CN207379509U - A kind of miniaturization optical fiber gyro inertial measuring unit - Google Patents
A kind of miniaturization optical fiber gyro inertial measuring unit Download PDFInfo
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- CN207379509U CN207379509U CN201721378235.XU CN201721378235U CN207379509U CN 207379509 U CN207379509 U CN 207379509U CN 201721378235 U CN201721378235 U CN 201721378235U CN 207379509 U CN207379509 U CN 207379509U
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Abstract
The utility model is related to a kind of inexpensive miniaturization optical fiber gyro inertial measuring units, belong to inertial survey technique field.3 optical fibre gyro gauge outfits of the utility model share a light source, and 3 optical fibre gyros share block signal processing and interface circuit, reduce the weight and power consumption of product；Targetedly using inferior grade component, cost is reduced；Optical fiber gyro inertial measurement device as the application of aerospace model replaces plain conductor using flexible wires for the first time, improves product reliability and production efficiency；Using light source driving temperature control circuit Two-level ensemble scheme, compared with the volume-diminished more than 50% of traditional circuit.
Description
Technical field
The utility model is related to a kind of miniaturization optical fiber gyro inertial measuring units, belong to inertial survey technique field.
Background technology
The mark that spacecraft develops as high and new technology plays particularly important role in the national defense construction in China.
Local war under the conditions of future high-tech proposes the acquisition capability of information very high requirement, and the attitude stability of space flight is
Premise and the guarantee of each tasks such as aiming, docking are efficiently performed, wherein inertia type instrument is the key that attitude control system again
Sensor, it directly affects the precision and performance of attitude control system.The inertia measurement of spacecraft generally use gyroscope composition
Device collectively constitutes the attitude measurement system of satellite with optical sensor (such as infrared horizon, sun sensor and star sensor)
System.There is no the characteristic of accumulated error using gyro short time high certainty of measurement and optical sensor, the two complements each other, common
To lasting high-precision attitude and attitude angular rate metrical information.
Optical fibre gyro is a kind of all solid state inertia type instrument, it has the advantages that not available for traditional electro-mechanical instrument.It is only
The closed-loop system being made of optical device and electronic device determines own angular velocity by detecting the phase difference of two-beam, because
This in structure it be complete solid state gyro, without any moving component.Optical fibre gyro is exactly in its principle and structure
The advantages of, make it that there is apparent advantage in many application fields, especially very high to product reliability and life requirements
On spacecraft, main feature shows the following aspects：(1) high-precision：External high-precision optical fiber gyro precision has reached
0.00038°/h；(2) it is all solid state：The component of optical fibre gyro is all solid, has anti-vacuum, anti-vibration and the characteristic of impact；
(3) long-life：Critical optical device used in optical fibre gyro can all meet the space application long life requirement of 15 years；(4) height can
By property：Optical fibre gyro structure design is flexible, and production technology is relatively easy, it is convenient to it is carried out the Redundancy Design of circuit or
Person forms inertial measurement system using slack gyro, can so improve the reliability of system.
Optical fiber gyro inertial measurement device can thus measure mostly using the discrete designing scheme of three axis in the prior art
Three axis of spacecraft is compared with the posture of inertial space, but this designing scheme cost is higher, and small product size is larger, it is impossible to preferable full
The miniaturization of foot future space flight, cost degradation demand.
Utility model content
The technology of the utility model solves the problems, such as：To overcome the deficiencies of the prior art and provide a kind of optical fibre gyro inertia
Measuring device by optoelectronic integration and cost control engineering, meets low cost, the requirement of miniaturization.
