CN111060090A - Triaxial integrated satellite-borne fiber optic gyroscope light path - Google Patents
Triaxial integrated satellite-borne fiber optic gyroscope light path Download PDFInfo
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- 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
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- 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
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Abstract
The invention relates to the technical field of optical paths of fiber optic gyroscopes, in particular to a triaxial integrated satellite-borne optical fiber gyroscope optical path, which comprises 2 light sources, 5 1 × 3 fiber optic couplers, 3Y waveguides, 3 fiber rings and 3 detectors, wherein the 2 light sources comprise 1 main part light source and 1 backup light source, two light sources are respectively welded with a single tail fiber port of the 1 × 3 fiber optic couplers, the couplers divide optical signals into 3 paths to respectively provide optical signals for three sensitive axes of the gyroscope, each sensitive axis comprises 1 × 3 fiber optic couplers, 1Y waveguide and 1 fiber ring, wherein the Y waveguides and the fiber rings form a sensitive loop of each gyro axis, the 1 × 3 fiber optic couplers realize the light splitting of interference signals carrying Sagnac phase shift information, the split interference optical signals are detected by the detectors, key devices in the optical path, namely the light sources adopt double light sources, and the optical path has no single-point fault and has higher reliability.
Description
Technical Field
The invention relates to the technical field of optical paths of fiber-optic gyroscopes, in particular to a three-axis integrated satellite-borne optical path of a fiber-optic gyroscope.
Background
The fiber-optic gyroscope is an inertial instrument based on the Sagnac effect, has the advantages of small volume, light weight, wide precision range, no moving parts and the like, and has attracted increasingly wide attention in recent years in the field of satellite aerospace. The gyro light path is a core part of the fiber-optic gyro and is the most important sensitive and detection part of the Sagnac effect. The advantages of low power consumption, high reliability, small volume and light weight are important characteristics of aerospace products. Therefore, the optical path of the satellite-borne fiber-optic gyroscope also needs to meet the requirements of low power consumption, high reliability, small size and light weight.
Fiber optic gyro assemblies for satellites typically include a three-axis gyro to sense the angular rate of rotation of three orthogonal axes. The currently adopted technical schemes mainly comprise two kinds. The first is a triaxial fiber optic gyroscope formed by orthogonally mounting and combining three uniaxial fiber optic gyroscope sensitive axes, and although the configuration has high reliability, the number of optical devices is large, and miniaturization is difficult to realize. Particularly, three light sources are adopted, and the light sources are main energy consumption devices and heating devices of the gyro light path system, so that the power consumption of the gyro is increased by adopting a mode of combining three single-axis fiber-optic gyros, and the difficulty of heat dissipation is also increased. The second scheme is to adopt a mode that three axes share one light source, and the light source is used for providing light signals for the three-axis gyroscope in a light splitting mode through a coupler. According to the scheme, only one light source is used for providing light signals for three axes, so that the volume and the power consumption are reduced, but if the light source or a light splitting coupler behind the light source fails, the failure of the whole gyro combination can be caused, namely, a single-point failure exists.
The fiber optic gyroscope for the satellite faces high-energy particle irradiation environment in space. In order to improve the stability of the satellite-borne fiber optic gyroscope, a gyroscope light path is required to have better radiation resistance. The optical path working wavelength of the fiber-optic gyroscope usually has three working bands of 1550nm, 1310nm and 850 nm. In 1550nm band, the optical fiber has the best radiation resistance, but the 1550nmASE light source is large in volume, and the erbium-doped optical fiber therein has poor radiation resistance, so that complicated protection measures are required, and the volume and the weight of the gyroscope are increased. The 850nm scheme has the best sensitivity and is easy to miniaturize, but the fiber has very high radiation-induced loss at 850 nm.
Disclosure of Invention
The invention aims to provide a triaxial integrated satellite-borne fiber optic gyroscope optical path to solve the problems in the background technology. The triaxial integrated satellite-borne fiber optic gyroscope light path has the advantages of small light source volume, strong irradiation resistance of the light source, high sensitivity and strong irradiation resistance of the fiber optic ring, and is suitable for satellite application.
