CN109533359A - A kind of optical fiber navigation attitude instrument system using electromechanical data indicating equipment - Google Patents
A kind of optical fiber navigation attitude instrument system using electromechanical data indicating equipment Download PDFInfo
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- CN109533359A CN109533359A CN201811566484.0A CN201811566484A CN109533359A CN 109533359 A CN109533359 A CN 109533359A CN 201811566484 A CN201811566484 A CN 201811566484A CN 109533359 A CN109533359 A CN 109533359A
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- 239000013307 optical fiber Substances 0.000 title claims abstract description 21
- 239000000835 fiber Substances 0.000 claims abstract description 33
- 230000001360 synchronised effect Effects 0.000 claims abstract description 33
- 230000003321 amplification Effects 0.000 claims abstract description 6
- 238000003199 nucleic acid amplification method Methods 0.000 claims abstract description 6
- 230000005284 excitation Effects 0.000 claims description 15
- 238000006243 chemical reaction Methods 0.000 claims description 10
- 230000010354 integration Effects 0.000 description 13
- 238000013461 design Methods 0.000 description 9
- 238000000034 method Methods 0.000 description 4
- 230000006978 adaptation Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000012857 repacking Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005662 electromechanics Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002085 persistent effect Effects 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 230000011664 signaling Effects 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
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- General Physics & Mathematics (AREA)
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Abstract
A kind of optical fiber navigation attitude instrument system using electromechanical data indicating equipment, contain magnetic course transmitter, optic fiber gyroscope component, electromechanical data shows equipment and relay box, the magnetic course transmitter is connect with optic fiber gyroscope component by RS422 data/address bus, optic fiber gyroscope component exports the course attitude data after resolving to box adapter by RS422 data/address bus, the RS422 data bus signal that optic fiber gyroscope component inputs is converted to three-phase synchronous device signal and carries out servo amplification by the box adapter, three-phase synchronous device signal is exported by relay box to electromechanical data again and shows that equipment is read for pilot.
Description
Technical field
It is specifically a kind of optic fiber gyroscope component and electromechanical data instruction to be set the invention belongs to instrument technical field
Standby matching used optical fiber navigation attitude instrument system.
Background technique
Navigation attitude instrument system generally consists of three parts: magnetic course transmitter, gyrounit, data indicating equipment.Flying
Machine in-flight, the course of gyrounit survey aircraft and attitude data, and receive magnetic course transmitter measurement magnetic heading number
It after carrying out processing resolving, then is transmitted to data indicating equipment and is read for pilot, the other systems being also transmitted on aircraft make
With and record.Navigation attitude instrument system is one of system mostly important in aircraft, and pilot generally requires the number by the system
The important informations such as course, roll, the pitching of aircraft are understood according to indicating equipment.So no matter military aircraft or civil aircraft,
Generally two sets or more of navigation attitude instrument system is equipped with to ensure the safety navigated by water.It can be said that just whether navigation attitude instrument system
Really installation, if it is safe and reliable, directly determine that can aircraft normal flight.
In the navigation attitude instrument system design production of aircraft, all kinds of navigation attitude instrument are generally distinguished with the title of gyrounit
System, such as using the optical fiber navigation attitude instrument system of optic fiber gyroscope component, navigation attitude instrument system is floated using the liquid of liquid floated gyroscope component
System, uses the full attitude integration gyro navigation attitude instrument system etc. of full attitude integration gyrounit.
In view of the importance of navigation attitude instrument system, development is attached great importance to, for a period of time, navigation attitude instrument system hair
Exhibition rapidly, is largely weeded out the old and bring forth the new, update is exceedingly fast.However still has much be produced in the complete of the seventies in boat aircraft utilization at present
Attitude integration gyro navigation attitude instrument system, this aviation attitude system is by full attitude integration gyrounit, magnetic course transmitter, relay
Box, electromechanical data indicating equipment are formed with corresponding connecting cable, and this system has that weight is big, pointing accuracy is low, failure rate
The shortcomings such as high, safety and maintainability difference, and full attitude integration gyrounit of these disadvantages in system,
This navigation attitude instrument system is caused seriously to fall behind the times demand.
