CN105136359A - Method for calculating work load based on beam surface strain values measured by optical fiber sensors - Google Patents

Method for calculating work load based on beam surface strain values measured by optical fiber sensors Download PDF

Info

Publication number
CN105136359A
CN105136359A CN201510575438.7A CN201510575438A CN105136359A CN 105136359 A CN105136359 A CN 105136359A CN 201510575438 A CN201510575438 A CN 201510575438A CN 105136359 A CN105136359 A CN 105136359A
Authority
CN
China
Prior art keywords
fibre optical
optical sensor
load
moment
place
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.)
Granted
Application number
CN201510575438.7A
Other languages
Chinese (zh)
Other versions
CN105136359B (en
Inventor
魏鹏
郑雷雷
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shandong Shuangshi Security Information Technology Industry Research Institute Co., Ltd
Original Assignee
Beihang University
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Beihang University filed Critical Beihang University
Priority to CN201510575438.7A priority Critical patent/CN105136359B/en
Publication of CN105136359A publication Critical patent/CN105136359A/en
Application granted granted Critical
Publication of CN105136359B publication Critical patent/CN105136359B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Landscapes

  • Length Measuring Devices By Optical Means (AREA)

Abstract

The invention discloses a method for calculating a work load based on beam surface strain values measured by optical fiber sensors, and aims to utilizing an optical fiber Bragg grating (FBG) technology to measure the beam surface internal strain values and then obtain real-time planar applied bending or torsion work load data. According to the invention, FBG strain sensors are utilized and are pasted on a beam structure at certain intervals, so that the beam is divided into a plurality of regions. By adopting the method, the torque, the bending moment and the shearing force of the cross section where the optical fiber sensor is arranged are calculated, and then the work load value of the region is calculated by utilizing the shearing forces of two adjacent cross sections. Specific embodiment schemes are provided by invention for verifying the precision of the method. Compared with other methods for measuring the work load of the beam in the prior art, the method provided by the invention is interference resistant, time-saving, cost-saving and high in efficiency.

