CN113514047B - Small-size light triaxial top combination for aerospace - Google Patents
Small-size light triaxial top combination for aerospace Download PDFInfo
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- CN113514047B CN113514047B CN202110624303.0A CN202110624303A CN113514047B CN 113514047 B CN113514047 B CN 113514047B CN 202110624303 A CN202110624303 A CN 202110624303A CN 113514047 B CN113514047 B CN 113514047B
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- miniaturized
- optical fiber
- gyroscope
- gyro
- fiber ring
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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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- 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
- G01C19/725—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 using nxn optical couplers, e.g. 3x3 couplers
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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
- G01C19/728—Assemblies for measuring along different axes, e.g. triads
Abstract
The invention relates to a small-sized light three-axis fiber-optic gyroscope combination for aerospace, which realizes the miniaturization and light weight of the three-axis fiber-optic gyroscope combination for aerospace, expands the application field of a closed-loop fiber-optic gyroscope in the miniaturization of an angular velocity measuring device and belongs to the field of inertial guidance. Compared with the prior art, the invention reduces the number of circuits, reduces the total mass of the gyroscope structure, is beneficial to reducing the whole size, simplifies the assembly process and improves the reliability of circuit connection.
Description
Technical Field
The invention relates to a small-sized light three-axis fiber-optic gyroscope combination for aerospace, which realizes the miniaturization and light weight of the three-axis fiber-optic gyroscope combination for aerospace, expands the application field of a closed-loop fiber-optic gyroscope in the miniaturization of an angular velocity measuring device and belongs to the field of inertial guidance.
Background
The gyroscope is a core device of various inertial measurement systems, is used for sensing angular motion of a carrier relative to an inertial space and measuring angular displacement and angular velocity of the carrier, and can be used for attitude control/stabilization systems of carriers such as missiles, rockets, satellites and the like. The types of gyros currently used in inertial measurement systems are mainly liquid floating gyros, flexible gyros, hemispherical resonator gyros, laser gyros, fiber optic gyros, and the like.
The fiber optic gyroscope is used as a new-generation inertial device, based on narrow-sense relativity theory and Sagnac effect, adopts an optical-mechanical-electrical integration technology, has the characteristics of all solid state, no rotating and friction parts, wide precision application coverage range, large dynamic range, strong environmental adaptability, lower power consumption, distributed structure, high integration degree, quick response and the like, and has the advantages of high reliability, long service life, low power consumption, strong spatial environmental adaptability, lightness, small size and flexible design in principle. Based on the advantages of the fiber-optic gyroscope, the fiber-optic gyroscope becomes one of the main schemes of the gyroscope used in the application fields of various missiles, rockets, satellites and the like. In order to meet the requirements of inertia measurement systems of spacecrafts such as modern lightweight and small satellites, the lightweight and small design of the triaxial fiber-optic gyroscope combination for aerospace must also become the main technical development direction of the fiber-optic gyroscope.
At the present stage, due to factors of the bending limit of the optical fiber and the volume of the optical fiber, the volume of the optical path of the optical fiber gyroscope accounts for a large proportion, and the optical fiber gyroscope is a main bottleneck for the microminiaturization development of the optical fiber gyroscope. Especially for the optical fiber gyroscope, the length and the diameter of the optical fiber directly influence the scale factor of the optical fiber gyroscope, and when the scale factor is increased, the same phase difference is obtained
The smaller the error of the angular rate omega obtained after demodulation is, the higher the precision of the fiber optic gyroscope is. Therefore, there is a certain contradiction between the precision and the miniaturization in the optical fiber gyro. To reduce the volume of the fiber-optic gyroscope, the volume of the optical path part is usually reduced by reducing the length of the fiber-optic coil or reducing the average diameter of the fiber-optic coil, which inevitably causes the precision of the fiber-optic gyroscope to be reduced, so that the application of the fiber-optic gyroscope is greatly restricted. Therefore, on the basis of reducing the size of the optical fiber ring to a certain degree, the overall structure design is needed, devices are reasonably arranged, the circuit part is integrated, the number of circuit boards is reduced, and the light weight of the optical fiber gyroscope is realized while the precision is ensured.
In the aspect of miniaturization of the fiber optic gyroscope, in the current stage, the size of the fiber optic gyroscope is reduced, and the main technical approach is to reduce the length of a fiber optic coil by adopting an ultra-fine diameter fiber with the diameter smaller than that of the existing fiber optic, so as to reduce the average diameter D of the fiber optic coil; meanwhile, all optical components and circuit components adopt miniaturized components. The main technical difficulty is three aspects: firstly, after the length of the optical fiber is shortened and the diameter of the optical fiber is reduced, the precision of the optical fiber gyroscope is reduced, and the length of the optical fiber and the diameter of the optical fiber need to be balanced to a certain extent; the integration and miniaturization of the optical fiber gyroscope circuit are realized, for the optical fiber gyroscope with small volume, after the circuit is miniaturized, various electronic components are densely arranged, and under the condition of high operating frequency of a gyroscope closed loop, a weak signal of Sagnac phase difference is easily interfered by cross coupling, so that the performance of the gyroscope is degraded; thirdly, after further miniaturization of the optical components and circuits, new challenges are brought to assembly manufacturability, assembly difficulty is greatly increased, and new assembly process methods, such as solderless optical path assembly and solder joint coating protection process methods, and long-term reliability research thereof, need to be researched pertinently.
Disclosure of Invention
The technical problem of the invention is solved: the three-axis fiber-optic gyroscope combination overcomes the defects of the prior art, provides a small and light three-axis gyroscope combination for aerospace, realizes the miniaturization and light weight of the three-axis fiber-optic gyroscope combination for aerospace, and expands the application field of the closed-loop fiber-optic gyroscope in the miniaturization of an angular velocity measuring device.