The technical solution of the utility model is：
A kind of optical fiber gyro inertial measurement device, peripheral equipment include extraneous power control system and extraneous gesture stability point
System；
The device includes body, upper cover, three-axis integrative fibre optic gyroscope, light source driving temperature control module, electronic cabinets, signal
Processing and interface module, secondary power supply module and bottom cover；
The body is a hollow cuboid；
The hollow cylinder that the upper cover carries head cover for one, head cover are an integral molding structure with hollow cylinder；
Light source is carried inside the three-axis integrative fibre optic gyroscope；
The light source driving temperature control module provides stable driving electricity for the light source inside three-axis integrative fibre optic gyroscope
Stream, and provide temperature monitoring and temperature control current for the constant temperature of light source tube core；
The hollow shell that the electronic cabinets carry head cover for one, head cover are an integral molding structure with housing；
The angular velocity signal that the signal processing is used to receive according to the setting cycle with interface module carries out
Extraneous attitude control subsystem is sent to after smooth；
The secondary power supply module is used to the supply voltage of extraneous power control system being converted into three-axis integrative optical fiber
Gyroscope, light source driving temperature control module and signal processing and the voltage needed for interface module；
Three gyroscopes in the three-axis integrative fibre optic gyroscope are respectively gyroscope A, gyroscope B and gyroscope C；
Gyroscope A, gyroscope B are fixedly mounted on adjacent two side of body, and gyroscope C is fixedly mounted on the top surface of body；
The light source driving temperature control module is mounted on the side of body；
The signal processing is fixedly mounted on the inside of electronic cabinets with interface module；
The secondary power supply module is fixedly mounted on bottom cover the upper surface of；
The bottom cover is fixedly mounted on the bottom of electronic cabinets, i.e. signal processing and interface module and secondary power supply
Module is fixedly mounted in the space of bottom cover and electronic cabinets envelope；
The bottom of the body is fixedly mounted on the top of electronic cabinets；
The upper cover is covered on body, i.e. light source driving temperature control module and three-axis integrative fibre optic gyroscope is fixedly mounted on
In the space that upper cover and body are formed；
Connected between the secondary power supply module and light source driving temperature control module by flexible wires, secondary power supply module with
It is connected between signal processing and interface module by flexible wires, between secondary power supply module and three-axis integrative fibre optic gyroscope
It is connected by flexible wires, is connected between signal processing and interface module and three-axis integrative fibre optic gyroscope by flexible wires,
It is connected between three-axis integrative fibre optic gyroscope and light source driving temperature control module by flexible wires.
The course of work：Using extraneous power control system supply voltage, secondary power supply module are provided to secondary power supply module
Supply voltage is converted into three-axis integrative fibre optic gyroscope, light source driving temperature control module and signal processing and interface module institute
The voltage needed；Light source driving temperature control module provides stable driving current for the power supply in three-axis integrative fibre optic gyroscope, and is
Light source tube core constant temperature provides temperature monitoring and temperature control current；After the power supply of three-axis integrative fibre optic gyroscope, three-axis integrative optical fibre gyro
The angular velocity signal detected is sent to signal processing and interface module, signal processing and interface module by instrument in real time
Extraneous attitude control subsystem is sent to after the angular velocity signal received is integrated according to the setting cycle.
The beneficial effects of the utility model are：
(1) the utility model passes through the fibre optic gyroscope of triaxial integration, signal processing and interface module and collection
Light source driving temperature control module into change effectively reduces the volume of device, can solve traditional fiber gyroscopic inertia measuring device body
The problem of product is big；
(2) connected in the device of the utility model using flexible wires, help to reduce the mutually dry of interiors of products signal wire
It disturbs and enhances the ability of environmental suitability, while improve the efficiency and reliability of assembling process；
(3) device of the utility model drives temperature control module instead of traditional analog circuit using one piece of integrated optical source
Plate, small, full electromagnetic shielding can be directly connected to body heat loss through conduction.
(4) the utility model is related to a kind of inexpensive miniaturization optical fiber gyro inertial measuring unit, inertia measurement skill is belonged to
Art field.3 optical fibre gyro gauge outfits of the utility model share a light source, 3 optical fibre gyros share block signal processing with
Interface circuit reduces the weight and power consumption of product；Targetedly using inferior grade component, cost is reduced；As space
Navigate model application optical fiber gyro inertial measurement device for the first time using flexible wires replace plain conductor, improve product reliability and
Production efficiency；Using light source driving temperature control circuit Two-level ensemble scheme, compared with the volume-diminished more than 50% of traditional circuit.
Description of the drawings
Fig. 1 is the composition schematic diagram of the measuring device of the utility model.
Specific embodiment
A kind of low cost miniaturization optical fiber gyro inertial measuring unit, including body, electronic cabinets, three-axis integrative optical fiber top
Spiral shell instrument, secondary power supply module, signal processing and interface module and light source driving temperature control module.Gyroscope is mounted on this side
Face and top, signal processing are mounted on interface module on electronic cabinets, and secondary power supply module is mounted on bottom cover.