Description

Based on the method for the beam surface strain values evaluation work load that Fibre Optical Sensor records
Technical field
The present invention relates to a kind of method of the beam surface strain values evaluation work load recorded based on Fibre Optical Sensor, belong to technical field of optical fiber sensing.
Background technology
At present, for obtaining the operating load on girder construction part, but a kind of strict method for designing consuming time of industrial employing, this method for designing relies on the method for calculating to a great extent, such as finite element modeling (FEM).But finite element modeling is the method for at substantial manpower and financial cost.
Further, for the real-time load relevant to aircraft wing, the method for use is one " foil gauge/load calibration " method relatively widely grown up nineteen fifties.First, traditional foil gauge of series of discrete is installed in the inside of wing structure, demarcates the response of foil gauge under these load in a series of centre-point load of aerofoil surface effect, be referred to as influence coefficient.Then by foil gauge measured value Input Software, real time execution load formula obtains result.Wherein take time and effort during this method sensor installation, and cost is higher.
Summary of the invention
The technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, there is provided a kind of method of the beam surface strain values evaluation work load recorded based on Fibre Optical Sensor, the beam surface strain values that the object of the invention is to use Fibre Optical Sensor to record obtains operating load in real time.
Another object of the present invention reduces the time that Real-time Obtaining acts on the operating load on beam.
Further object of the present invention reduces the financial cost relevant to the operating load on Real-time Obtaining beam.
The technology of the present invention solution: a kind of method of the beam surface strain values evaluation work load recorded based on Fibre Optical Sensor, described beam is uniform cantilever beam or cross section gradual change semi-girder, and operating load is bending load, torsional load, or both all have.Performing step is as follows:
(1) on girder construction part, install multiple Fibre Optical Sensor, when measuring bending load, Fibre Optical Sensor is pasted along the axis of beam; When measuring torsional load, Fibre Optical Sensor will be 45 ° with the axis of beam;
(2), after Fibre Optical Sensor arranges, apply bending load or torsional load, apply a known single-point load or a couple at the free end of beam, obtain the strain value at each Fibre Optical Sensor place;
(3) arrange and improve Fibre Optical Sensor and after being applied with known load, carry out to beam demarcations and test, obtain the structural behaviour of the beam at each Fibre Optical Sensor place, described structural behaviour comprises bending stiffness and torsional rigidity; And at this definition section factor s i, make wherein I ithe moment of inertia in cross section, i-th sensor place, c iit is the distance of i-th sensor and neutral axis.According to i-th sensor place moment M iwith strain stress irelation formula (E ibe the Young modulus at i-th sensor place), bring section factor into after distortion, obtain formula M i=(ES) iε i, then (ES) ifor the scale-up factor of moment of flexure and strain value, after demarcation, determine the relation between moment of flexure and strain;
(4) the strain value calculated torque, the moment of flexure that utilize the architectural characteristic of demarcating and Fibre Optical Sensor to record;
(5) moment of flexure between adjacent two Fibre Optical Sensors is utilized to obtain shearing force, the operating load that recycling computation of cutting force beam is real-time.
Described Fibre Optical Sensor is Fiber Bragg Grating FBG (FBG) sensor.
Described scaling method is as described below, the length of the semi-girder demarcated is l, on beam, Fibre Optical Sensor is arranged before demarcation, the free end of beam acts on a known single-point load P, then beam can bend, beam is separated into multiple region by Fibre Optical Sensor, and each zone length is Δ l, cross section x=x ithe moment of flexure at place is M=P (l-i △ l), carries it into formula in, obtain formula deflection of beam rigidity is just determined at each measuring position place; Strain value is recorded, according to calibration formula at each Fibre Optical Sensor place obtain the bending stiffness at each Fibre Optical Sensor place.
The process of the strain value calculated bending moment utilizing the architectural characteristic of demarcating and Fibre Optical Sensor to record in described step (4) is: described step (3) calibration result obtains each Fibre Optical Sensor place bending stiffness, according to formula: namely determine the relation between moment of flexure and strain, and strain value is recorded by each Fibre Optical Sensor, so determine the moment of flexure on beam section residing for each Fibre Optical Sensor.
Utilize the moment of flexure between adjacent two Fibre Optical Sensors to obtain shearing force in described step (5), process and the formula of recycling shearing force acquisition operating load are:
