CN106323265A - Narrow line-width inertial-navigation closed-loop photon crystal fiber gyroscope and narrow line-width laser - Google Patents
Narrow line-width inertial-navigation closed-loop photon crystal fiber gyroscope and narrow line-width laser Download PDFInfo
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- CN106323265A CN106323265A CN201610710120.XA CN201610710120A CN106323265A CN 106323265 A CN106323265 A CN 106323265A CN 201610710120 A CN201610710120 A CN 201610710120A CN 106323265 A CN106323265 A CN 106323265A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
- G01C19/58—Turn-sensitive devices without moving masses
- G01C19/64—Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams
- G01C19/72—Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams with counter-rotating light beams in a passive ring, e.g. fibre laser gyrometers
- G01C19/721—Details
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01S—DEVICES USING THE PROCESS OF LIGHT AMPLIFICATION BY STIMULATED EMISSION OF RADIATION [LASER] TO AMPLIFY OR GENERATE LIGHT; DEVICES USING STIMULATED EMISSION OF ELECTROMAGNETIC RADIATION IN WAVE RANGES OTHER THAN OPTICAL
- H01S3/00—Lasers, i.e. devices using stimulated emission of electromagnetic radiation in the infrared, visible or ultraviolet wave range
- H01S3/02—Constructional details
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Abstract
The invention discloses a navigation interference closed-loop photon crystal fiber gyroscope, and the solution of the gyroscope is integrated with an air chamber frequency stabilization technology so that a miniaturized narrow line-width laser (21) with a steady average wavelength can be formed; besides the negative influence on back scattering, back reflection and a nonlinear Kerr effect and a polarization error can be restrained through the line width of the narrow line-width laser (21); finally a hollow-core photon crystal fiber ring (24) is wound with a hollow-core photon crystal fiber (50) with the optimized structure and material, so that the environmental sensibility of a closed-loop fiber gyroscope (10) can be effectively restrained, and requirements of an airborne inertial navigation system can be reached when stability of scale factors, zero-bias stability and environmental suitability of the gyroscope are achieved; moreover, the solution of the closed-loop fiber gyroscope (10) can meet volume, cost and weight requirements thereof on the airborne inertial navigation system and the fiber gyroscope can really support the airborne inertial navigation system.
Description
Technical field
The invention belongs to airborne navigation level closed-loop fiber optic gyroscope technology, be specifically related to a kind of constant multiplier stability, zero inclined
Stability and environmental suitability thereof reach the navigation level of Airborne Inertial Navigation System requirement simultaneously and interfere formula closed loop photonic crystal fiber top
Spiral shell.
Background technology
Fibre optic gyroscope is as the representative of a new generation's gyroscope, its Larger Dynamic war fighting requirement and the adaptability water of complex environment
Flat lifting, the development for strategy air armament platform and air armament is significant.Specifically, Larger Dynamic optical fiber
The requirement of gyroscope, actually refers to: high performance fibre optic gyroscope product, not only should possess stable and low noise when static
Zero offset, and good precision should be provided simultaneously with in whole dynamic range.In Airborne Inertial navigation system, emphasis
Pay close attention to the anglec of rotation change that extraneous turning rate integration causes, be not to pay close attention to current turning rate simply, institute
With the turning rate measurement error in any past, the information accuracy after having influence on.This of Airborne Inertial navigation system
Kind of operating characteristic, implying optical fibre gyro should be under the conditions of various extraneous turning rate, and all can keep accurately measuring is steady
Determine function.In sum, if applying in Airborne Inertial Navigation System by optical fibre gyro, constantly promoting optical fibre gyro static accuracy
On the basis of, also will should constantly promote its constant multiplier performance as an important ring.