Under operating mode, the supply voltage of extraneous power control system is converted into gyro by secondary power supply module after power-up
Voltage needed for instrument, signal processing and interface module and light source driving temperature control module, the angle that gyroscope will detect in real time
Speed signal is sent to signal processing and interface module, and light source driving temperature control module provides stable driving electricity for light source
Stream, and provide temperature monitoring and temperature control current, the angle that signal processing will be collected with interface module for light source tube core constant temperature
Speed signal is sent to extraneous attitude control subsystem after integrating.
The integration method is：Signal processing gathers angular velocity signal with interface module according to the fixed cycle,
Angular velocity signal is smooth according to the fixed cycle, and will treated that angular velocity signal is sent to that extraneous gesture stability point is
System.
Signal processing and interface circuit, the circuit are integrated with the discrete gyro circuit board of three axis in traditional sense, three axis signals
Processing and the dual function of interface card.
The connection of internal signal is completed using three axis customization flexible wires, connection path and trace arrangements are all solidificated in optical fiber
In gyroscopic inertia measuring device inner structural members.
Temperature control module is driven instead of traditional analog circuit board using one piece of integrated optical source, small, full electromagnetic shielding,
It can be directly connected to body heat loss through conduction.
Inferior grade component is targetedly selected, ensures that component disclosure satisfy that reliability will with reference to means such as screenings
It asks, achievees the purpose that reduce products-hardware cost.
The utility model is further discussed below below in conjunction with the accompanying drawings.
A kind of optical fiber gyro inertial measurement device, peripheral equipment include extraneous power control system and extraneous gesture stability point
System；
The device includes body 1, upper cover 2, three-axis integrative fibre optic gyroscope 3, light source driving temperature control module 4, electronic cabinets
5th, signal processing and interface module 6, secondary power supply module 7 and bottom cover 8；
The body 1 is a hollow cuboid；
The hollow cylinder that the upper cover 2 carries head cover for one, head cover are an integral molding structure with hollow cylinder；
3 inside of three-axis integrative fibre optic gyroscope carries light source；
The light source driving temperature control module 4 provides stable driving for the light source inside three-axis integrative fibre optic gyroscope 3
Electric current, and provide temperature monitoring and temperature control current for the constant temperature of light source tube core；
The hollow shell that the electronic cabinets 5 carry head cover for one, head cover are an integral molding structure with housing；
The angular velocity signal that the signal processing is used to receive according to the setting cycle with interface module 6 carries out
Extraneous attitude control subsystem is sent to after smooth；
The secondary power supply module 7 is used to the supply voltage of extraneous power control system being converted into three-axis integrative optical fiber
Gyroscope 3, light source driving temperature control module 4 and signal processing and the voltage needed for interface module 6；
Three gyroscopes in the three-axis integrative fibre optic gyroscope 3 are respectively gyroscope A, gyroscope B and gyroscope
C；Gyroscope A, gyroscope B are fixedly mounted on adjacent two side of body 1, and gyroscope C is fixedly mounted on the top of body 1
Face；
The light source driving temperature control module 4 is mounted on the side of body 1；
The signal processing is fixedly mounted on the inside of electronic cabinets 5 with interface module 6；
The secondary power supply module 7 is fixedly mounted on bottom cover 8 the upper surface of；
The bottom cover 8 is fixedly mounted on the bottom of electronic cabinets 5, i.e. signal processing and interface module 6 and secondary
Power module 7 is fixedly mounted in the space of 5 envelope of bottom cover 8 and electronic cabinets；
The bottom of the body 1 is fixedly mounted on the top of electronic cabinets 5；
The upper cover 2 is covered on body 1, i.e., light source driving temperature control module 4 and three-axis integrative fibre optic gyroscope 3 fix peace
In the space that upper cover 2 and body 1 are formed；
It is connected between the secondary power supply module 7 and light source driving temperature control module 4 by flexible wires, secondary power supply module
It is connected between 7 and signal processing and interface module 6 by flexible wires, secondary power supply module 7 and three-axis integrative optical fibre gyro
It is connected between instrument 3 by flexible wires, by soft between signal processing and interface module 6 and three-axis integrative fibre optic gyroscope 3
Property line connection, connected between three-axis integrative fibre optic gyroscope 3 and light source driving temperature control module 4 by flexible wires.