According to the equilibrium principle of moment, at cross section x=x ithe shearing force V at place ican determine, computing formula is according to equilibrium of forces principle, at cross section x=x iplace operating load P ican be determined, computing formula is P i=-△ V i.
The present invention's advantage is compared with prior art:
(1) the present invention reduces the complexity of finite element modeling, and namely compared with finite element modeling, the present invention is simple, and counting yield is high.
(2) the Fibre Optical Sensor quality of the present invention's employing is light, and size is little, and the advantages such as easy networking, electromagnetism interference overcome the weak point of traditional foil gauge, have time saving and energy saving advantage.
(3) the present invention has decreased structure analysis to a great extent, has increased time needed for process such as degree of accuracy and cost.
Accompanying drawing explanation
Fig. 1 is the arrangenent diagram of uniform beam upper sensor;
In figure, 1-beam; 2-FBG sensor (survey torsional strain); The axis of 3-beam; 4-FBG sensor (lateral bending curved strain); 5-sensor distance; 6-c (sensor is to the distance of neutral axis or neutral surface); The length of 7-beam.Along the axial direction attachment bending strain Fibre Optical Sensor of beam, be 45 ° along the axial direction of beam and axle and mount and survey torsional strain Fibre Optical Sensor.
Embodiment
Objective for implementation is cantilever beam structure part as shown in Figure 1, and left end is clamped, and right-hand member is the free end of beam, in FIG, and 1-beam; 2-FBG sensor (survey torsional strain); The axis of 3-beam; 4-FBG sensor (lateral bending curved strain); 5-sensor distance △ l; 6-c (sensor is to the distance of neutral axis or neutral surface); The length l of 7-beam.Along the axial direction attachment bending strain Fibre Optical Sensor of beam, the axial direction along beam mounts torsional strain Fibre Optical Sensor with axial in 45 °.
The present invention is implemented as follows:
(1) on girder construction part, install multiple Fibre Optical Sensor, when measuring bending load, the axis along beam is pasted; When measuring torsional load, Fibre Optical Sensor will be 45 ° with the axis of beam;
(2), after Fibre Optical Sensor arranges, apply bending load or torsional load, namely act on free end known single-point load or a couple of beam, obtain the strain value at each Fibre Optical Sensor place;
(3) arrange and improve Fibre Optical Sensor and after being applied with known load, carry out a simple calibration experiment to beam, obtain the structural behaviour of the beam at each Fibre Optical Sensor place, described structural behaviour comprises bending stiffness and torsional rigidity;
(4) the strain value calculated bending moment, the moment of torsion that utilize the architectural characteristic of demarcating and Fibre Optical Sensor to record;
(5) moment of flexure between adjacent two Fibre Optical Sensors is utilized to obtain shearing force, the operating load that recycling computation of cutting force beam is real-time.
Further, the present invention installs the rational Fibre Optical Sensor network of a set of spatial resolution on beam, in order to obtain the architectural characteristic in cross section, sensor place, for deflection of beam situation, applies a single-point load at the free end of beam, is used for obtaining deflection of beam performance.Similar, apply a couple at the free end of beam, obtain the torsion structure characteristic of beam.
The invention provides a kind of method of improvement, the beam surface strain values evaluation work load that the method records based on Fibre Optical Sensor.Usually, multiple Fibre Optical Sensor is arranged on beam and presents latticed, well-regulated model.Fibre Optical Sensor has the features such as size is little, lightweight, because being employed herein a large amount of Fibre Optical Sensors.In fact beam be divide into multiple region by these sensors, and these regions are the part between adjacent two sensors.The present invention supposes that there is constant structural behaviour in these regions, but the structural behaviour of zones of different may be different.Because record strain value at the two edges place in each region, the length in these regions can be the same or different.
The present invention adopts optical frequency domain reflection technology, uses the grating having the antiradar reflectivity of identical central wavelength, and tunable laser.Up to a hundred FBG become a string.A kind of common configuration is use 480 sensors, and on the optical fiber that a treaty 6m is long, 1FBG/cm pastes.The quantity of sensor depends on the length of beam, and example, for wing, user can paste one by about 1.27cm.The inventive method has higher spatial resolution compared with current additive method.
After Fibre Optical Sensor is arranged on beam, bending can to apply according to described method below with torsional load.For bending load, an outer single-point load of additional plane, and load is known, acts on the free end of beam, usually along wing major axes orientation.Similar, for torsional load, a pair known force couple role is at the free end of structure.Next, joist support is made to be subject to operating load.At loading duration, the structural behaviour information utilizing every part and the strain value recorded from sensor, according to the time interval of user oneself setting, moment of torsion, the moment of flexure at each region place, shearing force, load can be calculated.
