CN102564332A - Method for embedding FBG (Fiber Bragg Grating) sensors into three-dimensional weaving composite material parts - Google Patents
Method for embedding FBG (Fiber Bragg Grating) sensors into three-dimensional weaving composite material parts Download PDFInfo
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Abstract
The invention provides a method for embedding FBG (Fiber Bragg Grating) sensors into three-dimensional weaving composite material parts, belonging to the field of health monitoring of three-dimensional weaving composite materials for aeration. According to the invention, according to the conditions of an aeration environment, the parts with different composite material parameters and the same sensor intervals and the parts with the same composite material parameters and different sensor intervals can be developed first, the deformation of the parts and the characters of embedded sensors under different bearing conditions can be then analyzed, a two-step method and a four-step method in the manufacturing method of the three-dimensional weaving composite materials can be combined at last; and aiming at the characters of the FBG sensors, the FBG sensors can be woven together with fibers with different intervals by the adoption of different angles and forces, and the distribution of a network of the FBG sensors can be processed. According to the method provided by the invention, the influence on the mechanical property of the three-dimensional weaving composite material parts is smaller, the monitoring signals of the sensors are more accurate, an axial mechanical property of the two-step method is highlighted, and the more sensitivity character of a four-step weaving method to a strain rate is kept.
Description
Technical field
The invention belongs to the health monitoring field of aviation, be specifically related to a kind of method that fiber Bragg grating sensor is embedded the D braided composites product with three-dimensional establishment compound substance.
Background technology
Since distribution type fiber-optic Bragg grating (FBG) sensor was imbedded in the epoxy resin composite material in nineteen ninety first, domestic scientific research person had carried out the health monitoring research work of FBG at the aviation composite structure.Up to the present; Domestic research mainly comprises: people such as Qiu Lei, Yuan Shenfang, Miao Miao have realized that the wing box section structure health monitoring based on FBG (please refer to Qiu Lei; Yuan Shenfang; Miao Miao. based on the wing box section structure health monitoring systems functional verification research [J] of FBG. piezoelectricity and acousto-optic, 2009,31 (3): 350-353); People such as Chang Xinlong, Guo Fenghua, lijin army utilize the FBG sensor to form the solid propellant rocket structural healthy monitoring system and (please refer to Chang Xinlong; Guo Fenghua; Lijin army. based on the solid propellant rocket structural health monitoring technology [J] of FBG sensor. intensity and environment; 2006,33 (4): 17-22.), the feasibility that the FBG sensing technology is used for solid propellant rocket structural strain field, the health monitoring of temperature occasion damage status has been discussed; People such as Zhou Xuefang, Liang Lei studied a kind of imbedded fiber grating concrete strain sensor (please refer to Zhou Xuefang, beam is of heap of stone. flush type FBG concrete strain sensor characteristic research [J]. sensor and micro-system, 2008,27 (3): 14-17); Letter think people such as gold studied the application of FBG sensing technology in dam safety monitoring (please refer to letter and think the applied research [J] of golden .FBG sensing technology in dam safety monitoring. Wuhan University of Technology's journal, 2004,26 (8): 35-37); People such as Jin Weiliang, Zhang Enyong has studied the application of distributing optical fiber sensing technology in the submarine pipeline health monitoring and (please refer to Jin Weiliang; Zhang Enyong etc. the application [J] of distributing optical fiber sensing technology in the submarine pipeline health monitoring. Chinese offshore oil and gas (engineering); 2003,15 (4): 5-8).
