CN213688375U - Triaxial integrated small optical fiber inertial navigation system - Google Patents
Triaxial integrated small optical fiber inertial navigation system Download PDFInfo
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- CN213688375U CN213688375U CN202022121852.XU CN202022121852U CN213688375U CN 213688375 U CN213688375 U CN 213688375U CN 202022121852 U CN202022121852 U CN 202022121852U CN 213688375 U CN213688375 U CN 213688375U
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Abstract
A three-axis integrated small-sized optical fiber inertial navigation relates to the field of optical fiber inertial navigation and comprises a mechanical framework, an optical fiber gyro component and a quartz flexible accelerometer component, wherein the mechanical framework is a regular hexahedron; the fiber-optic gyroscope assembly and the quartz flexible accelerometer assembly are distributed on six faces of the regular hexahedron. The small-sized fiber-optic inertial navigation is characterized in that a triaxial quartz accelerometer is fused on the basis of a triaxial fiber-optic gyroscope for integrated design, wherein the triaxial fiber-optic gyroscope shares one light source, and forms microminiaturization and low-cost triaxial integrated fiber-optic inertial navigation with the quartz accelerometer, so that the small-sized fiber-optic inertial navigation device can be widely applied to the navigation and guidance fields of small-sized unmanned aerial vehicles, target planes, aviation emergency instruments, intermediate-range missile guidance, small-sized air missiles, accurate guidance bombs, torpedoes and other small-space aircrafts, and the miniaturization is realized on the premise of ensuring the navigation precision.
Description
Technical Field
The utility model relates to an optic fibre is used to lead the field, particularly, relates to a small-size optic fibre of triaxial integration is used to lead.
Background
A Fiber Optic Gyroscope (FOG) is a novel angular rate sensor developed based on the Sagnac effect, and has the advantages of being all solid, fast in starting, long in service life and the like. With the maturity of the fiber optic gyroscope engineering technology, the application range of the fiber optic gyroscope is wider and wider, the development technology of the single-axis closed-loop fiber optic gyroscope is relatively mature, the precision can reach 0.001 degree/h, the three-axis fiber optic gyroscope component can be realized through the simple single-axis fiber optic gyroscope combination, but the volume, the power consumption and the cost after the combination are generally difficult to meet the system requirements, especially the combination has larger volume and cannot be installed in a small aircraft, and the application range of the fiber optic gyroscope and the fiber optic inertial navigation is limited, so that the double-axis and three-axis integrated fiber optic gyroscope and the integrated fiber optic inertial navigation technology are more and.
The current MEMS gyroscope has unique advantages in the aspect of miniaturization, but the precision of the MEMS gyroscope has a certain gap compared with the precision of a fiber optic gyroscope, and through research and analysis, the current domestic microminiaturized inertial navigation with the gyroscope precision of 0.5 degree/h-5 degree/h is in a blank area, so that the practical refractive index of an engineering prototype can be counted.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a triaxial integration's small-size optic fibre is used to lead, its simple structure, and convenient to use not only has higher measurement accuracy, still has characteristics such as with low costs, microminiaturization, light in weight, has more extensive application space.
The embodiment of the utility model is realized like this:
a three-axis integrated small-sized optical fiber inertial navigation system comprises a mechanical framework, an optical fiber gyro assembly and a quartz flexible accelerometer assembly, wherein the mechanical framework is a regular hexahedron; the mechanical framework comprises three first mounting surfaces sharing a vertex and three second mounting surfaces opposite to the three first mounting surfaces; the number of the optical fiber gyro assemblies and the number of the quartz flexible accelerometer assemblies are three, the three optical fiber gyro assemblies are respectively arranged on three first installation surfaces, and the three quartz flexible accelerometer assemblies are respectively arranged on three second installation surfaces.
Further, in other preferred embodiments of the present invention, the middle portion of the second mounting surface is provided with a mounting groove, and the quartz flexible accelerometer assembly is embedded in the mounting groove.
Further, in other preferred embodiments of the present invention, the sensitive axes of the three quartz flexible accelerometer components are all coincident with the central line of the second mounting surface where each is located.
Further, in other preferred embodiments of the present invention, the small-sized fiber optic inertial navigation device further includes a light source assembly, and the light source assembly is disposed on one of the second mounting surfaces and covers the surface of the mounting groove.
Further, in other preferred embodiments of the present invention, the light source assembly includes a light source, a light source driving board and two beam splitters.
Further, in other preferred embodiments of the present invention, the light source is an SLD light source, and the light source driving board is a constant power light source driving board.
Further, in other preferred embodiments of the present invention, the fiber optic gyroscope assembly includes a front board, a Y waveguide, a frameless shielding ring, a detector, and a beam splitter; the front board, the Y waveguide, the detector and the beam splitter are all arranged inside the frameless shielding ring.
