CN101776441A - Real-time online system for measuring space vehicle shell impact degree and impact position - Google Patents
Real-time online system for measuring space vehicle shell impact degree and impact position Download PDFInfo
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Abstract
The invention discloses a real-time online system for measuring the space vehicle (space station) shell impact degree and impact position, which is based on a distributed fiber sensor stress and strain measurement technology and a space vehicle shell impact degree and impact position technology, and comprises a Brag fiber sensor system, a signal demodulation system and a space vehicle shell impact degree and impact position computing system, wherein a distributed Brag fiber grating sensor system is laid in a space vehicle shell, when the space vehicle shell is impacted by the outside and then stress and strain are generated, the periphery of an impact point deforms to cause the central wave length of the monitoring light wave of Brag fiber grating sensors to change, and the signal demodulation system converts the variation value of the central wave length of the monitoring wave into stress and strain at the positions of three sensors (or more) at the periphery of the impact point, inputs the stress and the stain into the space vehicle shell impact degree and impact position computing system, and determines the space vehicle shell impact degree and the impact position.
Description
[technical field]
The present invention is a kind of spacecraft (space station) housing degree of being impacted and bump positioning measurment system of real-time online, and ess-strain technology and spacecraft (space station) housing degree of being impacted and bump location technology are measured based on distributed fiberoptic sensor by this system.
[background technology]
Southampton, Britain university research personnel Publishing Study on November 4th, 2009 is reported, increase along with human space probation activity, space trash quantity will sharply increase, in following 10 years, in the space between two articles " brushing past " incident of 5 kilometers of less thaies can increase by 50%; Can increase by 250% by 2059.Increasing space trash will make the occurrence probability of space " collision " incident heighten undoubtedly.U.S.'s " line science " has obtained the hypervelocity impact database in October, 2009, show from carry out code name be STS-50 to 54 subtasks of STS-114, space trash and meteoroid hit the aircraft window 1634 times of space shuttle, force 92 windows to be replaced; The heating radiator of space shuttle is hit 317 times, the actual aluminium honeycomb panel broken hole that causes heating radiator 53 times.Discussing about sub-committee of the space junk House of Representatives about space and aviation meeting, chief scientist's Nicholas Johnson of orbit debris project office of U.S. NASA space agency announces, space junk has become a serious day by day problem, and this forces the aerospace engineer to mention schedule finding out the way that reduces this danger.
(Fiber Bragg Grating is a kind of simple intrinsic sensing element FBG) to Fiber Bragg Grating FBG, utilizes the UV photosensitive characteristic of silicon optical fiber to write in the fiber core, and the altered part refractive index of UV-irradiation forms fiber grating.Because Fiber Bragg Grating FBG has a lot of special advantages: volume is little, light weight, intensity height, good bandability, pliability are good, be not subjected to Electromagnetic Interference, do not need additional power source, corrosion-resistant, be easy to imbed structure, set up the networking monitoring, optical spectrum encoded, cost is low etc.So its sensor application field is very widely, comprising: the health monitoring intelligent network of large-sized concrete works (bridge, viaduct, railway); The application of empty space industry; The application of mining industry; The application of electric power factory; Medical domain is used; The chemical co-ordination device; Filtering device or the like.
The fiber Bragg grating sensor array can be formed the sensor network of needs in the following manner: the one, and wavelength-division multiplex (Wavelength Division Multiplexing, WDM), promptly a plurality of fiber Bragg grating strain sensors of serial connection come the strain of measurement structure body at diverse location on same optical fiber, and the number of serial connection is by the frequency range and the decision of each sensor prediction range of strain of the module of light source and signals collecting; The 2nd, (Space Division Multiplexing SDM), promptly is designed to radial pattern to the light networking by 1 * N optical exchanger (optical switch), and each passage can connect a wavelength-division multiplex sensor that comprises multi-wavelength in space division multiplexing; The 3rd, time division multiplex (Time Division Multiplexing, TDM), promptly on the light carrier in a broadband, time is divided into periodic frame, each frame is divided into some time slots (frame or time slot all are non-overlapping copies) again, each time slot is exactly a communication channel, distributes to an output port.