Through proactive effort, the bias instaility of fibre optic gyroscope and environmental suitability thereof the most gradually meet airborne ins system
System requirement, the bias instaility under the conditions of the most various applied environments due to 0.01 °/h, but according to the environment of Airborne Inertial Navigation System
Index request, fibre optic gyroscope constant multiplier stability indicator in various harsh environments all should be less than 5ppm magnitude,
But the constant multiplier stability of the fibre optic gyroscope through continuing to optimize also only reaches 20ppm magnitude, and this will be to affect closed loop
Optical fibre gyro product really realize supporting Airborne Inertial Navigation System the most thorny, be also the difficult problem that must solve.
Scientific research engineering specialist for the closed-loop fiber optic gyroscope being applicable to Airborne Inertial Navigation System carried out a large amount of theoretical research and
Engineering practice, the constant multiplier quantitative relationship of closed-loop fiber optic gyroscope expert definition is as follows:
By above-mentioned analysis it can be found that, the constant multiplier of closed-loop fiber optic gyroscope depend on optical fiber sensitivity loop length L and
Its average diameter D, mean wavelength λ of wide spectrum optical signal, half-wave voltage V of integrated optical modulatorπ, and during DA full scale pair
The modulation voltage V answeredPPEtc. parameter.
Focus first on Vπ、VPPThe impact on constant multiplier stability of two parameters.When external in the phase at the end of the eighties in last century
Complete-digital closed-loop scheme proposition after, according to the difference of optical fibre gyro modulation depth, rise at whole staircase waveform and decline
In cycle, the average output constant multiplier of optical fibre gyro and half-wave voltage V of integrated optical modulatorπ, DA full scale time corresponding
Modulation voltage VPPQuadratic power or the cube of variable quantity are directly proportional, and circuit modulation /demodulation is for the impact of constant multiplier stability
It is suppressed to of a sufficiently low.This patent citation complete-digital closed-loop scheme.
Then the impact on constant multiplier stability of two parameters of L, D is paid close attention to.Owing to the length of optical fiber sensitivity loop is with flat
All the full temperature change of diameter, depends primarily on the selection optimization of material parameter, uses the inside and outside coating of High Linear thermal coefficient of expansion
And around ring glue material so that fibre cladding vitreous silica part dragged generation circumferential strain, formed～the optical fiber of 5ppm/ DEG C
Ring length changes, and makes the surface area generation change of the end face of whole fiber optic loop, bottom surface, and the average diameter of fiber optic loop is then due to light
The fine internal layer of ring and the variation tendency of outer layer are it is instead possible to produce small change amount, but its product still presents directrix
The variation tendency of property.Solve the impact of the two parameter, inside and outside coat that thermal linear expansion coefficient is less should be selected and around ring
Glue material reduces change in size Thermo-sensitive；Non-sensitive optical fiber can be used to replace the part that sensitive optical fibre thermal sensitive resin is bigger, fall
The low fiber optic loop size sensitivity to temperature；Eigenfrequency can be used to follow the tracks of makes constant multiplier stability close with fiber optic loop length
System's desensitization, the change only for fiber optic loop average diameter optimizes material and geometric parameter, certainly uses this kind of scheme to make scale
Factor stability with set up dependency around ring optical fiber effective refractive index, also need to use dual oblique wave modulation scheme to make constant multiplier simultaneously
Stability desensitizes with optical fiber effective refractive index, and above several schemes need engineering staff that material behavior is accomplished accurate perception, work
Journey difficulty and quantities are the biggest.Fairly simple engineering proposal is fiber optic loop to carry out accurate temperature control, makes fiber optic loop entirely
Working cycle inside dimension does not changes, and the length making optical fiber sensitivity loop is stable to optic fiber gyroscope graduation factor with average diameter
Property impact be suppressed to of a sufficiently low.This patent citation fiber optic loop precision temperature control scheme.