Under operating mode, the supply voltage of extraneous power control system is converted into gyro by secondary power supply module after power-up
Voltage needed for instrument, signal processing and interface module and light source driving temperature control module, the angle that gyroscope will detect in real time
Speed signal is sent to signal processing and interface module, and light source driving temperature control module provides stable driving electricity for light source
Stream, and provide temperature monitoring and temperature control current, the angle that signal processing will be collected with interface module for light source tube core constant temperature
Speed signal is sent to extraneous attitude control subsystem after integrating.
Above-mentioned integration method is：Signal processing gathers angular velocity signal with interface module according to the fixed cycle,
Angular velocity signal is smooth according to the fixed cycle, and will treated that angular velocity signal is sent to that extraneous gesture stability point is
System.
The connection of internal signal is completed using three axis customization flexible wires, connection path and trace arrangements are all solidificated in optical fiber
In gyroscopic inertia measuring device inner structural members.
Using one piece of light source driving temperature control module instead of traditional analog circuit board, small, full electromagnetic shielding, can be straight
Body heat loss through conduction is connect in succession.
Inferior grade component is targetedly selected, ensures that component disclosure satisfy that reliability will with reference to means such as screenings
It asks, achievees the purpose that reduce products-hardware cost.
Embodiment
(1) main assembly designs：Optical fiber gyro inertial measurement device, as shown in Figure 1, including on a body 1 and one
Cover 2；At 1 side of body and top there are three fibre optic gyroscope 3, light source driving temperature control module 4, electronic box are also equipped on body 1
The inside of body 5 is equipped with signal processing and interface module 6, and secondary power supply module 7 is mounted on lower lid, in electronic cabinets 5
The bottom of side have mounting hole, for being fixed on spacecraft structure body；
Busbar voltage is converted into the voltage that can be used inside the device by secondary power supply module 7, is respectively light source
Driving temperature control module 4, optical signal prosessing and interface module 6 are powered；
Signal processing receives 3 fibre optic gyroscope output informations with interface module 6, is sent after digital information is integrated
Give control subsystem；
2) electrical theory of constitution：The shape of above-mentioned 3 fibre optic gyroscopes is the iron-nickel alloy structure with 4 each mounting holes
Part, inside are fiber optic loop, and fiber optic loop uses the symmetrical winding method of level Four；Remaining optical device is mounted in electronic cabinets, including 3
A SLD light sources, 13 × 3 coupler and 32 × 2 couplers, 3 Y waveguides, 3 detectors；
Light source driving temperature control module provides stable driving current for light source, and provides temperature monitoring for light source tube core constant temperature
And temperature control current；
Signal processing uses the central information processing list using the FPGA of APA600-CQ208B as core with interface module
Member, the signal of reception optical fiber gyroscope output carry out data processing, and will treated data sending to controlling subsystem；It should
Circuit includes the units such as FPGA, A/D, D/A, level shifting circuit composition；This triaxial integration gyro circuit is than common gyro
Input interface circuit, input interface circuit receive spaceborne computer asynchronous serial communication data and ground inspection number all the way for circuit increase
According to programmable logic cells is transferred to be handled, are exported by output interface circuit.
3) inner flexible line designs：
The power cord that circuit uses no longer is banded together as conducting wire, crossover phenomenon occurs, is avoided between power supply
Interference, and the distance between power supply and ground wire only have 10mil, avoid coupled interference, particularly light source drive part point
Analog signal, driving and temperature control separate cabling；
The thickness of flexible wires only has 1/3rd of plain conductor diameter, and it is flexible portion to employ intermediate, and both ends are print
The mode of circuit board processed, only needs to reserve via in printed board, during assembling, it is only necessary to the printed board at both ends be fixed on light source,
On the contact pin of drive module, gyro circuit board and secondary power supply circuit board, convenient for welding, reduce empty caused by welding lead
Weldering and conducting wire take off head, ward off the unequal reason of tin caused by the risk that breaks, and using flexible cabling after, without again as making
It is the same with conducting wire, it is necessary to reserve threading hole on circuit boards, save space to circuit board, improve assembly reliability；
The direction of routing of flexible wires, length are devised according to actual conditions and it is identified, during assembling, due to
The direction of moving towards of flexible wires has been fixed, after the completion of one of flexible wires need to only being welded, according to the cabling side of flexible wires
To, flexible wires are fixed on structural member, then can other end welding completion；Due to flexible wires identify and not
The shape and length for the flexible wires that same position uses are different, cannot be exchanged between flexible cabling, are not in that welding mistake is made
The problem of being powered damage into component, reduces the appearance of the low level quality problems caused by welding mistake.