The foreign scholar early (please refer to Inaudi to the research that FBG is used for space flight product status monitoring; D; And Glisic; B..Distributed fiber optic strain and temperature sensing for structural health monitoring [C] .the Third International Conference on Bridge Maintenance, Safety and Management.July 2006, Porto Portugal:IABMAS; Portugal, 2006:16-19; Seiji Kojima; Shinji Komatsuzaki; Yoshinori Kurosawa; Et alEmbedding type strain sensors using small diameter fiber Bragg grating to composite laminate structures [J] .Hitachi Cable Review, 2004,23 (8): 11-15; Thodi, P., Khan; F., Haddara, M..TheSelection of Corrosion prior Distributions for Risk Based Integrity Modeling [J] .Stoch Environ Res Risk Assess-Springer; 2009,23 (6): 793-809).Wherein, The researchists such as M.Tmtzel of Germany DaimlerChrysler Aerospace (DASA) aircraft test center have carried out a lot of experiment tests and practical application in this field; They are pasted on FBG on the surface of carbon fiber reinforced plastics (CFPR) wing of up-to-date development at that time; Temperature and strain variation through FBG monitoring analysis compound substance (please refer to Trutzel, D.Belz, M.Holz et al.Investigation of Fiber optic Bragg Grating Sensor for applications in the Aviation industry [J] .Proc.OFS-13; 1999,624-626; Michael N.Trutzel, Karsten Wauer, Daniel Betz, et al.Smart Sensing of Aviation Structures with Fiber-optic Bragg Grating Sensors [C] .SPIE, 2000,3986:134-143; Daniel Betz, Lothar Staudigel.Test of a Fiber Bragg Grating Sensor Network for Commercial Aircraft Structures [J] .Proc.OFS-16,2002; 55-58); Realized that the health monitoring to the wing fatigue properties (please refer to Y.Okabe, S.Yashiro, T.Kosaka; N.Takeda.Detection of transverse cracks in composites by using embedded FBG sensors [C] .SPIE ' s International symposium on Smart Structures and Materials; Proceeding of SPIE, 2000,3986:282-291; Tahir B.A., J.Ali, R.A.Rahman, Strain measurements using fiber Bragg grating sensor [J] .American Journal of Applied Science, 2005,02 (special issue): 40-48; H.Iwaki; H.Yamakawa, A.Mita.FBG-based displacement and strain sensors for health monitoring of smart structures [C] .Proceedings of MOVIC 2000 Conference, Australia; 2000,4-8).
In addition, calendar year 2001, the people such as Wolfgang Eche of Germany have developed the spatially distributed sensing network system of a cover based on 12 FBG sensors, are used for the health monitoring of x-38 spaceship Ship Structure.The FBG sensor is secured at the surface of x-38 spaceship hull back element, is used for monitoring mechanical loading and the thermal force of airship in the emission and the process of making a return voyage.Through spatially distributed temperature and strain measurement to the top load structure member; Can estimate the residual life of airship structure critical piece; Realized that the health monitoring to airship (please refer to Wolfgang Ecke; Stephan Grimm.Optical Fiber Grating Sensor Network Basing on High-Reliable Fibers and Components for Spacecraft Health Monitoring [C] .SPIE, 2001,4328:160-167).
2004; The people such as Toshimiehi Ogisu of Japan utilize piezoelectric ceramics (PZT) driver/FBG sensor; Realized the damage monitoring of spacecraft advanced composite structure of new generation (please refer to Toshimichi Ogisu; Masakazu Shimanuki.Development of Damage Monitoring System for Aircraft Structure Using a PZT Actuator/FBG Sensor Hybrid System [C] .SPIE, 2004,5388:425-436).
2005; But people such as Japan Shinji Komatsuzaki have reported based on the optical wavelength addressing system of the spacecraft composite structure damage detection system of piezoelectric ceramic actuator/FBG mixed type sensor and the FBG sensor assembly of flush type composite inner and (please refer to Shinji Komatsuzaki; Seiji Kojima; Akihito Hongo; Et al.Development of high speed optical wavelength interrogation system for damage detection in composite materials [C] .SPIE, 2005,5758:51-60).
2007; People such as Nakamura Noritsugu utilize the FBG sensor to study aerospace composite and (please refer to Nakamura Noritsugu in the monitoring of impacting under carrying; Ogisu Toshimichi, Yoneda Hiroshi, et al.Impact monitoring of the aircraft composite structure using FBG sensor/PZT actuator hybrid sensor system [C] .SPIE; 2007,6527:65270B.1-65270B).