Finally pay close attention to the impact on constant multiplier stability of the λ parameter.For Airborne Inertial Navigation System to closed-loop fiber optic gyroscope
Constant multiplier stability indicator decomposes, it is desirable to the mean wavelength stability arrived on photodetector photosurface reaches 1ppm magnitude
Within, it is necessary to the mean wavelength stability of light signal reaches 0.1ppm magnitude.At the end of the eighties in last century, the most generally adopt
With super-radiance light emitting diode wide spectrum optical signal carrying out temperature control and driving electric current to control, the mean wavelength making wide spectrum optical signal is steady
It is scheduled on 100ppm magnitude.Phase at the beginning of the nineties in last century turns to the alternative rare-earth doped optical fibre wide spectrum light source of research, this kind of light source
Can provide more stable mean wavelength, light path scheme uses the pump diode laser of 980nm/1480nm to excite er-doped light
Fibre, outgoing mean wavelength reaches close to the ASE wide spectrum optical signal of 1550nm, the mean wavelength stability of the wide spectrum optical signal of output
20ppm, but the mean wavelength stability of the wide spectrum optical signal of such scheme optimization can't reach Airborne Inertial Navigation System requirement.
Within making the impact of the wide spectrum optical signal averaging wavelength stability of arrival photodetector be reduced to 0.1ppm magnitude, both at home and abroad
Engineering staff is in optimized selection for the pumping wavelength of Er-Doped superfluorescent fiber source, pump power, pumping degree of polarization, erbium fibre length,
Erbium fibre temperature is used to control and the Restrain measurement of optical fibre gyro reverse optical signal if desired；Pass through in photodetector front end
Bragg feedback grating carries out narrow spectral filter to original spectrum, and this will make the mean wavelength stability of wide spectrum light source with original spectrum width
And the magnitude of filtering spectrum width ratio square promotes.But above process optimization, still can not make on arrival photosurface is average
1ppm is down in the impact of wavelength stability, so needing mean wavelength directly to be followed the tracks of feedback and controls.External for this
The through engineering approaches open source literature of aspect is less, but from the point of view of the information known, wants to control the mean wavelength of wide spectrum light source, all need
Want a highly stable wavelength reference systems as reference source.In terms of disclosed document, Honeywell company passes through will12C2H2The 1GHz live width DFB absolute wavelength of air chamber frequency stabilization is averaged wavelength shift with reference to, centre wavelength 1531nm arrowband WDM
Detection, four-quadrant photo detector and testing circuit thereof and/difference and mean wavelength computing and the feedback circuit wavelength that is averaged is inclined
The modes such as the resolving of shifting amount and feedback combine, and the standard deviation realizing alternating temperature mean wavelength stability in 1h length of testing speech is less than
The through engineering approaches model machine of 4ppm magnitude, and Draper laboratory uses the principle of similitude and increasingly complex testing program, at 60000s
Length of testing speech in realize alternating temperature mean wavelength performance for stability less than the Laboratory Principle model machine of 1ppm magnitude, but above-mentioned side
The complexity of case is high, and Airborne Inertial Navigation System is higher to volume, cost and the weight demands of closed-loop fiber optic gyroscope, even if so
Scheme success, the probability being finally assembled in closed-loop fiber optic gyroscope product is little.21st century, Stanford is for wide range
Optical signal mean wavelength stability is difficult to the engineering problem suppressed, and attempts using narrow linewidth laser as traditional fiber gyro
Signal input sources, it is desirable within the impact of optic fiber gyroscope graduation factor degree of stability is down to 1ppm by this, but narrow-linewidth laser
The mean wavelength stability of device still has bigger temperature drift phenomenon, it is expected that constant multiplier stability indicator the most very
Difficulty reaches the requirement of Airborne Inertial Navigation System.
Summary of the invention
It is an object of the invention to: the design providing a kind of narrow linewidth to interfere formula closed loop photon crystal optical fiber gyroscope and manufacturer
Method, can make by this method closed-loop fiber optic gyroscope under various external environments encourage, its constant multiplier stability, zero the most steady
Qualitative meet Airborne Inertial Navigation System requirement simultaneously.