Further, in other preferred embodiments of the present invention, the small-sized fiber optic inertial navigation device further includes a signal processing circuit component, the signal processing circuit component is disposed on one of the second mounting surfaces and covers the surface of the mounting groove; the signal processing circuit assembly and the light source assembly are respectively positioned on different second mounting surfaces; the signal processing circuit assembly is electrically connected with the front board and the detector.
Further, in other preferred embodiments of the present invention, the small-sized fiber optic inertial navigation device further includes an inertial navigation resolving circuit assembly, and the inertial navigation resolving circuit assembly is installed outside the signal processing circuit assembly and electrically connected to the signal processing circuit assembly.
Further, in other preferred embodiments of the present invention, the small-sized fiber optic inertial navigation device further includes a temperature sensor, the temperature sensor is disposed on one of the second mounting surfaces and faces the outside of the second mounting surface; the temperature sensor, the signal processing circuit assembly and the light source assembly are respectively positioned on different second mounting surfaces; the temperature sensor is electrically connected with the inertial navigation resolving circuit component.
The embodiment of the utility model provides a beneficial effect is:
the embodiment of the utility model provides a triaxial integrated small-size optical fiber inertial navigation, which comprises a mechanical framework, an optical fiber gyro assembly and a quartz flexible accelerometer assembly, wherein the mechanical framework is a regular hexahedron; the fiber-optic gyroscope assembly and the quartz flexible accelerometer assembly are distributed on six faces of the regular hexahedron. The small-sized fiber-optic inertial navigation is characterized in that a triaxial quartz accelerometer is fused on the basis of a triaxial fiber-optic gyroscope for integrated design, wherein the triaxial fiber-optic gyroscope shares one light source, and forms microminiaturization and low-cost triaxial integrated fiber-optic inertial navigation with the quartz accelerometer, so that the small-sized fiber-optic inertial navigation device can be widely applied to the navigation and guidance fields of small-sized unmanned aerial vehicles, target planes, aviation emergency instruments, intermediate-range missile guidance, small-sized air missiles, accurate guidance bombs, torpedoes and other small-space aircrafts, and the miniaturization is realized on the premise of ensuring the navigation precision.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic view of a three-axis integrated small-sized optical fiber inertial navigation system according to an embodiment of the present invention;
fig. 2 is a schematic optical path diagram of a three-axis integrated small-sized fiber inertial navigation system according to an embodiment of the present invention;
fig. 3 is a schematic block diagram of a three-axis integrated fiber optic gyroscope signal processing circuit assembly for small-scale fiber optic inertial navigation according to an embodiment of the present invention;
fig. 4 is a schematic diagram of a light source resolving circuit of the triaxial integrated miniature fiber optic inertial navigation system according to an embodiment of the present invention;
fig. 5 is a block diagram and a component diagram of a triaxial integrated small-sized fiber optic inertial navigation solution circuit assembly according to an embodiment of the present invention.
Icon: 100-small optical fiber inertial navigation; 110-a mechanical skeleton; 111-mounting grooves; 112-a wire-passing groove; 120-a fiber optic gyro assembly; 121-front placing plate; 122-Y waveguide; 123-frameless shielding ring; 124-a detector; 130-a quartz flexure accelerometer assembly; 140-a light source assembly; 141-a light source; 142-a light source drive board; 143-a beam splitter; 150-signal processing circuit components; 160-inertial navigation resolving circuit component; 170-temperature sensor.
Detailed Description
To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the drawings of the embodiments of the present invention are combined to clearly and completely describe the technical solutions of the embodiments of the present invention, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention. Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
Examples
The present embodiment provides a three-axis integrated compact fiber inertial navigation system 100, which is shown in fig. 1 and includes a mechanical frame 110, a fiber-optic gyroscope assembly 120, and a quartz flexible accelerometer assembly 130.
As shown in fig. 1, the mechanical skeleton 110 is a regular hexahedron; the mechanical skeleton 110 includes three first mounting surfaces sharing a vertex, and three second mounting surfaces opposite to the three first mounting surfaces; the number of the optical fiber gyro assemblies 120 and the number of the quartz flexible accelerometer assemblies 130 are three, the three optical fiber gyro assemblies 120 are respectively arranged on three first installation surfaces, and the three quartz flexible accelerometer assemblies 130 are respectively arranged on three second installation surfaces. The optical fiber inertial navigation system is integrated by fusing a triaxial quartz accelerometer on the basis of a triaxial optical fiber gyroscope to carry out integrated design, wherein the triaxial optical fiber gyroscope shares one light source 141, and forms a microminiaturized and low-cost triaxial integrated optical fiber inertial navigation with the quartz accelerometer. The overall dimension of the small-sized optical fiber inertial navigation system 100 can be less than or equal to 75mm multiplied by 75mm, the total weight is less than or equal to 1000g, and the small-sized optical fiber inertial navigation system can be widely applied to the fields of small-sized air vehicle navigation and guidance such as small-sized unmanned aerial vehicles, target planes, aviation emergency instruments, mid-range missile guidance, small-sized air bombs, accurate guidance bombs, torpedoes and the like, and can be miniaturized on the premise of ensuring the navigation precision.