4) component cost control
The credit rating of most of component has carried out centainly on the basis of other CAST grades of space models in circuit
Degrade, capacitance resistance ware is in more than G+, and homemade chip is at B grades or more, and import device is at 883 grades or more.
The main chip that circuit uses：Programmable logic device fpga chip is the APA600-CQ208B of Actel companies,
The device is FLASH type FPGA, can carry out online programming, overprogram reduces the volume because anti-fuse FPGA is used to bring
The risk of journey failure；The B9240 and B9762 that A/D converter part and D/A converter part are produced by 772, two component are
B grades of products, but its internal chip and CAST grade are same, Flouride-resistani acid phesphatase accumulated dose can reach identical with CAST grades of products
100Krad (si).
The volume for effectively reducing optical fiber gyro inertial measurement device of the utility model simultaneously reduces production cost, can be with
Solve the problems, such as that traditional fiber gyroscopic inertia measuring device volume is big, of high cost.
The utility model unspecified part belongs to common sense well known to those skilled in the art.
Claims (5)
1. a kind of optical fiber gyro inertial measurement device, it is characterised in that：The device includes body (1), upper cover (2), three-axis integrative
It is fibre optic gyroscope (3), light source driving temperature control module (4), electronic cabinets (5), signal processing and interface module (6), secondary
Power module (7) and bottom cover (8)；
The light source driving temperature control module (4) provides stable driving for the internal light source of three-axis integrative fibre optic gyroscope (3)
Electric current, and provide temperature monitoring and temperature control current for the constant temperature of light source tube core；
The hollow shell that the electronic cabinets (5) carry head cover for one, head cover are an integral molding structure with housing；
The signal processing is used to put down the angular velocity signal received according to the setting cycle with interface module (6)
Extraneous attitude control subsystem is sent to after cunning；
The secondary power supply module (7) is used to the supply voltage of extraneous power control system being converted into three-axis integrative optical fiber top
Spiral shell instrument (3), light source driving temperature control module (4) and signal processing and the voltage needed for interface module (6)；
Two gyroscopes in the three-axis integrative fibre optic gyroscope (3) are fixedly mounted on adjacent two side of body (1)
Face, another gyroscope are fixedly mounted on the top surface of body (1)；
The light source driving temperature control module (4) is mounted on the side of body (1)；
The signal processing is fixedly mounted on the inside of electronic cabinets (5) with interface module (6)；
The secondary power supply module (7) is fixedly mounted on bottom cover (8) the upper surface of；
The bottom cover (8) is fixedly mounted on the bottom of electronic cabinets (5)；
The bottom of the body (1) is fixedly mounted on the top of electronic cabinets (5)；
The upper cover (2) is covered on body (1).
2. a kind of optical fiber gyro inertial measurement device according to claim 1, it is characterised in that：The body (1) is
One hollow cuboid.
3. a kind of optical fiber gyro inertial measurement device according to claim 1, it is characterised in that：The upper cover (2) is
One carries the hollow cylinder of head cover, and head cover is an integral molding structure with hollow cylinder.
4. a kind of optical fiber gyro inertial measurement device according to claim 1, it is characterised in that：The electronic cabinets
(5) hollow shell for carrying head cover for one, head cover are an integral molding structure with housing.