The technical scheme of the invention is as follows:
a three-axis gyroscope assembly for miniature light aerospace comprises: the gyroscope comprises a gyroscope body structure, an outer cover, a bottom cover, an optical fiber ring component, a gyroscope digital circuit, a gyroscope analog circuit, a miniaturized light source, an isolator, a miniaturized 1X 3 coupler, a miniaturized Y waveguide, a miniaturized 2X2 coupler, a subminiature surface-mounted detector, a Darlington tube, an electric connector and an electric connector bracket;
four cylindrical pillars with threaded holes are distributed at the edge of the upper surface of the gyroscope body structure, four bosses with threaded holes are distributed at the center of a pit in the upper surface, and two threaded holes for mounting a miniaturized light source and one threaded hole for mounting a Darlington tube are arranged at the bottom of the pit; the side edge of the front surface is provided with an optical fiber baffle table and a fiber running groove, the inside of the front surface is provided with a rectangular groove for placing an isolator and a miniaturized 1X 3 coupler, three fiber passing holes for passing optical fibers, and three threaded holes below the front surface; the left side surface is provided with a pit for placing an optical fiber ring base, four cylindrical bosses with threaded holes for fixing the optical fiber ring base are distributed around the pit, the bottom of the pit is provided with two threading holes for a lead to pass through, the middle part below the left side surface is provided with a boss with a threaded hole, and two threaded holes are respectively arranged on two sides of the boss; the right side surface is internally provided with four bosses with threaded holes and a pit, the middle part below the right side surface is provided with a boss with a threaded hole, and two sides of each boss are respectively provided with a threaded hole; the rear side surface is provided with a pit for placing an optical fiber ring base and a weight-reducing groove, four cylindrical bosses with threaded holes for fixing the optical fiber ring base are distributed around the pit, the middle part below the rear side surface is provided with a boss with a threaded hole, and two sides of the boss are respectively provided with a threaded hole; a pit for placing the optical fiber ring base is arranged in the lower surface, four bosses with threaded holes for fixing the optical fiber ring base are distributed around the pit, four threaded holes for fixing the bottom cover are arranged outside the pit, and four through holes are distributed around the lower surface;
the optical fiber ring assembly comprises an optical fiber ring, an optical fiber ring base, a gyro single-meter upper cover and a gyro single-meter lower cover; the middle part of the optical fiber ring base is provided with a circular hole; four countersunk holes for being mounted on the gyroscope body structure and a fiber routing groove for allowing optical fibers to pass through are formed in the periphery of the optical fiber ring base; a square groove for mounting a miniaturized Y waveguide and a square groove for placing a miniaturized 2X2 coupler are formed above the optical fiber ring base, two screw holes are formed in the square groove and used for fixing the miniaturized Y waveguide, a circle of optical fiber blocking table is arranged above the optical fiber ring base, and three fiber passing ports are formed in the optical fiber blocking table; a hollow cylindrical structure is arranged below the optical fiber ring base, three bosses with countersunk screw holes are arranged in the cylindrical structure and used for mounting a gyro single-surface lower cover, three longitudinal grooves are distributed on the periphery of the cylindrical structure, and a circle of bosses are arranged below the cylindrical structure and used for cementing the optical fiber ring; four countersunk holes for fixing are formed in the periphery of the top single-surface cover of the gyroscope, a wire passing hole for passing through a signal wire is formed in the middle of the top single-surface cover, and two fiber passing grooves for passing through optical fibers are formed in the two sides of the top single-surface cover; the center of the gyro single-meter lower cover is provided with a circular pit, and three counter bores for fixing the gyro single-meter lower cover on the optical fiber ring base are arranged in the circular pit;
the gyroscope digital circuit comprises two circuits, one circuit is a square circuit board used for receiving signals of the subminiature surface-mounted detector and realizing closed-loop control processing of gyroscope signals, the subminiature surface-mounted detector is welded on the circuit board, the other circuit is a square circuit board used for outputting and receiving external signals outwards, and the two circuit boards are connected by adopting a flexible wire;
the gyroscope analog circuit is a rectangular circuit board for providing driving current for the light source, a flexible wire for connecting the miniaturized light source and the Darlington tube is arranged above the circuit, the flexible wire is also used for being connected with the gyroscope digital circuit, and the flexible wire is arranged below the circuit and is used for being connected with the electric connector;
two threaded holes for fixing the electric connector are formed above the electric connector bracket, and mounting holes for mounting the electric connector bracket on the gyroscope body structure are formed below the electric connector bracket;
twelve mounting holes for fixing on the gyroscope body structure are distributed around the lower part of the outer cover, and a slot for routing flexible wires is arranged below the right side surface;
four countersunk holes are distributed at four corners of the bottom cover and are used for being fixed on the gyroscope body structure.