The middle parts of the second mounting surfaces are provided with mounting grooves 111, and the quartz flexible accelerometer assembly 130 is embedded in the mounting grooves 111. The inside of the mounting groove 111 is provided with a wire passing groove 112, and the sensitive axes of the three quartz flexible accelerometer components 130 are all overlapped with the central line of the second mounting surface where the three quartz flexible accelerometer components are respectively located and are mounted close to the center of the mechanical framework 110, so that the acceleration sensitive measuring points of the quartz flexible accelerometer components 130 are overlapped with the center of mass of the mechanical framework 110 as much as possible, and the measuring precision is improved.
The compact fiber inertial navigation system 100 further includes a light source assembly 140, where the light source assembly 140 is disposed on one of the second mounting surfaces and covers the surface of the mounting groove 111. The light source assembly 140 is fixed by a screw, and the connection cable is fixed by a pressing clamp, and the light source assembly 140 includes a light source 141, a light source driving board 142, and two beam splitters 143. The light source assembly 140 can provide light sources 141 for three fiber-optic gyroscope assemblies 120 at the same time.
Further, the light source 141 is an SLD light source, and the light source driving board 142 is a constant power light source driving board 142. According to the characteristics of the light source 141, the injected current is changed under different temperature conditions, so that the power reaching the detector 124 is consistent under different temperature conditions, and the high-polarization light source 141 is selected as the product light source 141.
The fiber-optic gyroscope assembly 120 comprises a front board 121, a Y waveguide 122, a frameless shielding ring 123, a detector 124 and a beam splitter 143; the front board 121, the Y waveguide 122, the detector 124, and the beam splitter 143 are all disposed inside the frameless shielding ring 123. This no skeleton shielding ring 123 adopts the design of polarization-maintaining no skeleton magnetic screen ring, and its shielding bush and shielding dustcoat material select soft magnetic alloy for use, adopt vacuum annealing, guarantee magnetic screen performance. With 60/100um polarization maintaining fiber, 580m can be wound at most.
The light source assembly 140 and the three product fiber-optic gyroscope assemblies 120 form an optical path system of the small-sized fiber-optic inertial navigation system 100, the optical path system adopts a full polarization-maintaining structure, and includes one high-polarization light source 141, one 1:2 polarization-maintaining beam splitter 143, four 1:1 polarization-maintaining beam splitters 143, three Y waveguides 122, and three detectors 124, and the optical path schematic diagram is shown in fig. 2.
In addition, as shown in fig. 1, the small-sized fiber inertial navigation system 100 further includes a signal processing circuit component 150, wherein the signal processing circuit component 150 is disposed on one of the second mounting surfaces and covers the surface of the mounting groove 111; the signal processing circuit assembly 150 and the light source assembly 140 are respectively located on different second mounting surfaces; the signal processing circuit assembly 150 is electrically connected to the front board 121 and the detector 124. The signal processing circuit assembly 150 is fixedly connected to the second mounting surface through screws, and after the detector 124 converts the optical signal into a voltage signal, the voltage signal is filtered, amplified, modulated and demodulated by the signal processing circuit to finally output a digital quantity proportional to the input angular rate. The processing circuit is as shown in fig. 3, the front board 121 circuit mainly functions to filter and amplify the electrical signal output by the detector 124, the high pass filter filters the direct current component, the low pass filter filters the high frequency component, and finally the high frequency component is amplified by the equidirectional proportion amplifying circuit and then sent to the front amplifying circuit, the front amplifying and a/D converting circuit converts the output signal of the front board 121 circuit into a differential signal, and then the differential signal is converted into a digital signal by the a/D converting circuit, and the FPGA circuit mainly functions to modulate, demodulate and feed back, as shown in fig. 4.
The compact fiber optic inertial navigation system 100 further includes an inertial navigation solution circuit assembly 160, wherein the inertial navigation solution circuit assembly 160 is installed outside the signal processing circuit assembly 150 and electrically connected to the signal processing circuit assembly 150. The inertial navigation solution circuit assembly 160 is fixed by screws, the inertial navigation solution circuit assembly 160 adopts a DSP + CPLD architecture, a DSP chip TMS320VC33 is used as a circuit frame of a core processor, and the inertial navigation solution circuit assembly 160 is shown in fig. 5.