Patent purpose of the present invention is to solve above-mentioned space trash and meteoroid hits the deformation detection problem that produces behind spacecraft (space station) housing, and the technology of employing is that distributed fiberoptic sensor is measured ess-strain technology and spacecraft (space station) housing degree of being impacted and bump location technology.Determine mathematical model with physical theories such as elastokinetics and Foundations of Stress Wave in theory, determine model coefficient in conjunction with experiment and semi physical experiment simulation, finally set up the physical mathematics model of real space aircraft (space station) housing degree of being impacted and impingement position.And real-time online ground display space aircraft (space station) housing be impacted process and effect.Mainly be achieved as follows function: 1. determine the accurate position that spacecraft (space station) housing is impacted in real time, and in time on operation and control interface, show.2. determine spacecraft (space station) the housing degree of being impacted and the type that is impacted, thereby tell the deformation extent (elastic deformation or plastic deformation) after spacecraft (space station) housing is impacted.3. when meeting with rammer such as intensive meteoroid, big quality or a large amount of space trashes when spacecraft, judge spacecraft (space station) housing damage degree, determine the scheme of dodging of space craft, or take further emergency measure.
[summary of the invention]
The present invention is a kind of spacecraft (space station) housing degree of being impacted and bump positioning measurment system of real-time online, and ess-strain technology and spacecraft (space station) housing degree of being impacted and bump location technology are measured based on distributed fiberoptic sensor by this system.By the following technical solutions:
The invention discloses a kind of spacecraft (space station) housing degree of being impacted and bump positioning measurment system of real-time online, ess-strain technology and spacecraft (space station) housing degree of being impacted and bump location technology are measured based on distributed fiberoptic sensor by this system; This system comprises optical fiber Bragg sensing system, light signal demodulating system, spacecraft (space station) housing degree of being impacted and bump location Calculation system; Lay distribution type fiber-optic Bragg grating sensor system in spacecraft (space station) housing, after spacecraft (space station) housing is subjected to external impact generation ess-strain, deformation causes the centre wavelength of the monitoring light wave of fiber Bragg grating sensor to change around the rum point, the light signal demodulating system is converted to the rum point ess-strain of three sensors (or more) position on every side to the center wavelength variation value of monitoring light wave, and input is advanced spacecraft (space station) housing degree of being impacted and is clashed in the location Calculation system, and then definite spacecraft (space station) housing degree of being impacted and impingement position.
Wherein, described distributed fiberoptic sensor system comprises that wideband light source, adjustable filter, bragg grating array, optical fiber splicing device, WDM device, wavelength receive and analytical equipment; Wideband light source is transferred to the Fiber Bragg Grating FBG array by optical fiber splicing device and carries out the ess-strain induction after adjustable filter filtering, and the light signal after the induction is transferred to optical fiber splicing device, WDM device, wavelength reception and analytical equipment successively.
Wherein, described wideband light source is broad band laser light source or broad-band illumination diode light-source; Described adjustable filter is the adjustable filter of adjustable optic fibre grating filter or Fabry-Bo Luo tunable optic filter or sound/optic tunable filter or array waveguide grating adjustable filter or liquid crystal tunable optic filter or electricity/optic tunable filter or the humorous wave filter of optical fiber Bragg optical-fibre adjustable or based semiconductor or laser structure; Described optical fiber splicing device is the joints of optical fibre or fiber adapter or fiber alignment device; Described WDM device is grating multiplexer or dense wave division multiplexer or sonet standard wave division multiplex coupler or relaying type wavelength division multiplexer or film filtering type wavelength division multiplexer or Coarse Wave Division Multiplexer; Described wavelength receives and analytical equipment is many optical wavelengthmeters or fiber grating sensing system or spectroanalysis instrument.
Wherein, described Fiber Bragg Grating FBG arranged in arrays is in spacecraft (space station) housing inboard, and closely pastes mutually with the measured point.Each has the Fiber Bragg Grating FBG position of intrinsic centre wavelength and represents a measured position on spacecraft (space station) housing.When elastic deformation or plastic deformation had taken place the measured position on spacecraft (space station) housing, the wavelength of the Fiber Bragg Grating FBG reflection echo light signal of this point changed.The real-time corresponding spacecraft of wavelength variable quantity (space station) shell deformation state.