The theoretical method of bending load is determined in description more detail below, because the bending derivation with reversing is theoretical and formula has similar features, so analogy can obtain torsion situation.
This method establishment is in the classical bending equations of uniform beam:
d 2 y dx 2 = M ( x ) E I - - - ( 1 )
Wherein y is perpendicular displacement, and x is beam axial coordinate, and M (x) is moment of flexure, and E is Young modulus (or elastic modulus), and I is the form that moment of inertia formula (1) can be written as non-homogeneous beam:
M ( x ) E I ( x ) = ϵ ( x ) c ( x ) - - - ( 2 )
Wherein ε (x) is strain value, and c (x) is the distance of sensor to neutral axis, is the function of the axial x of beam.
Girder construction is divided into a lot of region by sensor, then each region may be defined as length on beam is the part of Δ l, and formula (2) can be write as the equation for each strain, such as cross section x=x iprescription journey is as follows
M i E i I i = ϵ i c - - - ( 3 )
Subscript i is cross section x=x ithe numbering of place's sensor.
If definition section factor:
s i = I i c i - - - ( 4 )
(4) formula is substituted into formula (3) is:
E i S i = M i ϵ i - - - ( 5 )
Next step is undertaken one by a known single-point load simply to demarcate.
The length of the beam in demarcation is l, is become multiple region by sensor discrete, and each zone length is Δ l, cross section x=x ithe moment of flexure at place is M=P (l-i △ l), and formula is brought into (3) formula, deflection of beam rigidity is just determined at each measuring position place.After bringing into:
( E I ) i = P ( l - i Δ l ) c i ϵ i - - - ( 6 )
Elastic modulus in formula (5) and the product of section factor are demarcated can be obtained by following formulas:
( E S ) i = P ( l - i Δ l ) ϵ i - - - ( 7 )
In order to obtain the operating load data of beam, strain value ε records in an experiment, and bending stiffness (EI) is obtained by single-point lotus calibration experiment, so under the effect of any load in an experiment, the moment of flexure at each region place can be determined:
M i = ( E I ) i ϵ i c i - - - ( 8 )
Then formula (5) is:
M i＝(ES) iε i(9)
According to the equilibrium principle of moment, at cross section x=x ithe shear-type load at place can be determined:
V i = d M d x ≅ ΔM i Δx i - - - ( 10 )
Finally, according to equilibrium of forces principle, operating load can be determined:
P i＝-△V i(11)
The beam surface face internal strain measured value that the present invention utilizes Fiber Bragg Grating FBG (FBG) technology to provide is real-time, the additional bending and torsion load of Calculation Plane of Ultra-High Efficiency.
In order to the present invention is described, an object lesson is as follows
(1) one long be l uniform cantilever beam on axially arrange according to certain intervals and paste FBG strain transducer
(2) apply a known single-point load power P at its free end, then can complete the bending stiffness calibration experiment at each sensor place according to formula (6).
(3) the uniform beam performance of demarcating can contrast with following formula result of calculation:
( E I ) i = Ebh 3 12 - - - ( 12 )
(4) then utilize the bending stiffness of demarcation, strain value uses formula (8), (10), (11) calculated bending moment, shearing force, operating load etc. in the present invention.
(5) on above-mentioned beam placement sensor position on apply equivalent load, record beam monitor strain value under equidistant Uniform Loads, then brings the formula (8) in the present invention, (10), (11) calculated bending moment, shearing force, operating load etc. into.
(6) load of calculating and the actual operating load applied are compared, counting accuracy.
(7) when beam is cross section gradual change beam, the situation of analogy uniform cross-section beam, under loading single-point load and uniformly distributed load situation respectively, the value of the moment of flexure of sensor place beam, shearing and load.
Can verify that uniform beam or cross section gradual change beam bear the calibration result correctness of bending stiffness in single-point load and uniformly distributed load situation respectively by above-mentioned specific embodiments.And utilizing the structural behaviour of beam surface face planted agent's variate and demarcation can the additional bending operating load of Calculation Plane in real time, by contrasting with the known load of applying, determining trueness error.Torsional load can be obtained in analogy.
Although be described the illustrative embodiment of the present invention above; so that those skilled in the art understand the present invention; but should be clear; the invention is not restricted to the scope of embodiment; to those skilled in the art; as long as various change to limit and in the spirit and scope of the present invention determined, these changes are apparent, and all innovation and creation utilizing the present invention to conceive are all at the row of protection in appended claim.