Optical fiber navigation attitude instrument system includes magnetic course transmitter, optic fiber gyroscope component, relay box, electronic flight instrument
Table (EFIS) and corresponding connecting cable composition, this navigation attitude instrument system have weight due to having used optic fiber gyroscope component
Gently, the advantages that failure rate is low, small power consumption, and pointing accuracy is high, and safety and reliability is high is replaced in design production rapidly
Full attitude integration gyro navigation attitude instrument system, obtained main airplane factory with using the consistent favorable comment of user.Therefore, very
Multi-user wishes the persistent ailment that puzzlement many years are solved not yet optical fiber navigation attitude instrument system is also replaced to the aircraft in longevity.
However, optical fiber navigation attitude instrument system can not the full attitude integration of simple replacement on the aircraft for having delivered user
Gyroscope instrument system, what this was primarily due to the output of the optic fiber gyroscope component in optical fiber navigation attitude instrument system is digital signal,
So being also required to receive the electronic flight instrument (EFIS) of corresponding standard to indicate that this data is read for pilot.Institute
With it is infeasible that full attitude integration gyrounit, which is only upgraded to optic fiber gyroscope component,.In the prior art, to upgrading navigation attitude system
The way of system is: or need systematic complete upgrading or a can export of additional designs is needed to indicate with electromechanical
The matched optic fiber gyroscope component of device signal standard.But systematicness comprehensively replaces old navigation attitude instrument system can involve it again
The airborne system that he is crosslinked, and since indicating equipment occupies most number space of cockpit instrument board, to indicating equipment
Update is also required to that cockpit is integrally redesigned and tested, and the complete upgrading of this aviation attitude system is regenerated, and at high cost, the period is long,
It is less economical, it is unable to satisfy the requirement of user.And the optic fiber gyroscope component of design specialized is also required in design to matured product
Additional modifications are carried out, and amount of purchase is small causes cost high.The above various reasons cause navigating on aircraft to navigation attitude
Instrument system carries out upgrading and updates price height, and time-consuming, has greatly hit the wish that customer upgrade updates the system.
So only upgrade gyrounit if old electromechanical data indicating equipment can be continued to employ, it both can be effective
Repacking cost is reduced, and the repacking time can be largely reduced, changes the outfit the wish of new-type instrument, is promoted to be obviously improved user
The safety of entire escadrille.And how to realize that the conversion of the intercommunication between two kinds of signaling modes is exactly the key for realizing this point
Technology.
Summary of the invention
The purpose of the present invention is to provide a kind of new optical fiber navigation attitude instrument system using electromechanical data indicating equipment,
It, will be received from optic fiber gyroscope component by increasing the box adapter of installation between optic fiber gyroscope component and relay box
RS422 data bus signal is converted into three-phase synchronous device signal and servo amplification, then three-phase synchronous device signal is exported to electromechanics
Formula data indicating equipment, so that electromechanical data indicating equipment can show correct numerical value.
A kind of optical fiber navigation attitude instrument system using electromechanical data indicating equipment, contains magnetic course transmitter, optical fiber top
Spiral shell component, electromechanical data show equipment and relay box, which is characterized in that the magnetic is navigated by RS422 data/address bus
It is connect to sensor with optic fiber gyroscope component, optic fiber gyroscope component is total by RS422 data by the course attitude data after resolving
Line is exported to box adapter, and it is identical which by the RS422 data bus signal that optic fiber gyroscope component inputs is converted to three
Step device signal simultaneously carries out servo amplification, then three-phase synchronous device signal is exported by relay box to electromechanical data and shows equipment
It is read for pilot.