Wherein, demarcate the corresponding relation that wavelength variable quantity and spacecraft (space station) housing ess-strain value size are determined in the back by experiment, after spacecraft (space station) outside point is clashed into, deformation causes the variation of the monitoring light wave centre wavelength of fiber Bragg grating sensor around the rum point, obtains the rum point ess-strain of three sensors (or more) position on every side by the light signal demodulating system.For example intrinsic centre wavelength is respectively λ
1, λ
2, λ
3Three optical fiber bragg grating FBG l, FBG2, FBG3, the changed wavelength in the i time is measured is respectively Δ λ (i)
1, Δ λ (i)
2, Δ λ (i)
3, can obtain three weight coefficient δ (i)
1=Δ λ (i)
1/ λ
1, δ (i)
2=Δ λ (i)
2/ λ
2, δ (i)
3=Δ λ (i)
3/ λ
3In once bump is measured together (the i time bump), the big more representative rum point of weight coefficient is near more apart from this measurement point.
Wherein, by analytical weight coefficient δ (i)
1, δ (i)
2, δ (i)
3(or more) can obtain the position and the bump degree size of three (or more) Fiber Bragg Grating FBGs of rum point distance, thereby have realized spacecraft (space station) housing degree of being impacted and impact site location.
Wherein, the optical fiber Bragg grating sensing array is determined rum point position and intensity, determine theoretical model based on physics theories such as elastokinetics and Foundations of Stress Wave, determine model parameter or coefficient with the semi physical experiment simulation by experiment, set up the mathematics physics model of real space aircraft (space station) housing degree of being impacted and impingement position.
Wherein, mathematics physics model and optical fiber Bragg grating sensing array after determining mutually combine, and determine spacecraft (space station) housing degree of being impacted and impingement position by the light signal of each measurement point feedback.And real-time online ground display space aircraft (space station) housing be impacted process and effect.Comprise that following function: a. determines the accurate position that spacecraft (space station) housing is impacted in real time, and in time on operation and control interface, show.B. determine spacecraft (space station) the housing degree of being impacted and the type that is impacted, thereby tell the deformation extent (elastic deformation or plastic deformation) after spacecraft (space station) housing is impacted.When c. judging rammers such as meeting with intensive meteoroid, big quality or a large amount of space trashes, spacecraft (space station) housing damage degree is determined the scheme of dodging of space craft, or takes further emergency measure.
Wherein, described software processing system is VC++ language development software systems, and can develop with computer language procedure system compatibles such as Matlab, labviw, VC, VB.
Wherein, this system determines the accurate position that spacecraft (space station) housing is impacted in real time, and in time shows on operation and control interface, the situation of real-time online ground display space aircraft (space station) housing degree of being impacted and impingement position.For the space personnel provide reliable man-machine control interface rationally, the bump degree is carried out diagnostic analysis and the life-span of the crucial framework of spacecraft (space station), structural member and housing is effectively predicted.
Beneficial effect of the present invention: but the accurate position that spacecraft (space station) housing is impacted is determined on the present invention's real-time online ground, and in time on operation and control interface, show.Determine spacecraft (space station) the housing degree of being impacted and the type that is impacted simultaneously, thereby tell the deformation extent (elastic deformation or plastic deformation) after spacecraft (space station) housing is impacted.When meeting with rammer such as intensive meteoroid, big quality or a large amount of space trashes when spacecraft, judge spacecraft (space station) housing damage degree, determine the scheme of dodging of space craft, or take further emergency measure., after the response under the effect of impact, the bump degree is diagnosed and the life-span of crucial framework in space station and housing is predicted at analysis space aircraft (space station) housing.Patent of the present invention has actual application value to the development of following aerospace field.
[Figure of description]
Fig. 1 is spacecraft (space station) housing degree of being impacted and bump positioning measurment system synoptic diagram
Fig. 2 is the Bragg-grating structure synoptic diagram;
Fig. 3 is a wavelength-division multiplex distribution type fiber-optic Bragg grating sensor system schematic.