2008; People such as Chandler K. utilize the FBG sensor to realize that monitoring (please refer to Chandler K. to compound substance individual aircraft health status; Ferguson S., Graver T., et al.On-line structural health and fire monitoring of a composite personal aircraft using an FBG sensing system [C] .SPIE; 2008,6933:69330-69330).
The study on monitoring of three-dimensional establishment composite product has higher researching value in China, because it can provide the basis of crucial monitoring method for the development of China a new generation Aero-Space D braided composites, multi-usage protection compound substance and matrix enhancing D braided composites.Though the conventional composite materials state health monitoring about aviation field has obtained certain progress both at home and abroad; But up to the present; Also not to technology and the method for aviation with the health monitoring comparative maturity of three-dimensional establishment compound substance; Its reason is: at first, the three-dimensional very complicacy of composite product manufacturing process of working out needs advanced establishment machinery and the weaving method that designs voluntarily; Next is a little less than being highly brittle with FBG sensor quality because of monitoring; And volume is very little; Therefore how effectively it to be embedded into the application performance that will directly influence it in the prefabricated component, and to be unusual difficulty through adopting traditional three-dimensional preparation method that the FBG sensor is embedded.
Summary of the invention
The objective of the invention is to solve a difficult problem that exists in the above-mentioned prior art; A kind of method that fiber Bragg grating sensor is embedded the D braided composites product is provided; Adopt the weaving of different angles and dynamics that the fiber Bragg grating sensor braiding is embedded three-dimensional composite material; Solved the rational deployment problem of distribution type fiber-optic Bragg grating sensor network in the D braided composites product, and single braiding embeds the problem that technology makes the serious decline of signals collecting accuracy.
The present invention realizes through following technical scheme:
A kind of method that fiber Bragg grating sensor is embedded the D braided composites product; Said method is at first according to the aerospace environment condition; Development has the different composite material parameter and identical transducer spacing and same compound material parameter and the product of different sensors spacing; Analyze then under the different bearer situation; The distortion of said product and the characteristic that embeds sensor combine two step method in the D braided composites method for making and four step rule, to the characteristic of fiber Bragg grating sensor at last; Adopt different angles and dynamics that fiber Bragg grating sensor is arrived together by different spacing and fibrage, simultaneously sensor network is carried out layout.
Compared with prior art, the invention has the beneficial effects as follows:
(1) the present invention is according to many physical quantitys detection technique and correlation analysis theory study the best sensor network layout, and analysis temperature, weaving have proposed the sensor embedded mode of suitable product health monitoring to the influence of monitoring system;
(2) the present invention combines two steps, the four step rule weaving of D braided composites, has obtained less, a kind of more accurately new sensor embedded mode of sensor monitors signal of D braided composites product mechanical property influence;
(3) two step method of the prior art, four step rule three dimensional knitting method are combined, can effectively give prominence to the axial mechanical property of two step method, and keep the four step rule weaving method characteristic relatively more responsive rate of strain.Effectively suppress to embed the mechanical property influence bigger disturbance factor of sensor to product;
(4) the present invention is significant to the reliable application of further research Aero-Space intelligent composite.
Description of drawings
Fig. 1-the 1st, the product synoptic diagram of the circular knit in the embodiment of the invention.
Fig. 1-2 is the braiding structure synoptic diagram of the product of Fig. 1 among the present invention-1 circular knit.
Fig. 2-the 1st, the product synoptic diagram of the open width braiding in the embodiment of the invention.
Fig. 2-the 2nd, the braiding structure synoptic diagram of the product of Fig. 2 among the present invention-1 open width braiding.
Embodiment
Below in conjunction with accompanying drawing the present invention is described in further detail:
A kind of method that the FBG sensor is embedded the D braided composites product; Said method is at first according to the aerospace environment condition; Development has the different composite material parameter and identical transducer spacing and same compound material parameter and the product of different sensors spacing is analyzed then under the different bearer situation, the distortion of said product and the characteristic that embeds sensor; At last two step method in the D braided composites method for making and four step rule are combined; To the characteristic of FBG sensor, adopt different angles and dynamics that the FBG sensor is arrived together by different spacing and fibrage, simultaneously sensor network is carried out layout.