In order to achieve the purpose, the invention provides the following technical scheme:
a triaxial integrated satellite-borne fiber optic gyroscope light path comprises 2 light sources, 5 optical fiber couplers of 1 x 3, 3Y waveguides, 3 optical fiber rings and 3 detectors;
the 2 light sources are respectively connected with a single tail fiber port of a 1 × 3 optical fiber coupler, the output optical signal of each light source is divided into three paths, and each path provides an optical signal for the one-axis optical fiber gyroscope;
the 5 1 × 3 optical fiber couplers are divided into two stages, and the first stage of optical fiber coupler is 2 for dividing the optical signals output by the 2 light sources into three paths. The three paths of output signals are respectively connected with one tail fiber at the three-port side of the 3 1X 3 optical fiber couplers of the second stage. The tail fiber at one port side of the second stage 3 of the optical fiber coupler is connected with the input tail fiber of the Y waveguide to provide an optical signal for the three gyro sensitive modules;
the input ends of the 3Y waveguides are connected with the single port side of the second-stage 1X 3 optical fiber coupler, input optical signals are divided into two beams, the two beams are polarized and then injected into the optical fiber ring, and two tail fibers of the output ends of the Y waveguides are respectively connected with two tail fibers of the optical fiber ring. During connection, the Y waveguide output tail fiber and the optical fiber ring tail fiber adopt 0-degree counter shaft;
the 3 optical fiber rings are all polarization-maintaining optical fiber rings, and tail fibers of the optical fiber rings are in butt fusion with 0-degree pairs of two Y waveguide output tail fibers;
the 3 detector PIN-FET detector components. The detector tail fibers are respectively connected with one tail fiber at the single port side of the second-stage 1X 3 optical fiber coupler. The method is used for detecting the change of interference optical power caused by Sagnac effect phase shift caused by rotation angular velocity in a sensitive loop consisting of a Y waveguide and a fiber loop.
Further, the optical path of the three-axis integrated satellite-borne fiber optic gyroscope is characterized in that the 2 light sources are SLD light sources, the working wavelength is 1310nm waveband, the optical path is packaged by adopting a single-side six-pin or double-side six-pin, a single-mode tail fiber with the cladding diameter of 80 μm is output, the spectral width is not less than 30nm, the polarization degree is not more than 1dB, the light emitting power is not less than 600 μ W, so that the gyroscope on each axis is guaranteed to be distributed with enough light power, the light source is a core component of the fiber optic gyroscope, a double-light-source scheme is adopted, the light source 1 is a main light source, the light source 2 is a backup light source, a cold backup mode is adopted, the light source 1 works under normal conditions, when the light source 1 fails, the light source 1 is powered on, the light source 2 works, the double-light-source configuration improves the reliability of the optical path of the gyroscope, the cold backup reduces the, and the reasonability of the power parameter configuration of the whole optical path system.
Furthermore, the optical path of the triaxial integrated satellite-borne fiber optic gyroscope is characterized in that the 1 × 3 fiber coupler is a single-mode fiber optic coupler, the splitting ratio is about 33: 33, the splitting ratio deviation is not greater than 3%, and the splitting ratio of the fiber optic coupler has small deviation, so that the optical signal power in the triaxial gyroscope keeps good consistency.
Furthermore, the optical path of the three-axis integrated satellite-borne fiber optic gyroscope is characterized in that the Y waveguide is a ceramic-packaged or stainless steel-packaged small-sized integrated optical modulator to achieve light splitting/combining, polarization and modulation functions, and one input tail fiber and two output tail fibers of the Y waveguide are polarization-maintaining fibers with cladding diameters of 80 mu m.
Further, the optical path of the triaxial integrated satellite-borne fiber optic gyroscope is characterized in that the optical fiber ring is a fiber ring wound by polarization maintaining fibers with cladding diameter of 80 μm and coating diameter of 135 μm, the ring-wound optical fiber not only meets the above dimensional requirements, but also needs to be formed by drawing optical fiber preforms manufactured by adopting a PCVD rod manufacturing process, and if the ring-wound optical fiber is formed by drawing optical fiber preforms manufactured by adopting an MCVD rod manufacturing process, the optical fiber is required to be a doped optical fiber with pure silicon fiber core and fluorine-doped cladding.
Furthermore, the optical path of the three-axis integrated satellite-borne fiber optic gyroscope is characterized in that the detector is a PIN-FET detector component formed by an InGaAs heterojunction photosensitive diode and an FET circuit, and the detector tail fiber is a single-mode tail fiber with the cladding diameter of 80 mu m.