Technical scheme: a kind of narrow linewidth laser 21, it includes distributed feedback laser the 41, first optical fiber
Beam splitter the 42, second fiber optic splitter 43, beam-expanding collimation lens 44, air chamber 45, condenser lens the 46, first photodetector assembly
47, the second photodetector assembly 48, microprocessor 49, wherein, the output tail optical fiber of distributed feedback laser 41 and the first light
The input tail optical fiber welding of fine beam splitter 42, the output tail optical fiber of the first fiber optic splitter 42 defeated with the second fiber optic splitter 43 respectively
Entering the input tail optical fiber welding of tail optical fiber and the second photodetector assembly 48, the output tail optical fiber of the second fiber optic splitter 43 is by expanding
Collimating lens 44 is countershaft with air chamber 45, and air chamber 45 rear end is photosensitive by condenser lens 46 and the first photodetector assembly 47
Central area, face or the first photodetector assembly 47 input the fibre core alignment of tail optical fiber, the first photodetector assembly 47, the
Two photodetector assemblies 48 are all connected to microprocessor 49, and microprocessor 49 interconnects with distributed feedback laser 41 phase simultaneously
Connect.
The mean wavelength of distributed feedback laser 41 is 1525～1575nm, and its live width cannot be below 300MHz.
The absworption peak placing gas in air chamber 45 is consistent with the mean wavelength of distributed feedback laser 41.
Described distributed feedback laser the 41, first fiber optic splitter the 42, second fiber optic splitter 43, beam-expanding collimation lens
44, air chamber 45, condenser lens the 46, first photodetector assembly the 47, second photodetector assembly 48, microprocessor 49 encapsulate
Narrow linewidth laser 21 is constituted in housing.
A kind of narrow linewidth inertial navigation level closed loop photon crystal optical fiber gyroscope, it includes that fiber coupler 22, integrated optics are modulated
Device 23, hollow-core photonic crystal fiber ring 24, photodetector assembly 25, closed-loop fiber optic gyroscope circuit part 30 and described narrow
Live width laser instrument 21, narrow linewidth laser 21, fiber coupler 22, integrated optical modulator 23, hollow-core photonic crystal fiber ring
24 connect into closed-loop fiber optic gyroscope light path part 20 in the way of welding, and fiber coupler 22 melts with photodetector assembly 25
Connecing, photodetector assembly 25 and integrated optical modulator 23 connect the input of closed-loop fiber optic gyroscope circuit part 30 respectively simultaneously
On exporting.
Between narrow linewidth laser 21 and fiber coupler 22 and integrated optical modulator 23 and mini optical fibre ring 24
Polarization Control device 26 it is provided with on optical fiber.
Polarization Control device 26 exports tail optical fiber and hollow-core photonic crystal fiber ring 24 when inputting tail optical fiber welding, should be by continuously
Small area analysis, the method for short time interval arc discharge or the transition optical fiber using mode field diameter to mate carry out welding.
Beneficial effects of the present invention: interfere formula closed loop photon crystal optical fiber gyroscope by a kind of narrow linewidth disclosed by the invention
Design and manufacture method, closed-loop fiber optic gyroscope can be made by this method at the various extraneous ring such as Wen Chang, magnetic field, oscillator field
Under the excitation of border, within bias instaility is reduced to 0.01 °/h magnitude, within constant multiplier stability is reduced to 1ppm magnitude, from
And make bias instaility, constant multiplier stability meet Airborne Inertial Navigation System requirement simultaneously, disclosure satisfy that airborne ins system simultaneously
The system requirement to closed-loop fiber optic gyroscope volume, cost and weight, enables closed-loop fiber optic gyroscope to be really applied to airborne ins system
In system.
Accompanying drawing explanation
Fig. 1 is to use narrow linewidth laser, the interference formula closed-loop fiber optic gyroscope principle of hollow-core photonic crystal fiber ring and group
Become block diagram.
Fig. 2 is the internal composition frame chart of narrow linewidth laser.
Fig. 3 is the hollow-core photonic crystal fiber end face design drawing that coiling hollow-core photonic crystal fiber ring uses.