The installation mode of installing other components on the gyroscope body structure is as follows:
a. horizontally placing the gyroscope body structure on a tool;
b. gluing and fixing the optical fiber ring on a boss of an optical fiber ring base, and winding the tail fiber of the optical fiber ring in an optical fiber baffle table on the upper surface of the optical fiber ring base after the tail fiber of the optical fiber ring passes through a fiber feeding groove; installing the miniaturized Y waveguide into a square groove of an optical fiber ring base, winding the tail fiber of the miniaturized Y waveguide into an optical fiber baffle table on the upper surface of the optical fiber ring base, and welding the tail fiber of the miniaturized Y waveguide with two tail fibers of an optical fiber ring; winding the tail fiber at the input end of the miniaturized Y waveguide in an optical fiber baffle table on the upper surface of the optical fiber ring base; gluing and fixing a miniaturized 2X2 coupler in a square groove of an optical fiber ring base, welding the 3 end of the tail fiber at the output end of the miniaturized 2X2 coupler with the tail fiber at the input end of a miniaturized Y waveguide, coiling the end of the tail fiber at the input end of the miniaturized 2X2 coupler in an optical fiber baffle table on the upper surface of the optical fiber ring base, and coiling the 1 end and the 2 end of the tail fiber at the input end of the miniaturized 2X2 coupler in the optical fiber baffle table on the upper surface of the optical fiber ring base and penetrating through a fiber passing port on the optical fiber baffle table;
c. fixing a gyro single-meter lower cover below the optical fiber ring base; a signal line of a miniaturized Y waveguide penetrates through a wire passing hole in an upper cover of a gyro single meter, the upper cover of the gyro single meter is covered above a base of an optical fiber ring to form an optical fiber ring assembly, then three optical fiber ring assemblies are respectively connected with a cylindrical boss with a threaded hole on a gyro body structure through countersunk holes, and the 1 end and the 2 end of a tail fiber at the input end of a miniaturized 2X2 coupler penetrating out of the three optical fiber ring assemblies are coiled in an optical fiber baffle table through fiber passing grooves on the front surface of the body;
d. installing a miniaturized light source on a gyroscope body structure through a threaded hole, and winding a tail fiber in an optical fiber baffle table after the tail fiber passes through a fiber passing hole on the front surface of the gyroscope body; the isolator is glued and fixed in the rectangular groove, the input end tail fiber is coiled in the optical fiber blocking platform and is welded with the tail fiber of the miniaturized light source, and the output end tail fiber is coiled in the optical fiber blocking platform; gluing and fixing the miniaturized 1X 3 coupler on the lower side of the isolator, winding the 2 ends of the tail fibers at the input end in the optical fiber baffle table, and welding the tail fibers with the tail fibers at the output end of the isolator, wherein the tail fibers at the output end are respectively welded with the 1 ends of the tail fibers at the input end of the miniaturized 2X2 coupler penetrating out of the three optical fiber ring assemblies;
e. fixing the Darlington tube on the gyroscope body structure through a threaded hole, welding a flexible wire of the gyroscope analog circuit with the miniaturized light source and the Darlington tube, welding the flexible wire with the electric connector, and fixing the gyroscope analog circuit on a boss on the right side surface of the gyroscope body structure;
f. fixing a circuit board in a gyro digital circuit on a boss of a gyro body structure, fixing the gyro digital circuit on the gyro body structure, and connecting the gyro digital circuit with a gyro analog circuit through a flexible wire of the gyro analog circuit;
g. three subminiature surface-mount detectors are welded on a digital circuit of the gyroscope, tail fibers welded by the subminiature surface-mount detectors penetrate through the front surface of the gyroscope body structure along fiber passing grooves formed in the side edge of the front surface of the gyroscope body structure, are respectively welded with 2 ends of tail fibers at the input ends of miniaturized 2X2 couplers penetrating out of three fiber ring assemblies, and are coiled in an optical fiber baffle table;
h. fixing the electric connector on the electric connector bracket;
i. fixing the outer cover on the gyroscope body structure;
j. and fixing the bottom cover on the gyroscope body structure.
The surface of the gyroscope body structure is subjected to ceramic anodic oxidation treatment.
The top cover and the bottom cover of the single top meter are made of iron-nickel alloy 1J 85; the gyroscope body structure is made of aluminum alloy 2A 12-T4.
The gyroscope combination realizes closed-loop control processing of the three-axis gyroscope signals by using a gyroscope digital circuit.
The combined envelope size of the gyroscope is 86mm multiplied by 74mm multiplied by 60mm.
The combined weight of the top is not more than 350g.
A three-axis gyroscope assembly for miniature light aerospace comprises: the gyroscope comprises a gyroscope body structure, an outer cover, a bottom cover, an optical fiber ring assembly, a gyroscope digital circuit, a gyroscope analog circuit, a miniaturized light source, an isolator, a miniaturized 1X 3 coupler, a miniaturized Y waveguide, a miniaturized 2X2 coupler and a subminiature surface-mounted detector; the gyroscope digital circuit, the gyroscope analog circuit and the miniaturized light source are all fixed on the gyroscope body structure through screws; the isolator and the miniaturized 1 multiplied by 3 coupler are fixed on the gyroscope body structure through silicon rubber; the optical fiber ring assembly comprises an optical fiber ring, an optical fiber ring base, a gyro single-meter upper cover and a gyro single-meter lower cover, wherein the optical fiber ring is fixed on the optical fiber ring base through a silicon rubber, the gyro single-meter lower cover is fixed on the optical fiber ring base through a screw, and the optical fiber ring base and the gyro single-meter upper cover are fixed on a gyro body structure through screws; the miniaturized Y waveguide is fixed on the optical fiber ring base through a screw; the miniaturized 2X2 coupler is fixed on the optical fiber ring base through silicon rubber. The invention realizes the small-size and light-weight of the triaxial fiber-optic gyroscope combination, reduces the power consumption of the triaxial gyroscope and reduces the size and weight of the triaxial gyroscope.