Claims (5)

1. the method for the beam surface strain values evaluation work load recorded based on Fibre Optical Sensor, it is characterized in that: described beam is uniform cantilever beam or cross section gradual change semi-girder, operating load is bending load, torsional load, or both all have, and performing step is as follows:
(1) on girder construction part, install multiple Fibre Optical Sensor, when measuring bending load, Fibre Optical Sensor is pasted along the axis of beam; When measuring torsional load, Fibre Optical Sensor will be 45 ° with the axis of beam;
(2), after Fibre Optical Sensor arranges, apply bending load or torsional load, apply a known single-point load or a couple at the free end of beam, obtain the strain value at each Fibre Optical Sensor place;
(3) arrange and improve Fibre Optical Sensor and after being applied with known load, carry out to beam demarcations and test, obtain the structural behaviour of the beam at each Fibre Optical Sensor place, described structural behaviour comprises bending stiffness and torsional rigidity; And at this definition section factor s i, make wherein I ithe moment of inertia in cross section, i-th sensor place, c ithe distance of i-th sensor and neutral axis, according to i-th sensor place moment M iwith strain stress irelation formula e ibe the Young modulus at i-th sensor place, after distortion, bring section factor into again, obtain formula M i=(ES) iε i, then (ES) ifor the scale-up factor of moment of flexure and strain value, after demarcation, namely determine the relation between moment of flexure and strain;
(4) the strain value calculated torque, the moment of flexure that utilize the architectural characteristic of demarcating and Fibre Optical Sensor to record;
(5) moment of flexure between adjacent two Fibre Optical Sensors is utilized to obtain shearing force, the operating load that recycling computation of cutting force beam is real-time.
2. the method for the beam surface strain values evaluation work load recorded based on Fibre Optical Sensor according to claim 1, is characterized in that: described Fibre Optical Sensor is Fiber Bragg Grating FBG (FBG) sensor.
3. the method for the beam surface strain values evaluation work load recorded based on Fibre Optical Sensor according to claim 1, it is characterized in that: described scaling method is as described below, the length of the semi-girder demarcated is l, on beam, Fibre Optical Sensor is arranged before demarcation, the free end of beam acts on a known single-point load P, then beam can bend, and beam is separated into multiple region by Fibre Optical Sensor, each zone length is Δ l, cross section x=x ithe moment of flexure at place is M=P (l-i △ l), carries it into formula in, obtain formula deflection of beam rigidity is just determined at each measuring position place; Strain value is recorded, according to calibration formula at each Fibre Optical Sensor place obtain the bending stiffness at each Fibre Optical Sensor place.
4. the method for the beam surface strain values evaluation work load recorded based on Fibre Optical Sensor according to claim 1, it is characterized in that: the process of the strain value calculated bending moment utilizing the architectural characteristic of demarcating and Fibre Optical Sensor to record in described step (4) is: described step (3) calibration result obtains each Fibre Optical Sensor place bending stiffness, according to formula: namely determine the relation between moment of flexure and strain, and strain value is recorded by each Fibre Optical Sensor, so determine the moment of flexure on beam section residing for each Fibre Optical Sensor.
5. the method for a kind of beam surface strain values evaluation work load recorded based on Fibre Optical Sensor according to claim 1, it is characterized in that: utilize the moment of flexure between adjacent two Fibre Optical Sensors to obtain shearing force in described step (5), process and the formula of recycling shearing force acquisition operating load are:
At cross section x=x ithe shearing force V at place icomputing formula is
At cross section x=x iplace operating load P icomputing formula is P i=-△ V i.
CN201510575438.7A 2015-09-11 2015-09-11 Method based on the beam surface strain values evaluation work load that fibre optical sensor measures Active CN105136359B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201510575438.7A CN105136359B (en) 2015-09-11 2015-09-11 Method based on the beam surface strain values evaluation work load that fibre optical sensor measures

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201510575438.7A CN105136359B (en) 2015-09-11 2015-09-11 Method based on the beam surface strain values evaluation work load that fibre optical sensor measures

Publications (2)

Publication Number Publication Date
CN105136359A true CN105136359A (en) 2015-12-09
CN105136359B CN105136359B (en) 2018-06-01

Family

ID=54721791

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201510575438.7A Active CN105136359B (en) 2015-09-11 2015-09-11 Method based on the beam surface strain values evaluation work load that fibre optical sensor measures

Country Status (1)