Wherein, 10-closed-loop fiber optic gyroscope, 20-closed-loop fiber optic gyroscope light path part, 30-closed-loop fiber optic gyroscope circuit part,
21-narrow linewidth laser, 22-fiber coupler, 23-integrated optical modulator, 24-hollow-core photonic crystal fiber ring, 25-photoelectricity
Detector assembly, 26-Polarization Control device, 31-optical signal detection and opto-electronic conversion analog circuit, the 32-signal of telecommunication quantify, modulation
Demodulation and numeral resolve output circuit, 33-digital feedback produces and apply analog circuit；41-distributed feedback laser, 42-
First fiber optic splitter, 43-the second fiber optic splitter, 44-beam-expanding collimation lens, 45-air chamber, 46-condenser lens, 47-first
Photodetector assembly, 48-the second photodetector assembly, 49-microprocessor；50-hollow-core photonic crystal fiber, 51-hollow
Photonic crystal fiber air-core, 52-hollow-core photonic crystal fiber parallel air hole array, 53-hollow-core photonic crystal fiber bag
Layer, 54-hollow-core photonic crystal fiber coat.
Detailed description of the invention
The invention will be further described with embodiment below in conjunction with the accompanying drawings:
Referring to Fig. 1, narrow linewidth inertial navigation level closed loop photon crystal optical fiber gyroscope of the present invention includes fiber coupler 22, integrated
Optical modulator 23, hollow-core photonic crystal fiber ring 24, photodetector assembly 25, closed-loop fiber optic gyroscope circuit part 30 and
Narrow linewidth laser 21, wherein, narrow linewidth laser 21, fiber coupler 22, integrated optical modulator 23, hollow photon crystal
Fiber optic loop 24 connects into closed-loop fiber optic gyroscope light path part 20 in the way of welding, and fiber coupler 22 and photodetector group
Part 25 welding, photodetector assembly 25 and integrated optical modulator 23 connect closed-loop fiber optic gyroscope circuit part 30 respectively simultaneously
Input and output on.
It addition, narrow linewidth laser 21 and fiber coupler 22 and integrated optical modulator 23 and hollow photon crystal light
It is provided with Polarization Control device 26 on optical fiber between fine ring 24.
Referring to Fig. 2, narrow linewidth laser 21 of the present invention includes distributed feedback laser the 41, first fiber optic splitter
42, the second fiber optic splitter 43, beam-expanding collimation lens 44, air chamber 45, condenser lens the 46, first photodetector assembly 47,
Two photodetector assemblies 48, microprocessor 49.Wherein, the output tail optical fiber of distributed feedback laser 41 and the first fiber beam splitting
The input tail optical fiber welding of device 42, the output tail optical fiber of the first fiber optic splitter 42 respectively with the input tail optical fiber of the second fiber optic splitter 43
And the second input tail optical fiber welding of photodetector assembly 48, the output tail optical fiber of the second fiber optic splitter 43 is saturating by beam-expanding collimation
Mirror 44 is countershaft with air chamber 45, and condenser lens 46 and the photosurface center of the first photodetector assembly 47 are passed through in air chamber 45 rear end
Territory or the first photodetector assembly 47 input the fibre core alignment of tail optical fiber, first photodetector assembly the 47, second smooth electrical resistivity survey
Surveying device assembly 48 and be all connected to microprocessor 49, microprocessor 49 is connected with each other with distributed feedback laser 41 simultaneously.
Narrow linewidth inertial navigation level of the present invention interferes formula closed loop photon crystal optical fiber gyroscope, by air chamber Frequency Stabilization Technique, is formed flat
The most Wavelength stabilized miniaturization narrow linewidth laser 21, in addition by using structure and the hollow-core photonic crystal fiber of optimization of material
50 coiling hollow-core photonic crystal fiber rings 24, effectively suppress the environment field sensitivity of closed-loop fiber optic gyroscope 10, finally by optimization
The live width of narrow linewidth laser 21 reaches to suppress relevant backscattering, back-reflection, non-linear Kerr effect and polarization error to lead
The negative effect caused, it is achieved bias instaility, constant multiplier stability and environmental suitability thereof reach Airborne Inertial Navigation System simultaneously
Requirement.