In the application the working principle of increased box adapter be, when box adapter works, by optic fiber gyroscope component with
The course angle of RS422 number bus output, roll angle, pitching angle signal pass through the number in box adapter/synchronizer transformation mould
Block is converted to three-phase synchronous device signal and carries out servo amplification, later again by relay box by three-phase synchronous device signal export to
Electromechanical data instruction and other equipment on machine.
The beneficial effects of the present invention are: by increasing box adapter, by RS422 data bus signal to convert three identical
Device signal is walked, this just makes it possible to upgrade in the navigation attitude instrument system of the aged aircraft of boat now, only need to be with advanced
Optic fiber gyroscope component substitutes the old-fashioned full attitude integration gyrounit using analog signal, then by newly-increased box adapter into
Row signal conversion, so that it may realize the Signal Matching between new-type optic fiber gyroscope component and old-fashioned electromechanical data indicating equipment, largely
Reduce aged aircraft and have to the number of devices of replacement and the redesign of system when updating navigation attitude instrument system, greatly subtracts
The content of the required redesign in the work is lacked, thus goods and materials cost needed for being significantly reduced update navigation attitude instrument system
And time cost.The method reasonable that this programme proposes has been subjected to actual product verifying.
Attached drawing is described in further detail the application with reference to embodiments:
Detailed description of the invention
Fig. 1 is the functional block diagram of the optical fiber navigation attitude instrument system using electromechanical data indicating equipment of the application.
Specific embodiment
As shown, the optical fiber navigation attitude instrument system using electromechanical data indicating equipment of the application, contains magnetic heading
Sensor, optic fiber gyroscope component, electromechanical data indicating equipment and relay box, by RS422 data/address bus by the magnetic
Course transmitter is connect with optic fiber gyroscope component, and the course attitude data after resolving is passed through RS422 data by optic fiber gyroscope component
Bus is exported to a box adapter, which is converted to the RS422 data bus signal that optic fiber gyroscope component inputs
Three-phase synchronous device signal simultaneously carries out servo amplification, then three-phase synchronous device signal is exported by relay box to electromechanical data and is referred to
Show equipment.The box adapter can also pass through relay box with other airborne equipments with three-phase synchronous device interconnection of signals simultaneously.
In implementation, required to meet the whole of optical fiber navigation attitude instrument system in the application, institute is increased in the application flies
The above-mentioned box adapter of machine navigation attitude instrument system must meet the following requirement:
Number/synchronizer conversion module is equipped in the box adapter, can by received mark navigation attitude data (containing course angle,
Pitch angle, roll angle) RS422 data bus signal be converted into three-phase synchronous device signal and export.
The reserved physical interface that can be mounted on airframe of the box adapter and on relay box and other machines
The electric interfaces of equipment connection.
Box adapter at least has following electric interfaces in implementation:
1) course angle that 2 tunnels are transmitted using RS422 data bus signal, pitch angle, roll angle information can at least be received.
2) 2 tunnels can be at least sent out and use 57V signal voltage, the three-phase synchronous device signal of 36V excitation voltage, to pass
Defeated pitch angle information, signal conversion accuracy must not be lower than ± 0.3 °.
3) 2 tunnels can be at least sent out and use 57V signal voltage, the three-phase synchronous device signal of 36V excitation voltage, to pass
Defeated roll angle information, signal conversion accuracy must not be lower than ± 0.3 °.
4) 2 tunnels can be at least sent out and use 16V signal voltage, the three-phase synchronous device signal of 36V excitation voltage, to pass
Defeated course angle information, signal conversion accuracy must not be lower than ± 0.3 °.
5) 1 tunnel can be at least sent out using 11.8V signal voltage, the three-phase synchronous device signal of 26V excitation voltage, to
Pitch angle information is transmitted, signal conversion accuracy must not be lower than ± 0.3 °.
6) 1 tunnel can be at least sent out using 11.8V signal voltage, the three-phase synchronous device signal of 26V excitation voltage, to
Roll angle information is transmitted, signal conversion accuracy must not be lower than ± 0.3 °.