Specifically:
(1) development has the different composite material parameter and identical transducer spacing and same compound material parameter and the product of different sensors spacing.
In the specific implementation, according to the aerospace environment condition, development has the different composite material parameter and 160 of the products of identical transducer spacing and same compound material parameter and different sensors spacing.Concrete product design parameter is shown in table 1-table 4, and design size is: 400mm * 400mm * 100mm.Respectively two step method, the four step rule D braided composites test specimen with different microscopic structural parameters being carried out axial compression and axial tension and Mechanics Performance Testing finds; The axial mechanical property of the three-dimensional composite material of two step method braiding is comparatively superior, and axial tension and compression performance are played a leading role; And the general rate of strain of three-dimensional composite material of four step rule braiding is relatively more responsive, and along with the continuous increase of rate of strain, its stretch modulus and maximum stress all increase, and the strain of maximum stress reduces.
Product process parameter table under the FBG transducer spacing different situations that are to use two step method that table 1 provides, the use that table 2 provides is with the product process parameter table under the FBG transducer spacing different situations of four step rule.Relatively can draw, under identical product and the surface weave angle same case, adopt two step method, four step rule transducer spacing difference, fiber volume fraction is identical, shown in table 1 and table 2.
Product process parameter table under the FBG transducer spacing same case that is to use two step method that table 3 provides, the product process parameter table under the FBG transducer spacing same case that is to use four step rule that table 4 provides.Relatively can draw; Adopt the four step rule transducer spacing identical with surface weave angle same case under, the fiber volume fraction of identical product is identical, and changes under the sensor braid pitch situation; Identical product fiber volume fraction can increase along with the increase of spacing, shown in table 3 and table 4.
In table 1 to the table 4; Experiment parameter is sensor braid pitch, surface weave angle; Experimental result is the variation of fiber volume fraction; Wherein, the variation at surface weave angle has obvious influence to stretching, compression and the bending property of main D braided composites, and is then very little for the influence of fiber volume fraction.
Table 1
Table 2
| 10 | 20 | 50 | Four step rule | 5 |
| 10 | 20 | 50 | Four step rule | 5 |
| 10 | 20 | 50 | Four step rule | 5 |
| 10 | 20 | 50 | Four step rule | 5 |
| 10 | 20 | 50 | Four step rule | 5 |
Table 3
Table 4
(2) analyze under the different bearer situation distortion of said product and the characteristic that embeds sensor.
Said different bearer is meant different Compression and Expansion situation.According to the best sensor network layout of many physical quantitys detection technique and correlation analysis theory study, and analysis temperature, weaving propose the sensor embedded mode of suitable product health monitoring to the influence of monitoring system.
(3) two step method in the D braided composites method for making and four step rule are combined,, adopt different angles and dynamics that the FBG sensor is arrived together by different spacing and fibrage, simultaneously sensor network is carried out layout to the characteristic of FBG sensor.
Embodiments of the invention are following:
What Fig. 1 provided is the synoptic diagram that method of the present invention is used for the braiding structure of circular knit; Two groups of knitting yarn formed angles in fabric by the different directions motion are α; In each braiding circulation, when promptly each knitting yarn was got back to its initial position on machine after through motion again, the fabric length that is knit out was r; The girth of braid (or width) is s, then in circular knit:
The notion of this and helix angle is identical.Here the length that weaves repetition is equivalent to helix round-robin length.
What Fig. 2 provided is the synoptic diagram that method of the present invention is used for the braiding structure of open width braiding, and the open width braiding is then slightly different with circular knit, and its expression formula is:
In this formula, an additional factor 2 is arranged.This is because in a braiding repetition, one side each one thread will return an initial side again from the another side that moves to of fabric.So in a braiding repeat length, comprise two how much repetitions.
Technique scheme is one embodiment of the present invention; For those skilled in the art; On the basis that the invention discloses application process and principle, be easy to make various types of improvement or distortion, and be not limited only to the described method of the above-mentioned embodiment of the present invention; Therefore the mode of front description is just preferred, and does not have restrictive meaning.