[embodiment]
The invention discloses a kind of spacecraft (space station) housing degree of being impacted and bump positioning measurment system of real-time online, as shown in Figure 1, ess-strain technology and spacecraft (space station) housing degree of being impacted and bump location technology are measured based on distributed fiberoptic sensor by this system, comprise optical fiber Bragg sensing system 110, light signal demodulating system 120, spacecraft (space station) housing degree of being impacted and bump location Calculation system 130; Lay distribution type fiber-optic Bragg grating sensor system in spacecraft (space station) housing (as 111,112,113), after spacecraft (space station) housing is subjected to external impact generation ess-strain, deformation causes fiber Bragg grating sensor (111 around the rum point 114, the variation of monitoring light wave centre wavelength 112,113); Obtain rum point 114 three sensors (111 on every side by light signal demodulating system 120,112,113) ess-strain of (or more) positions, in ess-strain value input space aircraft (space station) the housing degree of being impacted of sensing station and bump location Calculation system 130, can finally determine spacecraft (space station) housing degree of being impacted and impingement position.
Fig. 2 is the optical fiber with a plurality of gratings, and wherein the part 200 of each black is a grating 210, and each grating has different foveal reflex wavelength X
0, the grating on the difference can measure corresponding ess-strain and vibration situation respectively like this, can make a plurality of gratings in same optical fiber.210 is structure for amplifying patterns of a grating among the figure, and the part 211 of each black is a fiber core part after the light wave change in refraction.
(Fiber Bragg Grating is a kind of simple intrinsic sensing element FBG) to Fiber Bragg Grating FBG, and it utilizes the uv photosensitivity of silicon optical fiber to write in the fiber cores, and Fig. 2 has described the basic structure of fiber grating.The part 211 of each black of grating is a variations in refractive index part after the UV-irradiation among the figure.Fiber core grating bragg reflection wavelength (λ
B) condition can be represented by formula (1):
λ
B＝2×n×Λ (1)
In the formula, Λ is the grating Cycle Length; N is the optical fiber effective refractive index.When wide spectrum light source incides in the optical fiber, grating will reflect wherein with bragg wavelengths
BNarrow spectral component for centre wavelength.In transmission spectrum, this a part of component will disappear λ
BDrift delta λ with stress and temperature
BBe formula (2):
Wherein: ε is an applied stress; P
I, jIt is the photoelastic tensor coefficient of optical fiber; V is a Poisson ratio; α is the thermal expansivity of fiber optic materials (as quartz); Δ T is a temperature variation.
In the following formula: (n
2/ 2) [P
12-v (P
11+ P
12)] factor representative value is 0.22.Therefore, can derive FBG stress under normal temperature and normal stress condition and temperature-responsive condition as shown in the formula:
During the grating measuring ess-strain, at first grating is attached to below the stressed object or side, when stressed object is subjected to time spent of doing of power, grating is simultaneously stressed, is stretched or shrinks, and its intrinsic change is big or diminish like this.Pass through formula: λ
B=2 * n * Λ can know λ
BAlso can change.The initial Λ of grating so
0, have initial Prague central wavelength lambda
0=2 * n * Λ
0By comparison Δ λ=λ to intrinsic Prague centre wavelength and stressed bragg reflection wavelength
B-λ
0, system can converse the size that is under pressure.
Optical fiber Bragg sensing system 110, as shown in Figure 3, comprise that wideband light source 301, adjustable filter 302, optical fiber splicing device 307, Bragg grating fiber array induction installation 303, WDM device 304, wavelength receive and analytical equipment 305 and central processing unit 306, these devices connect by single-mode fiber or multimode optical fiber.
It is very wide (about tens nm to launch bandwidth from wideband light source 301 (broad band laser light source or broad-band illumination diode light-source), for example from 1530nm---light source 1560nm), passed to automatic and adjustable wave filter 302, described adjustable filter can be adjustable optic fibre grating filter or Fabry-Bo Luo tunable optic filter or sound/optic tunable filter or array waveguide grating (Array Wave-guide Grating, AWG) adjustable filter of adjustable filter or liquid crystal tunable optic filter or electricity/optic tunable filter or the humorous wave filter of optical fiber Bragg optical-fibre adjustable or based semiconductor or laser structure, adjustable filter 302 begins to increase fast 1nm from 1530nm and is increased to 1560nm always, increases altogether 30 times.If one second adjustable filter 302 sweep frequency be 300Hz, promptly can reach and repeat a second in this scope of 1530nm+1nm to 1560nm 10 times.It is 0.1 second that light source changes a time, and the Fiber Bragg Grating FBG on all measuring positions can inform central processing unit 306 to the situation of self.