Compared with the prior art, the invention has the following advantages:
(1) The invention adopts a miniaturized 1X 3 coupler, and the size of the coupler is only phi 2.4X 30mm;
(2) The invention adopts a miniaturized 2X2 coupler with the size of phi 2X 20mm, adopts a miniaturized Y waveguide with the size of 20X 10X 4.5mm, and can assemble both optical devices on an optical fiber ring assembly, thereby realizing the modularization of passive optical devices, reducing the assembly difficulty and improving the assembly efficiency;
(2) The diameter of the optical fiber ring of the core component of the three-axis gyroscope combination for small-sized light aerospace is only 36.2mm, the height is 10mm, the miniaturization of the whole optical fiber gyroscope is realized, the optical fiber adopts the ultra-fine polarization maintaining optical fiber with the cladding diameter of 60 mu m and the coating diameter of 100 mu m, the length of the optical fiber is increased under the condition of small size, and the precision of the optical fiber gyroscope is improved;
(3) The invention adopts the subminiature surface-mounted detector, the size of which is only 7.3 multiplied by 5 multiplied by 2.8mm, compared with the small and medium-sized 8-pin detector in the prior art, the volume is smaller, the subminiature surface-mounted detector can be directly welded on a circuit board in a surface-mounted mode, and the integral size is further reduced;
(4) Compared with the prior art, the invention reduces the number of circuits, reduces the total mass of the gyroscope structure, is beneficial to reducing the whole size, simplifies the assembly process and improves the reliability of circuit connection.
Drawings
FIG. 1 is a block diagram of the apparatus of the present invention;
FIG. 2a is a schematic view of the structural composition of the apparatus of the present invention;
FIG. 2b is a schematic view of a fiber ring assembly;
FIG. 3a is a schematic top view of a gyroscope body of the present invention;
FIG. 3b is a schematic rear view of a gyroscope body of the present invention;
FIG. 3c is a schematic bottom view of the structural body of a spinning top of the present invention;
FIG. 4a is a top view of a fiber ring mount of the present invention;
FIG. 4b is a bottom view of the fiber ring base of the present invention;
FIG. 5 is a top cover structure of the gyro of the present invention;
FIG. 6 is a view of the structure of the lower cover of the gyro unit of the present invention;
FIG. 7 is a schematic diagram of a gyroscope digital circuit board of the present invention;
FIG. 8 is a schematic diagram of a gyro analog circuit board of the present invention;
FIG. 9 is a block diagram of the electrical connector holder of the present invention;
FIG. 10 is a view of the housing of the present invention;
fig. 11 is a bottom cover structure view of the present invention.
Detailed Description
The structure, composition and operation of the present invention will be further described with reference to the accompanying drawings.
As shown in figure 1, along with the development trend of miniaturization of the optical fiber gyroscope, the invention provides a miniature light-weight three-axis gyroscope combination for aerospace, so that the miniaturization and light weight of the three-axis gyroscope combination for aerospace are realized, and the application field of the closed-loop optical fiber gyroscope in the inertia measurement system of the spacecraft such as modern light and small satellites is improved.
As shown in fig. 2a and 2b, a three-axis gyro assembly for compact and lightweight aerospace includes: the gyroscope comprises a gyroscope body structure 1, an outer cover 2, a bottom cover 3, a fiber ring component 4, a gyroscope digital circuit 5, a gyroscope analog circuit 6, a miniaturized light source 7, an isolator 8, a miniaturized 1X 3 coupler 9, a miniaturized Y waveguide 10, a miniaturized 2X2 coupler 11, a microminiature surface-mounted detector 12, a Darlington tube 13, an electric connector 14 and an electric connector support 15;
the gyroscope body structure 1 is used for installing components such as an outer cover 2, a bottom cover 3, a fiber ring component 4, a gyroscope digital circuit 5, a gyroscope analog circuit 6, a miniaturized light source 7, an isolator 8, a miniaturized 1 multiplied by 3 coupler 9, a Darlington tube 13, an electric connector bracket 15 and the like;
the outer cover 2 and the bottom cover 3 are used for protecting various components arranged in the triaxial gyro combination;
the optical fiber ring assembly 4 comprises an optical fiber ring 401, an optical fiber ring base 402, a gyro single-meter upper cover 403 and a gyro single-meter lower cover 404, and is used for installing the miniaturized Y waveguide 10 and the miniaturized 2X2 coupler 11 and protecting the components installed therein;
the gyro digital circuit 5 is used for installing the subminiature surface-mounted detector 12, modulating the miniaturized Y waveguide 10, processing the signal acquired by the subminiature surface-mounted detector 12 and outputting the processed signal to the outside through the electric connector 14;
the gyro analog circuit 6 is used for providing driving current and carrying out temperature control on the miniaturized light source 7 and providing a transmission channel to transmit an output signal of the gyro digital circuit 5 to the electric connector 14;
the miniaturized light source 7 is used for outputting optical signals;
the isolator 8 is used for transmitting the optical signal output by the miniaturized light source 7 backwards and isolating the optical signal transmitted forwards at the rear end of the isolator;
the miniaturized 1 × 3 coupler 9 is used for dividing the optical signal output by the miniaturized light source 7 into three paths;
the miniaturized 2X2 coupler 11 is used for transmitting the optical signal output by the miniaturized 1X 3 coupler 9 to the miniaturized Y waveguide 10 and transmitting the optical signal returned by the miniaturized Y waveguide 10 to the ultra-small surface-mounted detector 12;
the miniaturized Y waveguide 10 is used for dividing the received optical signal into two paths to be transmitted to the optical fiber ring 401, receiving the modulation of the gyro digital circuit 5, and returning the optical signal passing through the optical fiber ring 401 to the miniaturized 2X2 coupler 11;