Compared with the prior art, the invention has the beneficial effects that:
the main light source and the backup light source of the invention do not work simultaneously, namely a cold backup mode is adopted, the light source works under normal conditions, when the main light source fails, the main light source is closed, the backup light source is powered on to work, the double light source configuration improves the reliability of the gyro light path, the cold backup reduces the power consumption of the light source, the difference value of the light emitting power of the two main backup light sources is not more than 50 muW, so as to ensure the stability of the receiving power of the detector before and after the light source is switched and the reasonability of the power parameter configuration of the whole light path system.
The three-axis gyroscope shares the mode of one light source, so that the volume and the power consumption of the gyroscope are reduced, the number of couplers is small, and the size and the power consumption are reduced by adopting a miniaturized packaging device. The polarization maintaining fiber ring is wound by the fiber with the coating layer diameter of 135 mu m, and the tail fiber of each device is the tail fiber with the cladding diameter of 80 mu m, so that the volume and the weight of the fiber-optic gyroscope are further reduced. The requirements of small volume, light weight and low power consumption of the satellite-borne fiber-optic gyroscope are met.
The invention selects 1310nm wave band as working wavelength, compared with 1550nm wave band scheme, the volume of light source is small, the anti-radiation ability of light source is strong, and the sensitivity is high. Compared with 850nm wave band scheme, the optical fiber ring has strong radiation resistance. And the optical fiber drawn by the prefabricated rod manufactured by adopting a PCVD rod manufacturing technology or the phosphorus-free doped optical fiber drawn by the pure silicon fiber core fluorine-doped cladding prefabricated rod manufactured by adopting an MCVD rod manufacturing technology is used for ensuring the radiation resistance of the optical fiber. Suitable for satellite applications.
The key device in the light path, namely the light source, adopts double light source backup, and the light path has no single point failure and has higher reliability.
Drawings
Fig. 1 is a schematic diagram of a light path structure of a three-axis integrated satellite-borne fiber optic gyroscope of the invention.
FIG. 2 is a schematic diagram of the optical path principle of the three-axis integrated satellite-borne fiber-optic gyroscope of the present invention.
In the figure: 1-main light source, 2-backup light source, 3-1 × 3 single-mode fiber coupler I, 4-1 × 3 single-mode fiber coupler II, 5-1 × 3 single-mode fiber coupler III, 6-1 × 3 single-mode fiber coupler IV, 7-1 × 3 single-mode fiber coupler V, 8-Y waveguide I, 9-Y waveguide II, 10-Y waveguide III, 11-fiber ring I, 12-fiber ring II, 13-fiber ring III, 14-detector I, 15-detector II and 16-detector III.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper/lower end", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be configured in a specific orientation, and operate, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed/sleeved," "connected," and the like are to be construed broadly, e.g., "connected," which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1-2, the present invention provides a technical solution:
a three-axis integrated satellite-borne fiber optic gyroscope optical path comprises: a master 1310nm low-polarization high-power SLD light source 1 (hereinafter, also referred to as master SLD light source 1 or master SLD light source 1), a backup 1310nm low-polarization high-power SLD light source 2 (hereinafter, referred to as backup SLD light source or backup light source 2), a first-stage optical splitter composed of a 1 × 3 single-mode fiber coupler I3 and a 1 × 3 single-mode fiber coupler II 4, a second-stage optical combiner/splitter composed of a 1 × 3 single-mode fiber coupler III 5, a 1 × 3 single-mode fiber coupler IV 6, and a 1 × 3 single-mode fiber coupler V7, and three polarization-maintaining pigtail Y waveguides: y waveguide I8, Y waveguide II 9, Y waveguide III 10, three polarization-maintaining fiber rings: fiber ring I11, fiber ring II 12, fiber ring III 13, three PIN-FET detectors: detector I14, detector II 15, detector III 16.
The main SLD light source 1 and the backup SLD light source 2 require that the average wavelength is located at a 1310nm waveband, single-side six-needle or double-side six-needle packaging is adopted, a single-mode tail fiber with the cladding diameter of 80 mu m is output, the spectral width is not less than 30nm, the polarization degree is not more than 1dB, and the light output power is not less than 600 mu W. The difference of the light emitting power of the two main backup light sources is not more than 50 muW. The unilateral six-pin or bilateral six-pin package is favorable for reducing the volume of a gyro light path, and compared with the single-mode tail fiber output with the cladding diameter of 125 microns, the single-mode tail fiber output with the cladding diameter of 80 microns is favorable for reducing the bending radius, thereby being favorable for reducing the assembly volume of the gyro light path. The spectral width is not less than 30nm, which is beneficial to reducing the relative intensity noise of the gyroscope and the nonreciprocal errors such as polarization, temperature, back reflection and the like. The polarization degree is not more than 1dB, so that the stability of the gyro light path power is improved. The light output power is not less than 600 muW, which is beneficial to ensuring that sufficient light power is provided for each path of sensitive axis after light splitting. The difference value of the light emitting power of the two main backup light sources is not more than 50 muW, so that the stability of the receiving power of the detector before and after the light sources are switched and the reasonability of the power parameter configuration of the whole light path system are ensured.
