, such as to lay flexibly, simple process, safety it 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 methods of optical fiber sensing network figuration implantation body structure.
Background technique
Intelligence structure is a kind of biomimetic features system, it integrates main structure, sensor, controller and driver, no
Only there is bearing function, moreover it is possible to perception and processing internal and external environment information, and the physical property by changing structure changes structure
Become, environment is responded, realizes structural health self diagnosis, certainly monitoring, adaptive, selfreparing vital signs and intelligent function
Energy.Currently, there are many selection that can be used for the sensor of intelligence structure, there are commonly piezoelectric ceramics, resistance-strain silk, super mangnetos
Self-adhering film and optical fiber etc., wherein fibre optical sensor is since it is with small in size, light weight, intensity height, good bandability, flexibility
It is good, not by Electromagnetic Interference, be not required to additional power source, be corrosion-resistant, at low cost the advantages that, and can easily lay on the surface of the housing
It constitutes monitoring grid and is gradually formed a new field-optical-fiber intelligent knot by the favor of many intelligence structure researchers
Structure.1979, National Aeronautics and Space Administration 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 is connected with computer, assigns Flight Vehicle Structure part
With the self-test of entire aircraft, self diagnosis, from monitoring, self-correcting, adaptively and memory, thinking, judge and take confrontation
The function of measure.Wherein the imagination of 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, carries out dynamic monitoring to Flight Vehicle Structure part, together
When have the function of communication etc.；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 optical fiber link and computer
It connects and counter measure appropriate is provided.
It realizes optical fiber intelligent structure health monitoring, the large area laying optical fiber sensor on structural body is needed, with optical fiber
Using more and more, the combination method of fibre optical sensor and structure is particularly important the engineering of intelligence structure.It is a large amount of external
The monitoring of configuration state is retouched in the method realization that scientific research personnel also covered using Fibre Optical Sensor grid or be implanted into aircraft cabin
Optical fiber intelligent structure monitoring method has been stated, but more detailed statement is not done for the combination method of sensor and structural body.It awards
Power number is in a kind of patent " method of the pre-buried fibre optical sensor of aircraft cabin " of ZL201410048814.2, using flying
The method of the direct cutting in device cabin metal surface is implanted into though realizing figuration of the fibre optical sensor on structural body surface, golden
It is complicated to belong to grooving processes, long construction period, and have certain damage to the surface of structural body, it is of limited application.
Summary of the invention
The technical problems to be solved by the present invention are: overcome the deficiencies in the prior art, the present invention proposes a kind of optical fiber perception
The method that network figuration is implanted into body structure forms the continuous optical fiber sensing network packet of large area in missile airframe body structure surface
Network has real-time detection function, the comprehensive monitoring to missile airframe configuration state is realized, 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 implantation body knot
The method of structure, comprises the following steps that
Cork sheet: being pasted onto the metal housing surface of guided missile by step 1, by cutting out splicing, makes cork that gold be completely covered
Belong to surface of shell and form cork layer, forms fiber grooves according to the path excision cork layer of setting；
Step 2: sensor fibre is applied in fiber grooves one by one, is formed and is spaced equal, the staggered optical network of transverse and longitudinal
Network；
Step 3: the gap between sensor fibre and fiber grooves is filled using low elastic modulus glue, so that low elasticity mould
It measures glue and exceeds cork layer outer surface, stand 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 after phellem clast colloidal sol by suppressing, and in paste process, every piece of cork sheet bending angle is not
More than 45 °.
The cork layer is adhesively fixed by epoxy glue or acrylate glue with metal housing surface.
The overall thickness of the cork layer is 3 millimeters, wherein is machined with the cork layer of fiber grooves with a thickness of 2 millimeters, is used for
The cork layer of sensor fibre protection is with a thickness of 1 millimeter.
The sensor fibre is point type fibre optical sensor or distributed fiberoptic sensor.
Any two neighboring sensor optical fiber spacing require to be adjusted according to measurement accuracy in the fiber optic network, and spacing is got over
Small corresponding measurement accuracy is higher.
The low elastic modulus glue is silicon rubber, Elastic Modulus Values range are as follows: 1.5MPa~2.2MPa.