The light transmission of sending from adjustable filter 302 is given optical fiber splicing device 307, described optical fiber splicing device is the joints of optical fibre or fiber adapter or fiber alignment device, after this device space division multiplexing, pass to many Bragg grating fiber array induction installations 303, this installs has tens gratings on each bar, its centre frequency different (30 gratings are for example arranged, from the 1st to the 30th Prague centre frequency be 1530nm, 1531nm, 1532nm ... 1560nm).When the optical source wavelength of adjustable filter 302 was λ i, having only Prague centre wavelength was λ like this
iThe bragg reflection wavelength of grating sensed by the device of back.According to this principle, can access the wavelength variable quantity Δ λ of diverse location.As following calculating formula:
Δλ＝λ
B-λ
0 (5)
Reflection wavelength on the optical fiber that comes out from Bragg grating fiber array induction installation 303 is passed to optical fiber splicing device 307, after space division multiplexing, send WDM device 304 to, described WDM device is grating multiplexer or dense wave division multiplexer or sonet standard wave division multiplex coupler or relaying type wavelength division multiplexer or film filtering type wavelength division multiplexer or Coarse Wave Division Multiplexer, by this device wave division multiplex mode, tell the wavelength variations situation of the grating of some different Prague centre wavelength on the same optical fiber in real time.
The bragg reflection wavelength that comes out from WDM device 304, the reflected light wavelength of passing to the back receives and analytical equipment 305, described wavelength receives and analytical equipment is many optical wavelengthmeters or fiber grating sensing system or spectroanalysis instrument, is reflected bragg wavelength numerical value accurately by this device.Cooperate the reflected light wavelength to receive and analytical equipment 305, on central processing unit 306, can determine spacecraft (space station) housing degree of being impacted and clash into the back, location to show in real time with image.
Described Fiber Bragg Grating FBG array 110 is arranged in spacecraft (space station) housing 115 inboards, and closely pastes mutually with the measured point.Each has the Fiber Bragg Grating FBG of intrinsic centre wavelength and represents a measured position on spacecraft (space station) housing.When elastic deformation or plastic deformation had taken place the measured position on spacecraft (space station) housing, the wavelength of the Fiber Bragg Grating FBG reflection echo light signal of this point changed.Corresponding spacecraft (space station) the shell deformation state of wavelength variable quantity.Can determine corresponding spacecraft (space station) the housing ess-strain of wavelength variable quantity value size after demarcating by experiment.
After spacecraft (space station) outside point is clashed into, deformation causes the variation of the monitoring light wave centre wavelength of fiber Bragg grating sensor around the rum point, obtains the rum point ess-strain of three sensors (or more) position on every side by the light signal demodulating system.Intrinsic centre wavelength is respectively λ
1, λ
2, λ
3Three optical fiber bragg grating FBG l, FBG2, FBG3, their changed wavelength are respectively Δ λ (i)
1, Δ λ (i)
2, Δ λ (i)
3, can obtain three weight coefficient δ
1=Δ λ (i)
1/ λ
1, δ
2=Δ λ (i)
2/ λ
2, δ
3=Δ λ (i)
3/ λ
3In once bump was measured together, the big more representative rum point of weight coefficient was near more apart from this measurement point.By analytical weight coefficient δ (i)
1, δ (i)
2, δ (i)
3(or more) can obtain the position and the bump degree size of three (or more) Fiber Bragg Grating FBGs of rum point distance, thereby have realized spacecraft (space station) housing degree of being impacted and impact site location.
Here, the optical fiber Bragg grating sensing array is measured rum point position and intensity, determine theoretical model based on physics theories such as elastokinetics or Foundations of Stress Wave, determine model parameter or coefficient with the semi physical experiment simulation by experiment, set up the physical mathematics model of real space aircraft (space station) housing degree of being impacted and impingement position.Physical mathematics model after determining combines with the optical fiber Bragg grating sensing array, has determined spacecraft (space station) housing degree of being impacted and impingement position by the light signal of each measurement point feedback.And real-time online ground display space aircraft (space station) housing be impacted process and effect.Comprise following function: 1. determine the accurate position that spacecraft (space station) housing is impacted in real time, and in time on operation and control interface, show.2. determine spacecraft (space station) the housing degree of being impacted and the type that is impacted, thereby tell the deformation extent (elastic deformation or plastic deformation) after spacecraft (space station) housing is impacted.3. when meeting with rammer such as intensive meteoroid, big quality or a large amount of space trashes when spacecraft, judge spacecraft (space station) housing damage degree, determine the scheme of dodging of space craft, or take further emergency measure.