The 1X 3 optical fiber couplers I-V (3, 4, 5, 6, 7) all adopt single-mode optical fiber couplers, the coupler tail fibers are single-mode tail fibers with the cladding diameter of 80 mu m, the splitting ratio is about 33: 33, and the deviation of the splitting ratio is not more than 3%. The fiber coupler splitting ratio has small deviation, so that the optical signal power in the three-axis gyroscope keeps good consistency. The single-mode fiber coupler may be a fused taper type, micro-optical element type or integrated waveguide type coupler.
The Y waveguides I-III (8, 9 and 10) are ceramic packaged or stainless steel packaged small-sized integrated optical modulators to complete the functions of light splitting/combining, polarizing and modulating. One input tail fiber and two output tail fibers of the Y waveguide are polarization maintaining fibers with cladding diameters of 80 mu m.
The optical fiber rings I to III (11, 12 and 13) are optical fiber rings wound by polarization maintaining optical fibers with cladding diameter of 80 mu m and coating layer diameter of 135 mu m. Besides meeting the above size requirements, the ring-wound optical fiber also needs to be an optical fiber formed by drawing an optical fiber preform manufactured by adopting a PCVD rod manufacturing process. If the ring-wound optical fiber is formed by drawing an optical fiber preform manufactured by an MCVD rod making process, the optical fiber is required to be a phosphorus-free doped optical fiber with a pure silicon fiber core and a fluorine-doped cladding. So as to ensure that the optical fiber ring has higher radiation resistance. The length and the size of the optical fiber ring are determined according to actual application conditions.
The detectors I-III (14, 15 and 16) are PIN-FET detector components consisting of InGaAs heterojunction photosensitive diodes and FET circuits. The detector tail fiber is a single-mode tail fiber with the cladding diameter of 80 mu m. The detector has high responsivity in a 1310nm wave band, and the FET circuit converts a current signal output by PIN into a voltage signal, so that subsequent signal processing is facilitated.
Specifically, as shown in fig. 2, when the output single-mode pigtail 1-1 of the primary SLD light source 1 is fusion-spliced with the pigtail 3-1 of the 1 × 3 single-mode fiber coupler I3, the 1 × 3 single-mode fiber coupler I3 divides the output optical signal of the primary SLD light source 1 into three parts, and outputs the three parts from the pigtails 3-2, 3-3, and 3-4 of the 1 × 3 single-mode fiber coupler I3, respectively. The tail fiber 3-2 is welded with the tail fiber 5-2 of the 1 multiplied by 3 single-mode fiber coupler III 5, and the optical signal is output from the tail fiber 5-1 after passing through the coupler. The tail fiber 3-3 is welded with the tail fiber 6-2 of the 1 x 3 single-mode fiber coupler IV 6, and the optical signal is output from the tail fiber 6-1 after passing through the coupler. The tail fiber 3-4 is welded with the tail fiber 7-2 of the 1 multiplied by 3 single-mode fiber coupler V7, and the optical signal is output from the tail fiber 7-1 after passing through the coupler. The coupler tail fiber 5-1 is welded with an input tail fiber 8-1 of a Y waveguide I8, an optical signal is polarized through the Y waveguide I8 and is divided into two beams, the two beams of divided light are respectively output from Y waveguide output tail fibers 8-2 and 8-3, the Y waveguide output tail fiber 8-2 and an optical fiber ring tail fiber 11-1 are welded to a shaft at 0 degree, and the Y waveguide output tail fiber 8-3 and the optical fiber ring tail fiber 11-2 are welded to the shaft at 0 degree. Two paths of optical signals output by the Y waveguide enter the optical fiber ring from two tail fibers 11-1 and 11-2 of the optical fiber ring respectively, and are transmitted in the optical fiber ring along the clockwise direction and the anticlockwise direction respectively, when the axial direction of the optical fiber ring has a rotation angular velocity, Sagnac phase shift is generated in the optical fiber ring, namely, when the two paths of optical signals transmitted along the clockwise direction and the anticlockwise direction are recombined in the Y waveguide 8, phase difference is generated. The phase difference influences the interference light intensity, interference light signals are input into a tail fiber 8-1 through a Y waveguide and then are divided into three beams by a