Claims (1)
1. method that fiber Bragg grating sensor is embedded the D braided composites product; It is characterized in that: said method is at first according to the aerospace environment condition; Development has the different composite material parameter and identical transducer spacing and same compound material parameter and the product of different sensors spacing; Analyze then under the different bearer situation; The distortion of said product and the characteristic that embeds sensor combine two step method in the D braided composites method for making and four step rule, to the characteristic of fiber Bragg grating sensor at last; Adopt different angles and dynamics that fiber Bragg grating sensor is arrived together by different spacing and fibrage, simultaneously sensor network is carried out layout.
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| CN106338253A (en) * | 2016-08-17 | 2017-01-18 | 河海大学 | Dam surface underwater collapse distributed optical fiber detection device and detection method |
| CN106651891A (en) * | 2016-10-13 | 2017-05-10 | 天津工业大学 | Three-dimensional braided fabric composite material perform surface parameter measurement method |
| CN111366267A (en) * | 2020-04-01 | 2020-07-03 | 大连理工大学 | Method and device for monitoring internal temperature field in three-dimensional woven composite material forming process |
| CN111521126A (en) * | 2020-04-28 | 2020-08-11 | 兰州大学 | Fiber grating sensing monitoring method for three-dimensional reconstruction of submarine pipeline |
| CN111928971A (en) * | 2019-05-13 | 2020-11-13 | 南京大学昆山创新研究院 | State monitoring integrated composite material structure |
| CN114279312A (en) * | 2021-12-30 | 2022-04-05 | 中国科学院力学研究所 | High-sensitivity braided strain sensor and preparation method thereof |
| CN114964799A (en) * | 2022-04-28 | 2022-08-30 | 南京航空航天大学 | State monitoring system and method under multiple temperature gradients of rocket engine expansion section |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106338253A (en) * | 2016-08-17 | 2017-01-18 | 河海大学 | Dam surface underwater collapse distributed optical fiber detection device and detection method |
| CN106651891A (en) * | 2016-10-13 | 2017-05-10 | 天津工业大学 | Three-dimensional braided fabric composite material perform surface parameter measurement method |
| CN106651891B (en) * | 2016-10-13 | 2023-05-09 | 天津工业大学 | Surface parameter measurement method for three-dimensional braided fabric composite material prefabricated member |
| CN111928971A (en) * | 2019-05-13 | 2020-11-13 | 南京大学昆山创新研究院 | State monitoring integrated composite material structure |
| CN111366267A (en) * | 2020-04-01 | 2020-07-03 | 大连理工大学 | Method and device for monitoring internal temperature field in three-dimensional woven composite material forming process |
| CN111366267B (en) * | 2020-04-01 | 2022-01-07 | 大连理工大学 | Method and device for monitoring internal temperature field in three-dimensional woven composite material forming process |
| CN111521126A (en) * | 2020-04-28 | 2020-08-11 | 兰州大学 | Fiber grating sensing monitoring method for three-dimensional reconstruction of submarine pipeline |
| CN111521126B (en) * | 2020-04-28 | 2022-01-28 | 兰州大学 | Fiber grating sensing monitoring method for three-dimensional reconstruction of submarine pipeline |
| CN114279312A (en) * | 2021-12-30 | 2022-04-05 | 中国科学院力学研究所 | High-sensitivity braided strain sensor and preparation method thereof |
| CN114279312B (en) * | 2021-12-30 | 2023-01-31 | 中国科学院力学研究所 | High-sensitivity braided strain sensor and preparation method thereof |
| CN114964799A (en) * | 2022-04-28 | 2022-08-30 | 南京航空航天大学 | State monitoring system and method under multiple temperature gradients of rocket engine expansion section |
| CN114964799B (en) * | 2022-04-28 | 2023-09-29 | 南京航空航天大学 | State monitoring system and method under multiple temperature gradients of rocket engine expansion section |
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Application publication date: 20120711 |