Software processing system is VC++ language development software systems, and can develop with computer language procedure system compatibles such as Matlab, labviw, VC, VB.This software processing system is determined the accurate position that spacecraft (space station) housing is impacted in real time, and in time on operation and control interface, show, the situation of real-time online ground display space aircraft (space station) housing degree of being impacted and impingement position, for the space personnel provide reliable man-machine control interface rationally, the bump degree is carried out diagnostic analysis and the life-span of the crucial framework of spacecraft (space station), structural member and housing is effectively predicted.
The above; only be the basic scheme of specific implementation method of the present invention, but protection scope of the present invention is not limited thereto, any those skilled in the art that are in technical scope disclosed by the invention; the variation that can expect or replacement all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claim.All fall into the implication that is equal to of claim and the variation in the scope all will be included within the scope of claim.
Claims (10)
1. the invention discloses a kind of spacecraft (space station) housing degree of being impacted and bump positioning measurment system of real-time online, ess-strain technology and spacecraft (space station) housing degree of being impacted and bump location technology are measured based on distributed fiberoptic sensor by this system; This system comprises optical fiber Bragg sensing system, light signal demodulating system, spacecraft (space station) housing degree of being impacted and bump location Calculation system; Lay distribution type fiber-optic Bragg grating sensor system in spacecraft (space station) housing, after spacecraft (space station) housing is subjected to external impact generation ess-strain, deformation causes the centre wavelength of the monitoring light wave of fiber Bragg grating sensor to change around the rum point, the light signal demodulating system is converted to the rum point ess-strain of three sensors (or more) position on every side to the center wavelength variation value of monitoring light wave, and input is advanced spacecraft (space station) housing degree of being impacted and is clashed in the location Calculation system, and then definite spacecraft (space station) housing degree of being impacted and impingement position.
2. according to spacecraft (space station) the housing degree of being impacted of the described a kind of real-time online of claim 1 and bump positioning measurment system, it is characterized in that described distributed fiberoptic sensor system comprises that wideband light source, adjustable filter, bragg grating array, optical fiber splicing device, WDM device, wavelength receive and analytical equipment; Wideband light source is transferred to the Fiber Bragg Grating FBG array by optical fiber splicing device and carries out the ess-strain induction after adjustable filter filtering, and the light signal after the induction is transferred to optical fiber splicing device, WDM device, wavelength reception and analytical equipment successively.
3. according to spacecraft (space station) the housing degree of being impacted and bump positioning measurment system of claim 1 or 2 described a kind of real-time onlines, it is characterized in that described wideband light source is broad band laser light source or broad-band illumination diode light-source; Described adjustable filter is the adjustable filter of adjustable optic fibre grating filter or Fabry-Bo Luo tunable optic filter or sound/optic tunable filter or array waveguide grating adjustable filter or liquid crystal tunable optic filter or electricity/optic tunable filter or the humorous wave filter of optical fiber Bragg optical-fibre adjustable or based semiconductor or laser structure; Described optical fiber splicing device is the joints of optical fibre or fiber adapter or fiber alignment device; Described WDM device is grating multiplexer or dense wave division multiplexer or sonet standard wave division multiplex coupler or relaying type wavelength division multiplexer or film filtering type wavelength division multiplexer or Coarse Wave Division Multiplexer; Described wavelength receives and analytical equipment is many optical wavelengthmeters or fiber grating sensing system or spectroanalysis instrument.
4. according to spacecraft (space station) the housing degree of being impacted of the described a kind of real-time online of claim 1 and bump positioning measurment system, it is characterized in that described Fiber Bragg Grating FBG arranged in arrays in spacecraft (space station) housing inboard, and closely paste mutually with the measured point.Each has the Fiber Bragg Grating FBG position of intrinsic centre wavelength and represents a measured position on spacecraft (space station) housing.When elastic deformation or plastic deformation had taken place the measured position on spacecraft (space station) housing, the wavelength of the Fiber Bragg Grating FBG reflection echo light signal of this point changed.The real-time corresponding spacecraft of wavelength variable quantity (space station) shell deformation state.