coupler 5, one beam of light signals is output by a tail fiber 5-4 of a 1 x 3 single-mode fiber coupler III 5, the tail fiber 5-4 is welded with a tail fiber 14-1 of a detector 14, the interference light signals are injected into the detector I14 for detection, photoelectric conversion is completed, the output light signals are output in a voltage mode, the output voltage reflects the light intensity of the interference signals, the optical path difference of the two beams of interference signals is further reflected, and the rotation angle rate of an optical fiber ring along a sensitive axis is further reflected. In the scheme, one Y waveguide and one optical fiber ring form a sensitive module of the axial optical fiber gyroscope, and one sensitive module and one 1 multiplied by 3 single-mode optical fiber coupler in the second-stage coupler form a sensitive axis. The coupler tail fiber 6-1 is welded with the input tail fiber 9-1 of the Y waveguide II 9, the optical signal enters a second sensitive module, the working principle is the same as that of the first sensitive module, and the interference optical signal generated after transmission in the second sensitive module formed by the Y waveguide II 9 and the optical fiber ring II 12 enters a detector II 15 through a 1 x 3 single-mode optical fiber coupler IV 6 and the tail fiber 6-4 for detection. The coupler tail fiber 7-1 is welded with the input tail fiber 10-1 of the Y waveguide III 10, optical signals enter a third sensitive module, the working principle is the same as that of the first sensitive module, and interference optical signals 1 multiplied by 3 single-mode optical fiber coupler V7 and the tail fiber 7-4 generated after transmission in the third sensitive module formed by the Y waveguide III 10 and the optical fiber ring III 13 enter a detector III 16 for detection. And the output single-mode tail fiber 2-1 of the backup SLD light source 2 is welded with the tail fiber 4-1 of the 1 × 3 single-mode fiber coupler II 4, so that the 1 × 3 single-mode fiber coupler II 4 divides the output optical signal of the backup SLD light source 2 into three parts, and the three parts are respectively output from the tail fibers 4-2, 4-3 and 4-4 of the 1 × 3 single-mode fiber coupler II 4. The tail fiber 4-2 is welded with the tail fiber 5-3 of the 1 multiplied by 3 single-mode fiber coupler III 5, and an optical signal is output from the tail fiber 5-1 after passing through the coupler and enters the first sensitive module. The tail fiber 4-3 is welded with the tail fiber 6-3 of the 1 multiplied by 3 single-mode fiber coupler IV 6, the optical signal is output from the tail fiber 6-1 after passing through the coupler, and the optical signal enters the second sensitive module. The tail fiber 4-4 is welded with the tail fiber 7-3 of the 1 multiplied by 3 single-mode fiber coupler V7, the optical signal is output from the tail fiber 7-1 after passing through the coupler, and the optical signal enters a third sensitive module.
The primary SLD light source 1 and the backup SLD light source 2 do not work at the same time, namely, a cold backup mode is adopted. Under normal conditions, the master SLD light source 1 works, when the master SLD light source 1 breaks down, the master SLD light source 1 is closed, and the backup SLD light source 2 is electrified to work. The double-light-source configuration improves the reliability of a gyro light path, and the cold backup reduces the power consumption of the light source. The difference value of the light emitting power of the two main backup light sources is not more than 50 muW, so that the stability of the receiving power of the detector before and after the light sources are switched and the reasonability of the power parameter configuration of the whole light path system are ensured.
The three-axis gyroscope shares the mode of one light source, so that the volume and the power consumption of the gyroscope are reduced, the number of couplers is small, and the size and the power consumption are reduced by adopting a miniaturized packaging device. The polarization maintaining fiber ring is wound by the fiber with the coating layer diameter of 135 mu m, and the tail fiber of each device is the tail fiber with the cladding diameter of 80 mu m, so that the volume and the weight of the fiber-optic gyroscope are further reduced. The requirements of small volume, light weight and low power consumption of the satellite-borne fiber-optic gyroscope are met.