the microminiature surface-mounted detector 12 is used for receiving the optical signal returned by the miniaturized 2X2 coupler 11, converting the optical signal into an electric signal and outputting the electric signal to the gyro digital circuit 5;
the Darlington tube 13 is used for assisting the gyro analog circuit 6 to control the temperature of the miniaturized light source 7;
the electric connector 14 is used for electrically connecting the triaxial gyro combination to the outside;
an electrical connector holder 15 for holding and fixing the electrical connector 14;
as shown in fig. 3a, 3b and 3c, four cylindrical pillars 101 with threaded holes are distributed on the edge of the upper surface of the top body structure 1, four bosses 103 with threaded holes are distributed in the center of a pit 102 in the upper surface of the top body structure 1, and two threaded holes 104 for mounting the miniaturized light source 10 and one threaded hole 105 for mounting the darlington tube 16 are arranged at the bottom of the pit in the upper surface; the side edge of the front surface of the gyroscope body structure 1 is provided with an optical fiber blocking platform 106 and a fiber-passing groove 107, a rectangular groove 108 for placing the isolator 11 and the miniaturized 1X 3 coupler 9 and three fiber-passing holes 109 for passing optical fibers are arranged in the front surface, and three threaded holes 110 are arranged below the front surface; a pit 111 for placing the optical fiber ring base 4 is arranged on the left side surface of the gyroscope body structure 1, four cylindrical bosses 112 with threaded holes for fixing the optical fiber ring base 4 are distributed around the pit 111, two threading holes 113 for leading wires to pass through are arranged at the bottom of the pit 111, a boss 114 with a threaded hole is arranged in the middle of the lower part of the left side surface, and two threaded holes 115 are respectively arranged on two sides of the boss 114; four bosses 116 with threaded holes and a pit 117 are arranged in the inner part of the right side surface of the gyroscope body structure 1, a boss 118 with threaded holes is arranged in the middle part of the lower part of the right side surface, and two threaded holes 119 are respectively arranged on two sides of the boss 118; a pit 120 for placing the optical fiber ring base 4 and a weight-reducing groove 121 are arranged on the rear side surface of the gyroscope body structure 1, four cylindrical bosses 122 with threaded holes for fixing the optical fiber ring base 4 are distributed around the pit 120, a boss 123 with a threaded hole is arranged in the middle of the lower part of the rear side surface, and two threaded holes 124 are respectively arranged on two sides of the boss 123; a pit 125 for placing the optical fiber ring base 4 is arranged in the lower surface of the gyroscope body structure 1, four bosses 126 with threaded holes for fixing the optical fiber ring base 4 are distributed around the pit 125, four threaded holes 127 for fixing the bottom cover 3 are arranged outside the pit 125, and four through holes 128 are distributed around the lower surface;
as shown in fig. 4a and 4b, the fiber ring base 402 has a circular hole 405 in the middle; four countersunk holes 406 for mounting to the top body structure 1 and a fiber routing slot 407 for passing optical fibers are formed around the top body structure; a square groove 408 for installing the miniaturized Y waveguide 10 and a square groove 409 for placing the miniaturized 2X2 coupler 11 are arranged above the miniaturized Y waveguide, two screw holes 410 are arranged in the square groove 408 for fixing the miniaturized Y waveguide, a circle of optical fiber blocking table 411 is arranged on the periphery above the miniaturized Y waveguide, and three fiber passing openings 412 are formed in the optical fiber blocking table 411; a hollow cylindrical structure 413 is arranged below the top cover, three bosses 414 with countersunk screw holes are arranged in the cylindrical structure 413 and used for mounting the gyro single-surface lower cover 404, three longitudinal grooves 415 are distributed around the cylindrical structure 413, and a circle of bosses 416 are arranged below the cylindrical structure 413 and used for cementing the optical fiber ring 401;
as shown in fig. 5, four countersunk holes 417 for fixing are formed around the top cover 403 of the gyro sheet, a wire passing hole 418 for passing through a signal wire and a wire trough 419 for passing through a signal wire are formed in the middle of the top cover, and two fiber passing grooves 420 for passing through optical fibers are formed on two sides of the top cover;
as shown in fig. 6, the center of the gyro unit lower cover 404 has a circular recess 421, and three counter bores 422 for fixing the gyro unit lower cover 404 on the fiber ring base 402 are formed in the circular recess 421;
as shown in fig. 7, the gyro digital circuit 5 includes two circuits, one is a square circuit board 501 for receiving the signals of the ultra-small surface-mount detector 12 and realizing gyro signal closed-loop control processing, the ultra-small surface-mount detector 12 is welded on the circuit board 501, the other is a square circuit board 502 for outputting and receiving external signals, and the two circuit boards are connected by a flexible wire 503;
as shown in fig. 8, the gyro analog circuit 6 is a rectangular circuit board for supplying a driving current to the light source, and has a flexible wire 601 for connecting the miniaturized light source 7 and the darlington tube 13, a flexible wire 602 for connecting with the gyro digital circuit 5, and a flexible wire 603 for connecting with the electrical connector 14;
as shown in fig. 9, the electrical connector bracket 15 has two threaded holes 1501 on the top for fixing the electrical connector 14, and has mounting holes 1502 on the bottom for mounting the electrical connector bracket 15 on the top body structure;
as shown in fig. 10, twelve mounting holes 201 for fixing the outer cover 2 on the top body structure 1 are distributed around the lower side of the outer cover 2, and a slot 202 for routing a flexible wire 603 is arranged below the right side surface;
as shown in fig. 11, four countersunk holes 301 are distributed at four corners of the bottom cover 3 for fixing the bottom cover 3 on the top body structure 1.
The non-disclosed parts of the present invention are well known in the art.