5. a kind of optical fiber gyro inertial measurement device according to claim 1, it is characterised in that：The secondary power supply mould
It is connected between block (7) and light source driving temperature control module (4) by flexible wires, secondary power supply module (7) and signal processing and interface
Circuit module is connected between (6) by flexible wires, is passed through between secondary power supply module (7) and three-axis integrative fibre optic gyroscope (3)
Flexible wires connect, and are connected between signal processing and interface module (6) and three-axis integrative fibre optic gyroscope (3) by flexible wires
It connects, is connected between three-axis integrative fibre optic gyroscope (3) and light source driving temperature control module (4) by flexible wires.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201721378235.XU CN207379509U (en) | 2017-10-24 | 2017-10-24 | A kind of miniaturization optical fiber gyro inertial measuring unit |
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| CN201721378235.XU CN207379509U (en) | 2017-10-24 | 2017-10-24 | A kind of miniaturization optical fiber gyro inertial measuring unit |
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| CN207379509U true CN207379509U (en) | 2018-05-18 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110823220A (en) * | 2019-11-07 | 2020-02-21 | 北京航天时代光电科技有限公司 | Triaxial integrated fiber optic gyroscope inertia measuring device |
| CN110823219A (en) * | 2019-11-07 | 2020-02-21 | 北京航天时代光电科技有限公司 | Microminiature low-cost triaxial integrated fiber optic gyroscope inertia measuring device |
| CN110849361A (en) * | 2019-11-28 | 2020-02-28 | 湖南率为控制科技有限公司 | Light and small integrated optical fiber inertial navigation system for unmanned driving |
| CN111121775A (en) * | 2019-11-26 | 2020-05-08 | 中国科学院微小卫星创新研究院 | Optical fiber gyroscope combination device for satellite attitude control |
| CN111964661A (en) * | 2020-06-30 | 2020-11-20 | 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 |
| CN112146651A (en) * | 2020-09-25 | 2020-12-29 | 上海航天控制技术研究所 | Micro-mechanical gyroscope assembly with small volume, low power consumption and high reliability |
| 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 |
| CN113447017A (en) * | 2021-06-28 | 2021-09-28 | 北京航天控制仪器研究所 | Ultra-small optical fiber inertia platform electromechanical dense all-in-one machine structure |
| CN113514047A (en) * | 2021-06-04 | 2021-10-19 | 北京航天时代光电科技有限公司 | Small-size light triaxial top combination for aerospace |
| CN113945226A (en) * | 2021-08-31 | 2022-01-18 | 北京航天时代光电科技有限公司 | High-precision double-light-source redundant triaxial integrated fiber optic gyroscope measuring device structure |
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2017
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110823220B (en) * | 2019-11-07 | 2021-04-13 | 北京航天时代光电科技有限公司 | Triaxial integrated fiber optic gyroscope inertia measuring device |
| CN110823219A (en) * | 2019-11-07 | 2020-02-21 | 北京航天时代光电科技有限公司 | Microminiature low-cost triaxial integrated fiber optic gyroscope inertia measuring device |
| CN110823220A (en) * | 2019-11-07 | 2020-02-21 | 北京航天时代光电科技有限公司 | Triaxial integrated fiber optic gyroscope inertia measuring device |
| CN110823219B (en) * | 2019-11-07 | 2021-06-11 | 北京航天时代光电科技有限公司 | Microminiature low-cost triaxial integrated fiber optic gyroscope inertia measuring device |
| CN111121775A (en) * | 2019-11-26 | 2020-05-08 | 中国科学院微小卫星创新研究院 | Optical fiber gyroscope combination device for satellite attitude control |
| CN110849361B (en) * | 2019-11-28 | 2022-02-15 | 湖南率为控制科技有限公司 | Light and small integrated optical fiber inertial navigation system for unmanned driving |
| CN110849361A (en) * | 2019-11-28 | 2020-02-28 | 湖南率为控制科技有限公司 | Light and small integrated optical fiber inertial navigation system for unmanned driving |
| CN111964661A (en) * | 2020-06-30 | 2020-11-20 | 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 |
| 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 |
| CN112146651A (en) * | 2020-09-25 | 2020-12-29 | 上海航天控制技术研究所 | Micro-mechanical gyroscope assembly with small volume, low power consumption and high reliability |
| 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 |
| CN113514047A (en) * | 2021-06-04 | 2021-10-19 | 北京航天时代光电科技有限公司 | Small-size light triaxial top combination for aerospace |
| CN113447017A (en) * | 2021-06-28 | 2021-09-28 | 北京航天控制仪器研究所 | Ultra-small optical fiber inertia platform electromechanical dense all-in-one machine structure |
| CN113447017B (en) * | 2021-06-28 | 2022-07-29 | 北京航天控制仪器研究所 | Super-small optical fiber inertia platform electromechanical dense-distribution all-in-one machine structure |
| CN113945226A (en) * | 2021-08-31 | 2022-01-18 | 北京航天时代光电科技有限公司 | High-precision double-light-source redundant triaxial integrated fiber optic gyroscope measuring device structure |
| CN113945226B (en) * | 2021-08-31 | 2024-05-31 | 北京航天时代光电科技有限公司 | High-precision double-light-source redundant triaxial integrated fiber-optic gyroscope measuring device |
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