The scheme selects the 1310nm waveband as the working wavelength, and compared with the 1550nm waveband scheme, the light source has the advantages of small volume, strong radiation resistance and high sensitivity. Compared with 850nm wave band scheme, the optical fiber ring has strong radiation resistance. And the optical fiber drawn by the prefabricated rod manufactured by adopting a PCVD rod manufacturing technology or the phosphorus-free doped optical fiber drawn by the pure silicon fiber core fluorine-doped cladding prefabricated rod manufactured by adopting an MCVD rod manufacturing technology is used for ensuring the radiation resistance of the optical fiber. Suitable for satellite applications.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (10)
1. The optical path is characterized by comprising 2 light sources, a first-stage coupler, a second-stage coupler and 3 detectors, wherein the 2 light sources are connected to an input port of the first-stage coupler, three output ports of the first-stage coupler are respectively connected to one port of the three-port side of the second-stage coupler, the 3 detectors are connected with the other port of the three-port side of the second-stage coupler, and the single-port side of the second-stage coupler is connected with three gyro sensitive modules.
2. The optical path of the triaxial integrated satellite-borne fiber-optic gyroscope of claim 1, wherein the first-stage coupler comprises 2 1 x 3 fiber-optic couplers, the second-stage coupler comprises 31 x 3 fiber-optic couplers, the 2 light sources are respectively connected with a single tail fiber port of the 1 x 3 fiber-optic coupler of the first stage, the output light signal of each light source is divided into three paths, and the three paths of output signals are respectively connected with one tail fiber at the three port side of the 3 x 3 fiber-optic couplers of the second stage.
3. The optical path of the triaxial integrated satellite-borne fiber optic gyroscope according to claim 2, wherein the three-way gyroscope sensing module comprises 3Y waveguides, input ends of the 3Y waveguides are connected to a single port side of the second-stage 1 x 3 fiber coupler, an input optical signal is divided into two beams, the beams are polarized and then injected into the fiber optic ring, and two tail fibers at output ends of the Y waveguides are respectively connected to two tail fibers of the fiber optic ring.
4. The optical path of the triaxial integrated satellite-borne fiber optic gyroscope according to claim 3, wherein the Y waveguide output pigtail and the fiber ring pigtail are 0 ° in-axis.
5. The optical path of the triaxial all-in-one satellite-borne fiber optic gyroscope according to claim 3 or 4, wherein the 3 fiber loops are all polarization-maintaining fiber loops, and fiber loop pigtails are fusion-spliced with two Y-waveguide output pigtail 0 ° pairs of axes.
6. The optical path of the triaxial integrated satellite-borne fiber optic gyroscope according to claim 2, wherein the 3 detectors are PIN-FET detector assemblies composed of InGaAs heterojunction photodiodes and FET circuits, the detector pigtails are single-mode pigtails with cladding diameter of 80 μm, and the detector pigtails are respectively connected with one pigtail on the single port side of the second-stage 1 × 3 fiber coupler.
7. The optical path of the triaxial integrated satellite-borne fiber optic gyroscope according to claim 1, wherein the 2 light sources are SLD light sources, the operating wavelength is 1310nm, the optical path is encapsulated by a single-sided six-pin or double-sided six-pin package, a cladding diameter is 80 μm, the single-mode pigtail is output, the spectral width is not less than 30nm, the polarization degree is not more than 1dB, the light output power is not less than 600 μ W, and the difference between the light output powers of the two light sources is not more than 50 μ W.
8. The optical circuit of a three-axis all-in-one satellite-borne fiber-optic gyroscope according to any one of claims 2-4 and 6-7, wherein the 1 x 3 fiber coupler is a single-mode fiber coupler, the splitting ratio is about 33: 33, and the deviation of the splitting ratio is not more than 3%.
9. The optical path of the triaxial integrated satellite-borne fiber optic gyroscope according to claim 3 or 4, wherein the Y waveguide is a ceramic package or stainless steel package small-sized integrated optical modulator, and performs functions of splitting/combining light, polarizing and modulating, and one input tail fiber and two output tail fibers of the Y waveguide are polarization maintaining fibers with cladding diameters of 80 μm.
10. The optical path of the triaxial integrated satellite-borne fiber gyroscope according to claim 9, wherein the fiber ring is a fiber ring wound by a polarization maintaining fiber with a cladding diameter of 80 μm and a coating diameter of 135 μm, and the polarization maintaining fiber adopted by the wound fiber ring is a fiber drawn by a preform rod manufactured by a PCVD rod manufacturing technology or a fiber drawn by a pure silica fiber core fluorine-doped cladding preform rod manufactured by an MCVD rod manufacturing technology.
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