Further, as shown in fig. 1, the compact fiber inertial navigation system 100 further includes a temperature sensor 170, where the temperature sensor 170 is disposed on one of the second mounting surfaces, and faces an outer side of the second mounting surface; the temperature sensor 170, the signal processing circuit assembly 150 and the light source assembly 140 are respectively positioned on different second mounting surfaces; the temperature sensor 170 is electrically connected to the inertial navigation solution circuit assembly 160. The temperature sensor 170 can realize temperature compensation of the compact fiber inertial navigation system 100, so that the measurement result is more accurate.
To sum up, the embodiment of the present invention provides a three-axis integrated small-sized fiber inertial navigation system 100, which includes a mechanical frame 110, a fiber-optic gyroscope assembly 120, and a quartz flexible accelerometer assembly 130, wherein the mechanical frame 110 is a regular hexahedron; the fiber optic gyro assembly 120 and the quartz flexible accelerometer assembly 130 are distributed on six faces of the regular hexahedron. The small-sized fiber-optic inertial navigation device 100 is integrated by fusing a three-axis quartz accelerometer on the basis of a three-axis fiber-optic gyroscope, wherein the three-axis fiber-optic gyroscope shares one light source 141, and forms a microminiaturization and low-cost three-axis integrated fiber-optic inertial navigation device with the quartz accelerometer, so that the small-sized fiber-optic inertial navigation device can be widely applied to the navigation and guidance fields of small-sized aircrafts such as small-sized unmanned planes, target planes, aviation emergency instruments, intermediate-range missile guidance, small-sized air bombs, accurate guidance bombs, torpedoes and the like, and the miniaturization is realized on the.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A triaxial integrated small-sized optical fiber inertial navigation system is characterized by comprising a mechanical framework, an optical fiber gyro assembly and a quartz flexible accelerometer assembly, wherein the mechanical framework is a regular hexahedron; the mechanical framework comprises three first mounting surfaces sharing a vertex, and three second mounting surfaces opposite to the three first mounting surfaces; the number of the optical fiber gyro assemblies and the number of the quartz flexible accelerometer assemblies are three, the three optical fiber gyro assemblies are respectively arranged on the three first mounting surfaces, and the three quartz flexible accelerometer assemblies are respectively arranged on the three second mounting surfaces.
2. The miniature fiber optic inertial navigation system according to claim 1, wherein a mounting groove is formed in the middle of each second mounting surface, and the quartz flexible accelerometer assembly is embedded in the mounting groove.
3. The miniature fiber optic inertial navigation system according to claim 2, wherein the sensitive axes of the three quartz flexible accelerometer components are all coincident with the center line of the second mounting surface on which each is located.
4. The miniature fiber optic inertial navigation system according to claim 3, further comprising a light source assembly, wherein the light source assembly is disposed on one of the second mounting surfaces and covers the surface of the mounting groove.
5. The compact fiber optic inertial navigation system according to claim 4, wherein the light source assembly comprises a light source, a light source driving board and two beam splitters.
6. The miniature fiber optic inertial navigation system of claim 5, wherein the light source is an SLD light source and the light source drive board is a constant power light source drive board.
7. The miniature fiber optic inertial navigation system according to claim 6, wherein the fiber optic gyro assembly comprises a front loading plate, a Y-waveguide, a frameless shield ring, a detector, and one of the beam splitters; the front board, the Y waveguide, the detector and the beam splitter are all arranged inside the frameless shielding ring.
8. The miniature fiber optic inertial navigation system according to claim 7, further comprising a signal processing circuit component, wherein the signal processing circuit component is disposed on one of the second mounting surfaces and covers the surface of the mounting groove; the signal processing circuit assembly and the light source assembly are respectively positioned on different second mounting surfaces; the signal processing circuit component is electrically connected with the front board, the detector and the quartz flexible accelerometer component respectively.
9. The miniature fiber optic inertial navigation system according to claim 8, further comprising an inertial navigation solution circuit assembly, wherein the inertial navigation solution circuit assembly is mounted outside the signal processing circuit assembly and electrically connected to the signal processing circuit assembly.
10. The miniature fiber optic inertial navigation system according to claim 9, further comprising a temperature sensor disposed on one of said second mounting surfaces, facing outward of said second mounting surface; the temperature sensor, the signal processing circuit assembly and the light source assembly are respectively positioned on different second mounting surfaces; the temperature sensor is electrically connected with the inertial navigation resolving circuit assembly.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116026329A (en) * | 2023-03-31 | 2023-04-28 | 中国船舶集团有限公司第七〇七研究所 | High-reliability inertial component and inertial navigation system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116026329A (en) * | 2023-03-31 | 2023-04-28 | 中国船舶集团有限公司第七〇七研究所 | High-reliability inertial component and inertial navigation system |
| CN116026329B (en) * | 2023-03-31 | 2023-05-30 | 中国船舶集团有限公司第七〇七研究所 | High-reliability inertial component and inertial navigation system |
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