Country Link
CN (1) CN105136359B (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105547235A (en) * 2016-01-20 2016-05-04 武汉理工大学 Method for measuring pull-press and bending composite deformation field of variable cross section beam structure
CN107462353A (en) * 2017-07-26 2017-12-12 北京航空航天大学 A kind of wing bending moment method of real-time based on fiber grating actual measurement strain
CN107991060A (en) * 2017-11-20 2018-05-04 南京航空航天大学 Based on adaptive and iterative algorithm load distribution type fiber-optic discrimination method
CN108106952A (en) * 2017-11-30 2018-06-01 江西洪都航空工业集团有限责任公司 A kind of disymmetry section shock loading measuring method of beam
CN108519061A (en) * 2018-03-29 2018-09-11 中原工学院 A kind of method and apparatus measuring deformation of member strain gradient
CN110887448A (en) * 2019-11-28 2020-03-17 上海航天控制技术研究所 Beam structure form reconstruction method based on optical fiber strain measurement
CN111521126A (en) * 2020-04-28 2020-08-11 兰州大学 Fiber grating sensing monitoring method for three-dimensional reconstruction of submarine pipeline
CN111581744A (en) * 2020-05-07 2020-08-25 湖南师范大学 Elliptical cross-section equal-strength supporting beam with evenly distributed loads at intervals
CN112880578A (en) * 2020-12-28 2021-06-01 南京航空航天大学 System and method suitable for monitoring dislocation of airport pavement seam structure
CN113932725A (en) * 2021-09-24 2022-01-14 成都飞机工业（集团）有限责任公司 Calibration method of optical fiber strain sensor for load monitoring of cantilever type positioner
CN114720036A (en) * 2022-03-11 2022-07-08 中国航发沈阳发动机研究所 Aeroengine redundant mounting beam structure load calibration method and device

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040129867A1 (en) * 2002-12-20 2004-07-08 Mackey Jeffrey R. Force measurement system using polarization-state modulated optical polarimetry
CN102032965A (en) * 2010-12-17 2011-04-27 昆明理工大学 Method for measuring stress of broken-line reinforced T-shaped beam through fiber Bragg grating
CN203732039U (en) * 2014-02-11 2014-07-23 柳州欧维姆机械股份有限公司 Integrated temperature self-compensation fiber raster strain sensor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040129867A1 (en) * 2002-12-20 2004-07-08 Mackey Jeffrey R. Force measurement system using polarization-state modulated optical polarimetry
CN102032965A (en) * 2010-12-17 2011-04-27 昆明理工大学 Method for measuring stress of broken-line reinforced T-shaped beam through fiber Bragg grating
CN203732039U (en) * 2014-02-11 2014-07-23 柳州欧维姆机械股份有限公司 Integrated temperature self-compensation fiber raster strain sensor

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
KO W L, RICHARDS W L, TRAN V T.: "Displacement theories for in-flight deformed shape predictions structures", 《NASA DRYDEN FLIGHT RESEARCH CENTER》 *
梁龙彬等: "基于光纤光栅的标准梁应变分析与测量", 《光电子•激光》 *

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105547235A (en) * 2016-01-20 2016-05-04 武汉理工大学 Method for measuring pull-press and bending composite deformation field of variable cross section beam structure
CN105547235B (en) * 2016-01-20 2019-01-04 武汉理工大学 The measurement method of variable-section beam structure tension and compression and bending composite deformation field
CN107462353A (en) * 2017-07-26 2017-12-12 北京航空航天大学 A kind of wing bending moment method of real-time based on fiber grating actual measurement strain
CN107991060A (en) * 2017-11-20 2018-05-04 南京航空航天大学 Based on adaptive and iterative algorithm load distribution type fiber-optic discrimination method
CN108106952A (en) * 2017-11-30 2018-06-01 江西洪都航空工业集团有限责任公司 A kind of disymmetry section shock loading measuring method of beam
CN108106952B (en) * 2017-11-30 2020-05-08 江西洪都航空工业集团有限责任公司 Method for measuring impact load of beam with double symmetrical sections
CN108519061A (en) * 2018-03-29 2018-09-11 中原工学院 A kind of method and apparatus measuring deformation of member strain gradient
CN110887448A (en) * 2019-11-28 2020-03-17 上海航天控制技术研究所 Beam structure form reconstruction method based on optical fiber strain measurement
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
CN111581744A (en) * 2020-05-07 2020-08-25 湖南师范大学 Elliptical cross-section equal-strength supporting beam with evenly distributed loads at intervals
CN111581744B (en) * 2020-05-07 2023-10-10 湖南师范大学 Elliptic cross section equal strength supporting beam with uniformly distributed load at intervals
CN112880578A (en) * 2020-12-28 2021-06-01 南京航空航天大学 System and method suitable for monitoring dislocation of airport pavement seam structure
CN113932725A (en) * 2021-09-24 2022-01-14 成都飞机工业（集团）有限责任公司 Calibration method of optical fiber strain sensor for load monitoring of cantilever type positioner
CN114720036A (en) * 2022-03-11 2022-07-08 中国航发沈阳发动机研究所 Aeroengine redundant mounting beam structure load calibration method and device
CN114720036B (en) * 2022-03-11 2023-08-18 中国航发沈阳发动机研究所 Load calibration method and device for redundant mounting beam structure of aero-engine