Narrow linewidth inertial navigation level closed loop photon crystal optical fiber gyroscope practical set manufacture process of the present invention is as follows:
Step 1: make the mean wavelength stable narrow linewidth laser 21 letter as closed-loop fiber optic gyroscope light path part 20
Number input source.The distributed feedback laser 41 that narrow linewidth laser 21 selects mean wavelength to be 1525～1575nm, its live width
Cannot be below 300MHz.The output tail optical fiber of distributed feedback laser 41 and the input tail optical fiber of the first fiber optic splitter 42 are melted
Connect, by the output tail optical fiber of the first fiber optic splitter 42 respectively with input tail optical fiber and second photodetection of the second fiber optic splitter 43
The input tail optical fiber welding of device assembly 48, by the output tail optical fiber of the second fiber optic splitter 43 by beam-expanding collimation lens 44 and air chamber 45
Countershaft, air chamber 45 rear end is by condenser lens 46 and the photosurface central area of the first photodetector assembly 47 or the first light
Electric explorer assembly 47 inputs the fibre core alignment of tail optical fiber.The narrow linewidth optical signal of distributed feedback laser 41 output is through first
Fiber optic splitter 42, exceedes the luminous power fl transmission of half to the second fiber optic splitter 43, and residue luminous power is by the second photoelectricity
Detector assembly 48 is received, is processed Real-time Feedback adjustment driving electric current by microprocessor 49, swashs for Stable distritation formula feedback
The luminous power output of light device 41；Through the optical signal of the second fiber optic splitter 43, the luminous power exceeding half directly exports, residue
The luminous power C by length centimetres2H2Air chamber 45, C2H2GAS ABSORPTION peak is stable 1525～1575nm and not with outward
Boundary's environment input change, live width about 1GHz, when the live width of distributed feedback laser 41 is far smaller than the live width at GAS ABSORPTION peak
Time, air chamber 45 exports in the range of optical signal mean wavelength will stabilise at 1525～1575nm and not with external environment input change,
The ambient temperature of distributed feedback laser 41 measured in real time by microprocessor 49 by temperature sensor simultaneously, adjusts temperature control in real time
Electric current adjusts luminescence chip temperature, for luminous power and the mean wavelength output of Stable distritation formula feedback laser 41.By above-mentioned
Each device is encapsulated in the interior signal input sources as closed-loop fiber optic gyroscope 10 of a block length cube housing, the mark of closed-loop fiber optic gyroscope 10
Within degree factor stability is expected to be reduced to 1ppm, the narrow linewidth laser 21 of the most preferred live width can suppress relevant and dissipate dorsad
Penetrate, negative effect that back-reflection, non-linear Kerr effect and polarization error cause, within bias instaility arrives 0.01 °/h.
Step 2: use structure and material parameter through the hollow-core photonic crystal fiber 50 optimized and to mate coiling glue,
According to the scheme coiling hollow-core photonic crystal fiber ring 24 of specific symmetry, in winding process note control coiling tension force maximum and
Fluctuation absolute value, coiling can be arranged by ultraviolet radiation or step temperature after completing and solidify.Use structure and material
Material parameter can effectively suppress the environmental sensibility of closed-loop fiber optic gyroscope 10 through the hollow-core photonic crystal fiber 50 optimized, and temperature becomes
Under the excitation of the environment fields such as field, electromagnetic field and oscillator field, within its bias instaility arrives 0.01 °/h.
