CN202158858U - Navigation attitude system based on optical fiber gyro - Google Patents
Navigation attitude system based on optical fiber gyro Download PDFInfo
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- CN202158858U CN202158858U CN2010206414154U CN201020641415U CN202158858U CN 202158858 U CN202158858 U CN 202158858U CN 2010206414154 U CN2010206414154 U CN 2010206414154U CN 201020641415 U CN201020641415 U CN 201020641415U CN 202158858 U CN202158858 U CN 202158858U
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- measurement unit
- inertial measurement
- optical fibre
- computing machine
- fibre gyro
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Abstract
The utility model relates to a navigation attitude system, in particular to a navigation attitude system based on an optical gyro. The navigation attitude system comprises an inertia detection unit, a computer, a power supply and a global positioning system (GPS) receiving machine. The navigation attitude system is characterized in that the inertia detection unit is arranged at the bottom of the system and connected with a base. The computer, the power supply and the GPS receiving machine are arranged in multiple cavities. Compared with products of the same category, the navigation attitude system has the advantages of being compact in structure, small in volume, light, especially suitable for inertia technical fields with high requirements for volume, quality and cost and the like.
Description
Technical field
The utility model relates to a kind of boat appearance system, and particularly a kind of boat appearance system based on optical fibre gyro is particularly useful for the inertial technology field higher to volume, quality and cost requirement.
Background technology
Along with onboard navigation system only benefit of application demand in civil area increases, the onboard combined navigation technology is developed rapidly in recent years.Cost is low, precision has reliably become the basic demand of user to civilian onboard navigation system.Since the nineties in last century, optical fibre gyro constantly increases with the consumption in the strapdown attitude system at aircraft, and becomes the dominance inertia type instrument gradually.At present, external in/high-precision optical fiber gyro commercialization, in military-civil systems such as all kinds of aircrafts, naval vessel, sounding rocket, extensive application is arranged all.The research of internal optical fiber gyro is started in the eighties in last century, and in Tenth Five-Year Plan Period, under the drive and traction that model is used, China's optical fibre gyro through engineering approaches application technology has obtained fast development.The optical fiber boat appearance system, the combination boat appearance system that with the optical fibre gyro are sensitive element also succeed in developing gradually, and are applied, but the overall product that forms and few.Especially few for the research of miniaturization, low-cost system, incompatible for miniaturization, requirement cheaply.
Summary of the invention
The utility model technical matters to be solved provides a kind of miniaturization, cheaply based on the boat appearance system of optical fibre gyro.
For solving the problems of the technologies described above, the technical scheme of the utility model is:
A kind of boat appearance system based on optical fibre gyro; Comprise Inertial Measurement Unit, computing machine, power supply, GPS receiver, it is characterized in that said Inertial Measurement Unit is in the bottom of system; Link together with base, computing machine, power supply, GPS receiver are installed in the multi-cavity body.
Said Inertial Measurement Unit comprises the treatment circuit of triaxial integration optical fibre gyro and three quartz flexible accelerometers and accelerometer; Wherein accelerometer processing circuit is fixed on the body of three axis optical fibre gyro, and three axis optical fibre gyro and quartz flexible accelerometer are fixed on the base together.
Said multi-cavity body is divided into power source cavity, Inertial Measurement Unit chamber, computing machine chamber by support; Connect through the inside micro cable between three cavitys, computing machine is installed in the computing machine chamber, and the computing machine chamber is in the top of multi-cavity body; And be connected with GPS sheetpile stack; Power supply is installed in the power supply cavity, and Inertial Measurement Unit is installed in the Inertial Measurement Unit chamber, and power source cavity and Inertial Measurement Unit chamber are in the bottom of multi-cavity body.
The beneficial effect of the utility model is:Compare like product and have advantages such as compact conformation, volume are little, light weight.
Description of drawings
Further specify below in conjunction with accompanying drawing and embodiment technical scheme the utility model.
Fig. 1 is the system architecture layering synoptic diagram of the utility model.
Fig. 2 is the front view of the utility model inertial measurement cluster.
Fig. 3 is the utility model multi-cavity body structure figure.
Embodiment
As shown in Figure 1; A kind of boat appearance system based on optical fibre gyro comprises Inertial Measurement Unit 2, computing machine 5, power supply 6, GPS receiver 4, and Inertial Measurement Unit 2 is in the bottom of system; Link together with base 1, computing machine 5, power supply 6, GPS receiver 4 are installed in the multi-cavity body 3; As shown in Figure 2; Inertial Measurement Unit 2 comprises the treatment circuit 22 of triaxial integration optical fibre gyro 23 and three quartz flexible accelerometers 21 and accelerometer; Wherein accelerometer processing circuit 22 is fixed on the body of three axis optical fibre gyro 23, and three axis optical fibre gyro 23 is fixed on the base 1 with quartz flexible accelerometer 21 together; As shown in Figure 3, multi-cavity body 3 is divided between power source cavity 31, Inertial Measurement Unit chamber 32,33, three cavitys in computing machine chamber by support and connects through the inside micro cable; Computing machine 5 is installed in the computing machine chamber 33; Computing machine chamber 33 is in the top of multi-cavity body 3, and is connected with GPS receiver 4 sheetpile stacks, and power supply 6 is installed in the power supply cavity 31; Inertial Measurement Unit 2 is installed in the Inertial Measurement Unit chamber 32, and power source cavity 31 and Inertial Measurement Unit chamber 32 are in the bottom of multi-cavity body 3.