Claims (12)
1. A three-axis gyroscope combination for small-sized lightweight aerospace is characterized in that: the triaxial gyroscope combination comprises a gyroscope body structure (1), an outer cover (2), a bottom cover (3), an optical fiber ring assembly (4), a gyroscope digital circuit (5), a gyroscope analog circuit (6), a miniaturized light source (7), an isolator (8), a miniaturized 1X 3 coupler (9), a miniaturized Y waveguide (10), a miniaturized 2X2 coupler (11), a microminiature surface-mounted detector (12), a Darlington tube (13), an electric connector (14) and an electric connector support (15);
the gyroscope digital circuit (5), the gyroscope analog circuit (6) and the miniaturized light source (7) are fixed on the gyroscope body structure (1) through screws; the isolator (8) and the miniaturized 1 multiplied by 3 coupler (9) are fixedly arranged on the gyroscope body structure (1) through silicon rubber; the optical fiber ring assembly (4) comprises an optical fiber ring (401), an optical fiber ring base (402), a gyro single-meter upper cover (403) and a gyro single-meter lower cover (404), wherein the optical fiber ring (401) is fixed on the optical fiber ring base (402) through a silicon rubber adhesive, the gyro single-meter lower cover (404) is fixed on the optical fiber ring base (402) through screws, and the optical fiber ring base (402) and the gyro single-meter upper cover (403) are fixed on the gyro body structure (1) together through screws; the miniaturized Y waveguide (10) is fixed on the optical fiber ring base (402) through a screw; the miniaturized 2X2 coupler (11) is fixedly arranged on the optical fiber ring base (402) through silicon rubber;
the gyroscope body structure (1) is used for mounting an optical fiber ring assembly (4), a gyroscope digital circuit (5), a gyroscope analog circuit (6), a miniaturized light source (7), an isolator (8), a miniaturized 1X 3 coupler (9), a miniaturized Y waveguide (10), a miniaturized 2X2 coupler (11), a microminiature surface-mounted detector (12), a Darlington tube (13), an electric connector (14) and an electric connector support (15), and the outer cover (2) and the bottom cover (3) are used for protecting all parts mounted in the gyroscope body structure (1);
the optical fiber ring assembly (4) is used for mounting a miniaturized Y waveguide (10) and a miniaturized 2X2 coupler (11);
the gyroscope digital circuit (5) is used for mounting the ultra-small surface-mounted detector (12), modulating the miniaturized Y waveguide (10), processing signals acquired by the ultra-small surface-mounted detector (12), and outputting the processed signals to the outside through the electric connector (14);
the gyro analog circuit (6) is used for providing driving current for the miniaturized light source (7) and controlling temperature, and providing a transmission channel to transmit an output signal of the gyro digital circuit (5) to the electric connector (14);
the miniaturized light source (7) is used for outputting optical signals;
the isolator (8) is used for transmitting the optical signal output by the miniaturized light source (7) backwards and isolating the optical signal transmitted forwards at the rear end of the isolator;
the miniaturized 1 x 3 coupler (9) is used for dividing an optical signal output by the miniaturized light source (7) into three paths;
the miniaturized 2X2 coupler (11) is used for transmitting the optical signal output by the miniaturized 1X 3 coupler (9) to the miniaturized Y waveguide (10) and transmitting the optical signal returned by the miniaturized Y waveguide (10) to the ultra-small surface-mounted detector (12);
the miniaturized Y waveguide (10) is used for dividing the received optical signal into two paths for transmission, receiving the modulation of the gyro digital circuit (5) and returning the optical signal to the miniaturized 2X2 coupler (11);
the microminiature surface-mounted detector (12) is used for receiving the optical signal returned by the miniaturized 2X2 coupler (11), converting the optical signal into an electric signal and outputting the electric signal to the gyro digital circuit (5);
the Darlington tube (13) is used for assisting the gyro analog circuit (6) to control the temperature of the miniaturized light source (7);
the electric connector (14) is used for electrically connecting the triaxial gyro combination to the outside;
the electrical connector holder (15) is used for supporting and fixing the electrical connector (14).
2. The three-axis gyro combination for compact and lightweight aerospace of claim 1, wherein:
the gyroscope body structure (1) is a hexahedral structure, four cylindrical pillars (101) with threaded holes are distributed on the edge of the upper surface of the gyroscope body structure (1), a concave pit (102) is arranged at the center of the upper surface of the gyroscope body structure (1), four bosses (103) with threaded holes are distributed in the center of the concave pit (102), two threaded holes (104) for mounting a miniaturized light source (7) and one threaded hole (105) for mounting a Darlington tube (13) are arranged at the bottom of the concave pit (102) at the center of the upper surface; the side edge of the front surface of the gyroscope body structure (1) is provided with an optical fiber baffle table (106) and a fiber feeding groove (107), the middle part of the front surface is provided with a rectangular groove (108) for placing an isolator (8) and a miniaturized 1 x 3 coupler (9), three fiber passing holes (109) for passing optical fibers, and three threaded holes (110) below the front surface; a pit (111) for placing an optical fiber ring base (402) is arranged at the center of the left side surface of the gyroscope body structure (1), four cylindrical bosses (112) with threaded holes for fixing the optical fiber ring base (402) are distributed around the pit (111), two threading holes (113) for a lead to pass through are arranged below the pit (111), a boss (114) with a threaded hole is arranged in the middle of the lower part of the left side surface, and two threaded holes (115) are respectively arranged on two sides of the boss (114); four bosses (116) with threaded holes are arranged at four corners of the right side surface of the gyroscope body structure (1), a pit (117) is arranged at the lower part of the right side surface, a boss (118) with a threaded hole is arranged in the middle part below the right side surface, and two threaded holes (119) are respectively arranged at two sides of the boss (118); a pit (120) for placing a fiber ring base (402) is arranged in the center of the rear side face of the gyroscope body structure (1), a weight reducing groove (121) is formed in the right side of the pit (120), four cylindrical bosses (122) with threaded holes for fixing the fiber ring base (402) are distributed on the periphery of the pit (120), a boss (123) with a threaded hole is formed in the middle of the lower portion of the rear side face, and a threaded hole (124) is formed in each of two sides of the boss (123); the lower surface central point of top body structure (1) is provided with pit (125) that are used for placing fiber ring base (402), and pit (125) distributes all around four bosses (126) that are used for the threaded hole of fixed fiber ring base (402), and there are four threaded holes (127) that are used for fixed bottom (3) in pit (125) outside, and the lower surface distributes all around has four through-holes (128).