Step 3: by step 1, step 2 make narrow linewidth laser 21, hollow-core photonic crystal fiber ring 24 and its
Its Universal photoelectric, optical passive component are connected with each other composition closed-loop fiber optic gyroscope light path part 20 according to a definite sequence.Concrete next
Say that the output tail optical fiber of narrow linewidth laser 21 is with Polarization Control device 26 inputs tail optical fiber welding, Polarization Control device 26 exports tail optical fiber
The first end input tail optical fiber with fiber coupler 22 carries out the first end output tail optical fiber and integrated optics of welding, fiber coupler 22
The input tail optical fiber of manipulator 23 carry out welding, two of integrated optical modulator 23 output tail optical fibers respectively with another two Polarization Control
The input tail optical fiber of device 22 carries out welding, the output tail optical fiber of another two Polarization Control devices 22 respectively with hollow-core photonic crystal fiber
The two ends input tail optical fiber of ring 24 carries out the defeated of the second end input tail optical fiber and photodetector assembly 25 of welding, fiber coupler 22
Enter tail optical fiber and carry out welding, form closed-loop fiber optic gyroscope light path part 20.Fusion process passes through ordinary optic fibre heat sealing machine according to setting
Program is carried out, and notices that Polarization Control device 26 exports tail optical fiber and hollow-core photonic crystal fiber ring 24 when inputting tail optical fiber welding, Ying Tong
Cross continuous small area analysis, short time interval arc discharge or use the transition optical fiber of mode field diameter coupling to carry out welding.By closed loop
Fiber-optic gyroscope light path part 20 is combined with closed-loop fiber optic gyroscope circuit part 30, final composition closed-loop fiber optic gyroscope 10.This kind closes
Ring optical fibre gyro 10 is capable of bias instaility, constant multiplier stability and environmental suitability thereof and reaches airborne ins system simultaneously
System requirement.
The narrow linewidth laser selection mean wavelength of narrow linewidth inertial navigation level closed loop photon crystal optical fiber gyroscope of the present invention is
The distributed feedback laser 21 of 1525～1575nm, in the whole operating temperature range of closed-loop fiber optic gyroscope, mean wavelength
Variable quantity is not more than 0.15pm, and wide spectrum light source is amplified in the spontaneous radiation itself relatively passing by use, and has had relatively good flat
All wavelength stabilities.The air chamber made by preferred gas carries out absorbing frequency stabilization, it is possible to make the flat of distributed feedback laser 21
All wavelength stabilities have and flatly promote more greatly.The constant multiplier stability using the closed-loop fiber optic gyroscope 10 of the program is expected to fall
Within as little as 1ppm magnitude.
It addition, hollow-core photonic crystal fiber 50 is by hollow-core photonic crystal fiber air-core 51, hollow-core photonic crystal fiber
Parallel air hole array 52, hollow-core photonic crystal fiber covering 53, hollow-core photonic crystal fiber coat 54 4 part form, logical
Cross specific symmetrical winding method, make hollow-core photonic crystal fiber 50 form the air-core photonic in closed-loop fiber optic gyroscope light path part 20
Crystal optical fibre ring 24.The transmission medium that the main distinction is optical signal of real core fibre that this optical fiber relatively passes by use is air,
Rather than vitreous silica, the change of optical signal transmission medium will bring carrying of a series of closed-loop fiber optic gyroscope environmental adaptability
Rising: by the optimization to hollow-core photonic crystal fiber 50 structure and material parameter, its thermal field sensitivity coefficient reduces by 23 times, and magnetic field is quick
Sense coefficient reduces by 90 times.In addition, when the coherence length long enough of narrow linewidth laser 21, narrow linewidth laser 21 is used to drive
Closed-loop fiber optic gyroscope 10 and the precision approximation using spontaneous radiation to amplify the closed-loop fiber optic gyroscope 10 that wide spectrum light source drives, so
By the live width of optimized choice narrow linewidth laser 21, the relevant back of the body deteriorated due to employing narrow linewidth laser 21 can be suppressed
The negative effect caused to non-reciprocal phase differences such as scattering, back-reflection, non-linear Kerr effect and polarization errors.Comprehensive employing
Preferably narrow linewidth laser 21 and hollow-core photonic crystal fiber 50, closed-loop fiber optic gyroscope 10 is at temperature variable field, electromagnetic field, oscillator field
Under excitation, within its bias instaility is expected to be reduced to 0.01 °/h.