Also Published As

Publication number Publication date
CN105136359B (en) 2018-06-01

Similar Documents

Publication Publication Date Title
CN105136359A (en) Method for calculating work load based on beam surface strain values measured by optical fiber sensors
US7715994B1 (en) Process for using surface strain measurements to obtain operational loads for complex structures
Ma et al. Fiber Bragg gratings sensors for aircraft wing shape measurement: Recent applications and technical analysis
Glaser et al. Shape monitoring of a beam structure from measured strain or curvature
Roy et al. A shape sensing methodology for beams with generic cross-sections: Application to airfoil beams
CN110795884B (en) Novel hybrid test method based on multi-scale model updating
CN110127078B (en) Optical fiber monitoring method for strain-deflection-bending moment state of helicopter blade structure
CN104111032A (en) Fiber bragg grating sensor network based large-scale structure body deformation measurement method
CN203011351U (en) Sheet deformation measuring device with FBG (Fiber Bragg Grating) sensors
Iele et al. Load monitoring of aircraft landing gears using fiber optic sensors
CN103593542B (en) A kind of compound material bolt connection structure pin load distribution defining method considering gap and screw-down torque
Li et al. FBG-based online monitoring for uncertain loading-induced deformation of heavy-duty gantry machine tool base
CN109766617B (en) Displacement field reconstruction method based on strain sensor
CN106053010A (en) Multi-component fiber balance and measurement method thereof
CN111895918B (en) Multipoint serial distributed optical fiber displacement sensor and measuring system thereof
CN111232239B (en) Method, device and equipment for reconstructing curved surface flexural displacement field
Li et al. Deflection monitoring of thin-walled wing spar subjected to bending load using multi-element FBG sensors
CN114754691A (en) Distributed optical fiber monitoring and inversion method for helicopter blade bending form
CN107044828A (en) A kind of optical fiber grating structure device for detecting deformation, network and method
Tian et al. Structure shape measurement method based on an optical fiber shape sensor
Zhao Analytical solution of deflection of multi-cracked beams on elastic foundations under arbitrary boundary conditions using a diffused stiffness reduction crack model
CN106092162A (en) A kind of fiber grating sensing demodulation Peak Search Method of Feedback of Power formula
He et al. Fiber Brag grating monitoring of a morphing wing based on a polyvinyl chloride reinforced silicone substrate
Heaney et al. Distributed sensing of a cantilever beam and plate using a fiber optic sensing system
CN114417537B (en) Open type walking framework structure deformation field real-time measurement method, device and system

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant
TR01 Transfer of patent right
TR01 Transfer of patent right

Effective date of registration: 20210426

Address after: 261057 room 17, building 23, Wuzhou garden, 1166 Weifang Economic Development Zone, Shandong Province

Patentee after: Shandong Shuangshi Security Information Technology Industry Research Institute Co., Ltd

Address before: 100191 Haidian District, Xueyuan Road, No. 37,

Patentee before: BEIHANG University