3. The three-axis gyro combination for compact and lightweight aerospace of claim 1, wherein:
the optical fiber ring assembly (4) comprises an optical fiber ring (401), an optical fiber ring base (402), a gyro single-meter upper cover (403) and a gyro single-meter lower cover (404); the middle part of the optical fiber ring base (402) is provided with a circular hole (405); four countersunk holes (406) for mounting the gyro body structure (1) and a fiber routing groove (407) for passing optical fibers are formed in the periphery of the optical fiber ring base (402); a square groove (408) for installing a miniaturized Y waveguide (10) and a square groove (409) for placing a miniaturized 2X2 coupler (11) are formed above the optical fiber ring base (402), two screw holes (410) for fixing the miniaturized Y waveguide are formed in the square groove (408), a circle of optical fiber blocking table (411) is arranged above the optical fiber ring base (402), and three fiber passing ports (412) are formed in the optical fiber blocking table (411); a hollow cylindrical structure (413) is arranged below the optical fiber ring base (402), three bosses (414) with countersunk screw holes are arranged in the cylindrical structure (413) and used for mounting a gyro single-surface lower cover (404), three longitudinal grooves (415) are distributed on the periphery of the cylindrical structure (413), and a circle of bosses (416) are arranged below the cylindrical structure (413) and used for gluing and fixing the optical fiber ring (401); four countersunk holes (417) for fixing are formed in the periphery of the top sheet upper cover (403), a wire passing hole (418) for passing through a signal wire and a wiring groove (419) for the signal wire are formed in the middle of the top sheet upper cover, and two fiber passing grooves (420) for passing through optical fibers are formed in two sides of the top sheet upper cover; a round pit (421) is formed in the center of the gyro unit lower cover (404), and three counter bores (422) used for fixing the gyro unit lower cover (404) on the optical fiber ring base (402) are formed in the round pit (421).
4. The three-axis gyro combination for compact and lightweight aerospace of claim 1, wherein:
the gyroscope digital circuit (5) comprises two circuits, wherein one circuit board (501) is used for receiving signals of the ultra-small surface-mounted detector (12) and realizing gyroscope signal closed-loop control processing, the ultra-small surface-mounted detector (12) is welded on the circuit board (501), the other circuit board (502) is used for outputting and receiving external signals outwards, and the two circuit boards are connected through a flexible wire (503).
5. The three-axis gyro combination for compact and light aerospace as claimed in claim 1, wherein:
the gyroscope analog circuit (6) is used for providing a circuit board for driving current for the light source, a flexible wire (601) for connecting the miniaturized light source (7) and the Darlington tube (13) is arranged above the circuit, a flexible wire (602) for connecting the gyroscope digital circuit (5) is further arranged above the circuit, and a flexible wire (603) for connecting the electric connector (14) is arranged below the circuit.
6. The three-axis gyro combination for compact and lightweight aerospace of claim 1, wherein:
two threaded holes (1501) used for fixing the electric connector (14) are formed in the upper portion of the electric connector support (15), and mounting holes (1502) used for mounting the electric connector support (15) on the gyroscope body structure are formed in the lower portion of the electric connector support.
7. The three-axis gyro combination for compact and light aerospace as claimed in claim 1, wherein:
twelve mounting holes (201) used for fixing the outer cover (2) on the gyroscope body structure (1) are distributed around the lower part of the outer cover (2), and a slot (202) used for routing a flexible wire (603) is arranged below the right side surface.
8. The three-axis gyro combination for compact and lightweight aerospace of claim 1, wherein:
four countersunk holes (301) are distributed at four corners of the bottom cover (3) and are used for fixing the bottom cover (3) on the gyroscope body structure (1).