Claims (7)
1. a narrow linewidth laser, it is characterised in that include distributed feedback laser (41), the first fiber optic splitter
(42), the second fiber optic splitter (43), beam-expanding collimation lens (44), air chamber (45), condenser lens (46), the first photodetector
Assembly (47), the second photodetector assembly (48), microprocessor (49), wherein, the output of distributed feedback laser (41)
The input tail optical fiber welding of tail optical fiber and the first fiber optic splitter (42), the output tail optical fiber of the first fiber optic splitter (42) is respectively with second
The input tail optical fiber of fiber optic splitter (43) and the input tail optical fiber welding of the second photodetector assembly (48), the second fiber optic splitter
(43) output tail optical fiber is countershaft with air chamber (45) by beam-expanding collimation lens (44), and condenser lens (46) is passed through in air chamber (45) rear end
Tail optical fiber is inputted with photosurface central area or first photodetector assembly (47) of the first photodetector assembly (47)
Fibre core is directed at, and the first photodetector assembly (47), the second photodetector assembly (48) are all connected to microprocessor (49), with
Time microprocessor (49) be connected with each other with distributed feedback laser (41).
Narrow linewidth laser the most according to claim 1, it is characterised in that the average wave of distributed feedback laser (41)
A length of 1525～1575nm, its live width cannot be below 300MHz.
Narrow linewidth laser the most according to claim 2, it is characterised in that place in air chamber (45) absworption peak of gas with
The mean wavelength of distributed feedback laser (41) is consistent.
Narrow linewidth laser the most according to claim 2, it is characterised in that described distributed feedback laser (41),
One fiber optic splitter (42), the second fiber optic splitter (43), beam-expanding collimation lens (44), air chamber (45), condenser lens (46),
One photodetector assembly (47), the second photodetector assembly (48), microprocessor (49) constitute narrow line in being encapsulated in housing
Wide laser instrument (21).
5. a narrow linewidth inertial navigation level closed loop photon crystal optical fiber gyroscope, it is characterised in that include fiber coupler (22), integrated
Optical modulator (23), hollow-core photonic crystal fiber ring (24), photodetector assembly (25), closed-loop fiber optic gyroscope circuit part
(30) narrow linewidth laser (21) and described in any one of Claims 1-4, narrow linewidth laser (21), fiber coupler
(22), integrated optical modulator (23), hollow-core photonic crystal fiber ring (24) connect into closed-loop fiber optic gyroscope in the way of welding
Light path part (20), and fiber coupler (22) and photodetector assembly (25) welding, simultaneously photodetector assembly (25)
Connect respectively in input and the output of closed-loop fiber optic gyroscope circuit part (30) with integrated optical modulator (23).
Narrow linewidth inertial navigation level closed loop photon crystal optical fiber gyroscope the most according to claim 5, it is characterised in that narrow linewidth swashs
Between light device (21) and fiber coupler (22) and integrated optical modulator (23) and hollow-core photonic crystal fiber ring (24)
Polarization Control device (26) it is provided with on optical fiber.
Narrow linewidth inertial navigation level closed loop photon crystal optical fiber gyroscope the most according to claim 6, it is characterised in that Polarization Control
During device (26) output tail optical fiber and hollow-core photonic crystal fiber ring (24) input tail optical fiber welding, continuous small area analysis, in short-term should be passed through
Between be spaced arc discharge method or use mode field diameter coupling transition optical fiber carry out welding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610710120.XA CN106323265B (en) | 2016-08-23 | 2016-08-23 | Narrow-linewidth inertial navigation level closed-loop photonic crystal fiber gyroscope and narrow-linewidth laser |
Applications Claiming Priority (1)
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| CN110220509A (en) * | 2019-06-05 | 2019-09-10 | 中国科学院半导体研究所 | Hybrid integrated narrow linewidth laser system for high-precision optical fiber gyro |
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| CN117930446A (en) * | 2024-03-25 | 2024-04-26 | 北京航空航天大学 | On-chip integrated optical transceiver component for sensing and working method thereof |
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