The advantages of the present invention over the prior art are that:
(1) cork layer used in method of the invention is suppressed by phellem bits colloidal sol, has very high heat-insulated resistance
Characteristic is fired, is a kind of good high-speed aircraft outer layer heat-barrier material, improves security of system and reliability；On cork layer
Fluting, opposing metallic structural body surface are directly slotted, and construction is more
(2) method of the invention be successively laid on two layers of cork on guided missile metal shell formed a sensor fibre with it is embedding
The interlayer for entering cork is protected sensor fibre inside it completely, can prevent metal shell damage when being set with thermal protection layer
Hurt optical fiber, compared to the scheme directly slotted on metal shell, this mode can be in the premise for not reducing body structure intensity
Improve system reliability.
(3) fixed form of fibre optical sensor of the present invention is to process fiber grooves as laying on missile airframe surface
Every sensor fibre is fixed in corresponding groove by channel, convenient for the laying of sensor fibre, while can guarantee that sensor fibre exists
It is not damaged during missile flight.
(4) sensor fibre that the present invention uses has the advantages that good environmental adaptability, high reliablity, meets and flies in aircraft
The requirement used under the mal-conditions such as high temperature, vibration during row.
It (5), can be in aircraft casing table the invention proposes the method for being laid with sensor fibre in guided missile metal housing surface
Face forms all standing and equally distributed optical fiber sensing network, and can be met by precalculating suitable sensor fibre spacing
Measurement accuracy requirement.
Detailed description of the invention
Fig. 1 is that method of the invention is formed by structural schematic diagram.
Fig. 2 is cork layer structure sectional view of the invention.
Specific embodiment
Method of the invention is further described in conjunction with attached drawing.
As shown in Figure 1, a kind of method of optical fiber sensing network figuration implantation body structure, comprising the following steps:
Step 1: being pasted onto 1 surface of guided missile metal shell for rectangle cork sheet, by cutting out splicing, covers cork completely
1 surface of lid metal shell forms cork layer 2, then can accommodate completely according to the formation of cork layer 2 of design drawing excision particular path
The fiber grooves 3 that sensor fibre 4 is laid.
Step 2: sensor fibre 4 is applied to one by one in fiber grooves 3, and concrete operations are as follows, in each fiber grooves 3
Interior patch double-sided adhesive, 2 millimeters of double-sided adhesive bandwidth, 10 millimeters of length, the double-sided adhesive at 10 centimetres or so patches one apply sensor fibre 4
Being located in fiber grooves 3 comes into full contact with sensor fibre 4 with double-sided adhesive, and laid processes sensor fibre 4 does not allow recessed beyond optical fiber
Slot 3.Longitudinal fiber grooves 3 are first laid, lateral fiber grooves 3 are spaced equal, the staggered fiber optic network of transverse and longitudinal secondly, being formed
5。
Step 3: sensor fibre 4 and fiber grooves 3, the slightly mistake of low elastic modulus glue 6 are filled using low elastic modulus glue 6
Amount exceeds 2 outer surface of cork layer, stands 15 minutes or so, low elastic modulus glue 6 is made to be fully infiltrated into fiber grooves 3 and sense light
The gap of fibre 4, then strikes off extra low elastic modulus glue 6 with scraper plate, and continuing to stand 1 hour or so makes low elastic modulus glue 6
Outer surface solidification, coats the quarter turn or so of 1 all surfaces of metal shell every time, and coating is completed in four times.
Step 4: after the solidification of whole low elastic modulus glue 6,2 pairs of one layer of cork layer is re-layed on existing cork layer 2
Sensor fibre 4 is protected, to prevent metal shell 1 from damaging sensor fibre 4 when being set with thermal protection layer.Realize sensor fibre
Figuration on 1 surface of missile case is implanted into, while being connected with real-time watch device inside body, and body surface damage position is formed
Monitoring system.
The present invention is realized in the pre-buried sensor fibre in 1 surface of missile case, while being connected with body inside real-time watch device,
Body surface damage position monitoring system is formed, due to optical fiber strong antijamming capability, so this system is used with very high reliable
Property.
Rectangle cork sheet be by being suppressed after tiny phellem clast colloidal sol, vibration damping with higher, it is moisture-proof, heat-insulated,
The characteristics such as fire-retardant, corrosion-resistant, are suitable as the intermediate medium of guided missile metal shell and thermal protection shield.