9. The three-axis gyro combination for compact and lightweight aerospace of claim 1, wherein:
the mode of installing components in the gyroscope body structure (1) is as follows:
a. horizontally placing the gyroscope body structure (1);
b. gluing and fixing the optical fiber ring (401) on a boss (416) of an optical fiber ring base (402), passing the tail fiber of the optical fiber ring (401) through a fiber passing groove (407), and coiling the tail fiber in an optical fiber baffle table (411) on the upper surface of the optical fiber ring base (402); installing a miniaturized Y waveguide (10) into a square groove (408) of an optical fiber ring base (402), winding a tail fiber of the miniaturized Y waveguide (10) in an optical fiber blocking platform (411) on the upper surface of the optical fiber ring base (402), and welding the tail fiber with two tail fibers of an optical fiber ring (401); winding the tail fiber at the input end of the miniaturized Y waveguide (10) in an optical fiber baffle table (411) on the upper surface of an optical fiber ring base (402); gluing and fixing a miniaturized 2X2 coupler (11) in a square groove (409) of a fiber ring base (402), welding the 3 end of the tail fiber at the output end of the miniaturized 2X2 coupler (11) with the tail fiber at the input end of a miniaturized Y waveguide (10), coiling the welded tail fiber in a fiber baffle table (411) on the upper surface of the fiber ring base (402), coiling the 1 end and the 2 end of the tail fiber at the input end of the miniaturized 2X2 coupler (11) in the fiber baffle table (411) on the upper surface of the fiber ring base (402), and penetrating through a fiber passing port (412) on the fiber baffle table (411);
c. fixing a gyro single-meter lower cover (404) below a fiber ring base (402); a signal line of a miniaturized Y waveguide (10) passes through a wire passing hole (418) in a gyro single-meter upper cover (403), the gyro single-meter upper cover (403) is covered above a fiber ring base (402) to form a fiber ring assembly (4), then three fiber ring assemblies (4) are respectively connected with cylindrical bosses (112, 122 and 126) with threaded holes on a gyro body structure (1) through countersunk holes (406 and 417), and the 1 end and the 2 end of an input end tail fiber of a miniaturized 2X2 coupler (11) penetrating out of the three fiber ring assemblies (4) are coiled in a fiber baffle table (106) through a fiber feeding groove (107) on the front surface of the body;
d. the method comprises the following steps that a miniaturized light source (7) is installed on a gyroscope body structure (1) through a threaded hole (104), a tail fiber penetrates through a fiber passing hole (109) in the front surface of the gyroscope body and is wound in an optical fiber blocking table (106); the isolator (8) is glued and fixed in the rectangular groove (108), the input end tail fiber is coiled in the optical fiber blocking platform (106) and is welded with the tail fiber of the miniaturized light source (7), and the output end tail fiber is coiled in the optical fiber blocking platform (106); gluing and fixing a miniaturized 1X 3 coupler (9) on the lower side of an isolator (8), winding the 2 end of an input end tail fiber in an optical fiber baffle table (106) and welding the 2 end of the input end tail fiber with the output end tail fiber of the isolator (8), and respectively welding the output end tail fiber with the 1 end of the input end tail fiber of a miniaturized 2X2 coupler (11) penetrating out of three optical fiber ring assemblies (4);
e. fixing a Darlington tube (13) on a gyroscope body structure (1) through a threaded hole (105), welding a flexible wire (601) of a gyroscope analog circuit (6) with a miniaturized light source (7) and the Darlington tube (13), welding a flexible wire (603) with an electric connector (14), and fixing the gyroscope analog circuit (6) on a boss (116) on the right side surface of the gyroscope body structure (1);
f. fixing a circuit board (502) in a gyro digital circuit (5) on a boss (103) of a gyro body structure (1), fixing a circuit board (501) in the gyro digital circuit (5) on a cylindrical support (101) of the gyro body structure (1), and connecting the circuit board with a gyro analog circuit (6) through a flexible wire (602) of the gyro analog circuit (6);
g. three subminiature surface-mount detectors (12) are welded on a circuit board (501) in a gyroscope digital circuit (5), tail fibers welded by the subminiature surface-mount detectors (12) penetrate through the front surface of a gyroscope body structure (1) along fiber grooves (107) formed in the side edge of the front surface of the gyroscope body structure, are respectively welded with the tail fibers (2) at the input ends of miniaturized 2X2 couplers (11) penetrating out of three fiber ring assemblies (4), and are coiled in an optical fiber baffle table (106);
h. fixing the electrical connector (14) on the electrical connector support (15);
i. fixing the outer cover (2) on the gyroscope body structure (1);
j. and fixing the bottom cover (3) on the top body structure (1).
10. The three-axis gyro combination for compact and light aerospace as claimed in claim 1, wherein: the surface of the gyroscope body structure (1) is subjected to ceramic anodic oxidation treatment.
11. The three-axis gyro combination for compact and lightweight aerospace of claim 1, wherein: the top cover (403) and the bottom cover (404) of the gyro single watch are made of iron-nickel alloy 1J 85; the gyroscope body structure (1) is made of aluminum alloy 2A 12-T4.
12. The three-axis gyro combination for compact and light aerospace as claimed in claim 1, wherein: the gyroscope combination realizes closed-loop control processing on three-axis gyroscope signals by using a gyroscope digital circuit (5), the envelope size of the gyroscope combination is 86mm multiplied by 74mm multiplied by 60mm, and the weight of the gyroscope combination is not more than 350g.
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| CN114264295A (en) * | 2021-12-06 | 2022-04-01 | 河北汉光重工有限责任公司 | Small-sized biaxial optical fiber gyroscope beneficial to arrangement of optical fiber pigtails |
| CN114322977B (en) * | 2022-03-15 | 2022-06-21 | 西安中科华芯测控有限公司 | Small three-axis optical fiber gyroscope with multiplexing structure |
| WO2023189324A1 (en) * | 2022-03-28 | 2023-10-05 | 住友精密工業株式会社 | Sensor device |
| WO2023189823A1 (en) * | 2022-03-28 | 2023-10-05 | 住友精密工業株式会社 | Sensor device |
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| US8860933B2 (en) * | 2012-07-12 | 2014-10-14 | Honeywell International Inc. | Multi-axis atomic inertial sensor system |
| CN207379509U (en) * | 2017-10-24 | 2018-05-18 | 北京航天时代光电科技有限公司 | A kind of miniaturization optical fiber gyro inertial measuring unit |
| CN109443339B (en) * | 2018-12-10 | 2022-09-06 | 河北汉光重工有限责任公司 | Photoelectric integrated small closed-loop fiber optic gyroscope |
| CN110579204B (en) * | 2019-08-20 | 2021-05-28 | 北京航空航天大学 | Optical fiber coupler array for triaxial integrated optical fiber gyroscope |
| CN111964661B (en) * | 2020-06-30 | 2023-04-14 | 中国科学院微小卫星创新研究院 | High-heat-dissipation, light and small three-axis integrated fiber optic gyroscope structure |
| CN112097756A (en) * | 2020-09-16 | 2020-12-18 | 上海航天控制技术研究所 | Miniature optical fiber gyroscope combined system for satellite |
| CN112665572A (en) * | 2020-12-03 | 2021-04-16 | 贵州航天控制技术有限公司 | Microminiature triaxial integration fiber optic gyroscope |
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