5. according to spacecraft (space station) the housing degree of being impacted of the described a kind of real-time online of claim 1 and bump positioning measurment system, it is characterized in that demarcating by experiment the corresponding relation that wavelength variable quantity and spacecraft (space station) housing ess-strain value size are determined in the back, after spacecraft (space station) outside point is clashed into, deformation causes the variation of the monitoring light wave centre wavelength of fiber Bragg grating sensor around the rum point, obtains the rum point ess-strain of three sensors (or more) position on every side by the light signal demodulating system.For example intrinsic centre wavelength is respectively λ
1, λ
2, λ
3Three optical fiber bragg grating FBGs 1, FBG2, FBG3, the changed wavelength in the i time is measured is respectively Δ λ (i)
1, Δ λ (i)
2, Δ λ (i)
3, can obtain three weight coefficient δ (i)
1=Δ λ (i)
1/ λ
1, δ (i)
2=Δ λ (i)
2/ λ
2, δ (i)
3=Δ λ (i)
3/ λ
3In once bump is measured together (the i time bump), the big more representative rum point of weight coefficient is near more apart from this measurement point.
6. according to spacecraft (space station) the housing degree of being impacted and bump positioning measurment system of the described a kind of real-time online of claim 1, it is characterized in that by analytical weight coefficient δ (i)
1, δ (i)
2, δ (i)
3(or more) can obtain the position and the bump degree size of three (or more) Fiber Bragg Grating FBGs of rum point distance, thereby have realized spacecraft (space station) housing degree of being impacted and impact site location.
7. according to spacecraft (space station) the housing degree of being impacted of the described a kind of real-time online of claim 1 and bump positioning measurment system, it is characterized in that the optical fiber Bragg grating sensing array determines rum point position and intensity, determine theoretical model based on physics theories such as elastokinetics and Foundations of Stress Wave, determine model parameter or coefficient with the semi physical experiment simulation by experiment, set up the mathematics physics model of real space aircraft (space station) housing degree of being impacted and impingement position.
8. according to spacecraft (space station) the housing degree of being impacted of claim 1 or 7 described a kind of real-time onlines and bump positioning measurment system, mathematics physics model and optical fiber Bragg grating sensing array after it is characterized in that determining mutually combine, and determine spacecraft (space station) housing degree of being impacted and impingement position by the light signal of each measurement point feedback.And real-time online ground display space aircraft (space station) housing be impacted process and effect.Comprise that following function: a. determines the accurate position that spacecraft (space station) housing is impacted in real time, and in time on operation and control interface, show.B. determine spacecraft (space station) the housing degree of being impacted and the type that is impacted, thereby tell the deformation extent (elastic deformation or plastic deformation) after spacecraft (space station) housing is impacted.When c. judging rammers such as meeting with intensive meteoroid, big quality or a large amount of space trashes, spacecraft (space station) housing damage degree is determined the scheme of dodging of space craft, or takes further emergency measure.
9. according to spacecraft (space station) the housing degree of being impacted of the described a kind of real-time online of claim 1 and bump positioning measurment system, it is characterized in that described software processing system is VC++ language development software systems, and can develop with computer language procedure system compatibles such as Matlab, labviw, VC, VB.
10. according to spacecraft (space station) the housing degree of being impacted of the described a kind of real-time online of claim 1 and bump positioning measurment system, it is characterized in that this system determines the accurate position that spacecraft (space station) housing is impacted in real time, and in time on operation and control interface, show the situation of real-time online ground display space aircraft (space station) housing degree of being impacted and impingement position.For the space personnel provide reliable man-machine control interface rationally, the bump degree is carried out diagnostic analysis and the life-span of the crucial framework of spacecraft (space station), structural member and housing is effectively predicted.
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| CN103837333B (en) * | 2014-02-12 | 2016-06-01 | 北京航天时代光电科技有限公司 | A kind of aircraft cabin body buries the method for Fibre Optical Sensor in advance |
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| CN107101589A (en) * | 2016-02-23 | 2017-08-29 | 西门子公司 | A kind of device and method of robot collision detection |
| CN107036655A (en) * | 2017-05-04 | 2017-08-11 | 北京航空航天大学 | A kind of monitoring structural health conditions software desk Implementation method based on fibre optical sensor |
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