Cork layer 2 is that rectangle cork sheet is laid in 1 surface loop of body metal shell around splicing, passes through epoxy glue or third
Olefin(e) acid glue is adhesively fixed with surface of shell.Body surface curvature radius is greater than cork sheet extreme flexion radius, and every block of cork sheet is curved
Bent angle is no more than 45 °, to guarantee that cork layer screen resilience is significantly less than the bonding force of glue, guarantee cork process of deployment and after
It does not fracture, tilt in continuous work.
As shown in Fig. 2, cork layer 2, overall thickness is added by two layers of 2 thickness of cork, wherein processing fiber grooves
Cork layer 2 protects the cork layer 2 of sensor fibre with a thickness of 1 millimeter with a thickness of 2 millimeters, therefore 2 overall thickness of cork layer is 3 millimeters.
The fixed form of every sensor fibre 4 are as follows: firstly, then will in the groove 3 of body cork layer processing particular path
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, to prevent shell in suit thermal protection layer
When damage optical fiber.
4 size of sensor fibre that the size of fiber grooves 3 is accommodated by it determines, need to guarantee sensor fibre 4 completely into
Enter groove, it is contemplated that staggered 4 highest point of sensor fibre, the two optical fiber crosspoint of transverse and longitudinal should be fibre diameter twice 1.8 millimeters,
So 3 depth of fiber grooves should be slightly above this value, it is determined 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 under amount 6 surface tension effects of glue, the width of fiber grooves 3 needs to guarantee that glue can be smooth
The whole gaps for flowing into and filling groove and optical fiber determine that simple optical fiber groove 3 can satisfy the minimum of this requirement by test
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 require to be adjusted according to measurement accuracy, and the smaller corresponding measurement accuracy of spacing is higher.
Sensor fibre 4, it is contemplated that sensor fibre 4 is not damaged in the procedures of establishment, therefore selects polytetrafluoroethylene (PTFE) external protection
Fixed type optical fiber, 0.9 millimeter of diameter, not only ensure that sensor fibre 4 had certain intensity, but also make to dispose sensor fibre 4
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 range
Are as follows: 1.5MPa~2.2MPa.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (5)
1. a kind of method of optical fiber sensing network figuration implantation body structure, which is characterized in that comprise the following steps that
Cork sheet: being pasted onto metal shell (1) surface of guided missile by step 1, by cutting out splicing, makes cork that gold be completely covered
Belong to shell (1) surface and form cork layer (2), forms fiber grooves (3) according to path excision cork layer (2) of setting；
Step 2: sensor fibre (4) is applied to one by one in fiber grooves (3), is formed and is spaced equal, the staggered optical network of transverse and longitudinal
Network (5)；
Step 3: using 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 make 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 (4)
(2)；
Any two neighboring sensor optical fiber (4) spacing requires to be adjusted according to measurement accuracy in the fiber optic network (5), spacing
Smaller corresponding measurement accuracy is higher；
The low elastic modulus glue (6) is silicon rubber, Elastic Modulus Values range are as follows: 1.5MPa~2.2MPa.
2. a kind of method of optical fiber sensing network figuration implantation body structure according to claim 1, it is characterised in that: institute
Cork sheet is stated by suppressing after phellem clast colloidal sol, in paste process, every piece of cork sheet bending angle 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, feature exist
In: the cork layer (2) is fixed by epoxy glue or acrylate glue with metal shell (1) surface bonding.
4. a kind of method of optical fiber sensing network figuration implantation body structure according to claim 3, it is characterised in that: institute
The overall thickness for stating cork layer (2) is 3 millimeters, wherein is machined with the cork layer (2) of fiber grooves (3) with a thickness of 2 millimeters, is used for
The cork layer (2) of sensor fibre (4) protection is with a thickness of 1 millimeter.
5. a kind of method of optical fiber sensing network figuration implantation body structure according to claim 1 or 2, feature exist
In: the sensor fibre (4) is point type fibre optical sensor or distributed fiberoptic sensor.
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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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| 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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| CN107490326A CN107490326A (en) | 2017-12-19 |
| CN107490326B true CN107490326B (en) | 2019-06-18 |
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| 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 |
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