It should be noted last that; Above embodiment is only unrestricted in order to the technical scheme of explanation the utility model; Although with reference to preferred embodiment the utility model is specified, those of ordinary skill in the art should be appreciated that and can make amendment or be equal to replacement the technical scheme of the utility model; And not breaking away from the spirit and the scope of the utility model technical scheme, it all should be encompassed in the middle of the claim scope of the utility model.
Claims (3)
1. boat appearance system based on optical fibre gyro; Comprise Inertial Measurement Unit, computing machine, power supply, GPS receiver, it is characterized in that said Inertial Measurement Unit is in the bottom of system; Link together with base, computing machine, power supply, GPS receiver are installed in the multi-cavity body.
2. a kind of boat appearance system according to claim 1 based on optical fibre gyro; It is characterized in that; Said Inertial Measurement Unit comprises the treatment circuit of triaxial integration optical fibre gyro and three quartz flexible accelerometers and accelerometer; Wherein accelerometer processing circuit is fixed on the body of three axis optical fibre gyro, and three axis optical fibre gyro and quartz flexible accelerometer are fixed on the base together.
3. according to claim 1 or 2 said a kind of boat appearance systems based on optical fibre gyro; It is characterized in that said multi-cavity body is divided into power source cavity, Inertial Measurement Unit chamber, computing machine chamber by support, connect through the inside micro cable between three cavitys; Computing machine is installed in the computing machine chamber; The computing machine chamber is in the top of multi-cavity body, and is connected with GPS sheetpile stack, and power supply is installed in the power supply cavity; Inertial Measurement Unit is installed in the Inertial Measurement Unit chamber, and power source cavity and Inertial Measurement Unit chamber are in the bottom of multi-cavity body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206414154U CN202158858U (en) | 2010-12-04 | 2010-12-04 | Navigation attitude system based on optical fiber gyro |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206414154U CN202158858U (en) | 2010-12-04 | 2010-12-04 | Navigation attitude system based on optical fiber gyro |
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| Publication Number | Publication Date |
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| CN202158858U true CN202158858U (en) | 2012-03-07 |
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| CN2010206414154U Expired - Fee Related CN202158858U (en) | 2010-12-04 | 2010-12-04 | Navigation attitude system based on optical fiber gyro |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102735232A (en) * | 2012-06-26 | 2012-10-17 | 北京航天时代光电科技有限公司 | Apparatus for measuring inertia of fiber gyro composite unit and its calibration method |
| CN103604431A (en) * | 2013-11-21 | 2014-02-26 | 北京航空航天大学 | Strapdown compass system based on triaxial integrated high-precision optic fiber gyroscope |
| CN104713552A (en) * | 2013-12-11 | 2015-06-17 | 中国航空工业第六一八研究所 | Inertia sensitive assembly |
| CN106052682A (en) * | 2016-05-13 | 2016-10-26 | 北京航空航天大学 | Mixed inertial navigation system and navigation method |
| CN109533359A (en) * | 2018-12-20 | 2019-03-29 | 西安飞机工业（集团）有限责任公司 | A kind of optical fiber navigation attitude instrument system using electromechanical data indicating equipment |
| CN113624229A (en) * | 2021-08-27 | 2021-11-09 | 陕西华燕航空仪表有限公司 | Optical fiber attitude and heading reference unit and testing tool |
-
2010
- 2010-12-04 CN CN2010206414154U patent/CN202158858U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102735232A (en) * | 2012-06-26 | 2012-10-17 | 北京航天时代光电科技有限公司 | Apparatus for measuring inertia of fiber gyro composite unit and its calibration method |
| CN102735232B (en) * | 2012-06-26 | 2015-02-11 | 北京航天时代光电科技有限公司 | Apparatus for measuring inertia of fiber gyro composite unit and its calibration method |
| CN103604431A (en) * | 2013-11-21 | 2014-02-26 | 北京航空航天大学 | Strapdown compass system based on triaxial integrated high-precision optic fiber gyroscope |
| CN104713552A (en) * | 2013-12-11 | 2015-06-17 | 中国航空工业第六一八研究所 | Inertia sensitive assembly |
| CN106052682A (en) * | 2016-05-13 | 2016-10-26 | 北京航空航天大学 | Mixed inertial navigation system and navigation method |
| CN106052682B (en) * | 2016-05-13 | 2018-12-11 | 北京航空航天大学 | A kind of hybrid inertial navigation system and air navigation aid |
| CN109533359A (en) * | 2018-12-20 | 2019-03-29 | 西安飞机工业（集团）有限责任公司 | A kind of optical fiber navigation attitude instrument system using electromechanical data indicating equipment |
| CN113624229A (en) * | 2021-08-27 | 2021-11-09 | 陕西华燕航空仪表有限公司 | Optical fiber attitude and heading reference unit and testing tool |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee |
Owner name: HUBEI SANJIANG AEROSPACE HONGFENG CONTROL CO., LTD Free format text: FORMER NAME: STATE HONGFENG MACHINERY FACTORY |
|
| CP01 | Change in the name or title of a patent holder |
Address after: 432000 Hubei city of Xiaogan province Beijing Road No. 8 gate Patentee after: Hubei Sanjiang Aerospace Hongfeng Control Co., Ltd. Address before: 432000 Hubei city of Xiaogan province Beijing Road No. 8 gate Patentee before: State Hongfeng Machinery Factory |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120307 Termination date: 20141204 |
|
| EXPY | Termination of patent right or utility model |