In addition, the box adapter is suitable with other airborne equipments on aircraft, and it must satisfy country to air equipment
It is general to require, it is detailed in national military standard relevant criterion or airworthiness management relevant provision.
When aircraft flight, the optical fiber navigation attitude instrument system of the application enters work shape on machine under the support of power supply system
State, the course of optic fiber gyroscope component survey aircraft and attitude data, and receive magnetic course transmitter measurement magnetic heading data into
After row processing resolves, corresponding course angle, pitch angle, roll angle are obtained, then pass through RS422 data bus transmission to adapter
Box.RS422 data bus signal is converted three-phase synchronous device signal by box adapter, is sent to relay box, passes through relay
Box is distributed to electromechanical data indicating equipment and other airborne equipments, reads and uses for pilot.
The new design that the application includes increases the box adapter after optic fiber gyroscope component, is increased by box adapter
The process for having added a signal transformation of ownership, allowing realizes number using between the gyrounit and data display equipment of different data standard
According to exchange, electromechanical data indicating equipment is used, workload needed for reducing more exchange device reduces design cost and life
Produce cost.
The application is described in detail by the example of aviation attitude system is upgraded with aircraft below.
The original full attitude integration gyro aviation attitude system of aircraft is by magnetic course transmitter, full attitude integration gyro group
Part, electromechanical indicating equipment, relay box, several three-phase synchronous device signal-transmitting cable compositions.
Because of variety of problems existing for the set system, decision upgrades to new-type optical fiber navigation attitude to it.In an implementation, it is in
The considerations of redesigning required time is controlled upgrade cost and shortened, determines to use design method described herein, stay
With electromechanical indicating equipment original on aircraft.
Aviation attitude system after upgrading includes magnetic course transmitter, optic fiber gyroscope component, electromechanical data indicating equipment, adaptation
Device box, relay box, several RS422 bus standard signal transmission cables, several three-phase synchronous device signal-transmitting cables.Magnetic heading
It is directly crosslinked between sensor and optic fiber gyroscope component using RS422 bus standard signal, and optic fiber gyroscope component passes through adaptation
Device box is crosslinked indirectly with relay box, first exports RS422 bus standard signal to box adapter, then by fitting by optic fiber gyroscope component
Each road signal is distributed to guarantor by relay box to relay box by output three-phase synchronous device signal after orchestration box carries out data conversion
The electromechanical data indicating equipment stayed shows information needed, reads for pilot.
Evaluated test, the design work is good, and performance indexes meets or exceeds requirement.It navigates with general optical fiber
Appearance instrument system is compared, and this system only slightly reduces in the index of pointing accuracy, and the indexs such as weight, reliability, safety
It is substantially suitable, and production cost declines to a great extent with replacement cost；With general full attitude integration gyro navigation attitude instrument system
System is compared, and over-all properties is substantially improved, and due to continuing to employ existing equipment on the machine of part, significantly reduces upgrade cost,
It can be commonly used to carry out upgrading to the aircraft using full attitude integration gyro aviation attitude system in boat.
Claims (3)
1. a kind of optical fiber navigation attitude instrument system using electromechanical data indicating equipment, contains magnetic course transmitter, optical fibre gyro
Component, electromechanical data show equipment and relay box, which is characterized in that by RS422 data/address bus by the magnetic heading
Sensor is connect with optic fiber gyroscope component, and the course attitude data after resolving is passed through RS422 data/address bus by optic fiber gyroscope component
It exports to box adapter, which is converted to three-phase synchronous for the RS422 data bus signal that optic fiber gyroscope component inputs
Device signal simultaneously carries out servo amplification, then three-phase synchronous device signal is exported by relay box to electromechanical data and shows that equipment supplies
Pilot reads.
2. using the optical fiber navigation attitude instrument system of electromechanical data indicating equipment as described in claim 1, which is characterized in that institute
The box adapter stated has following electric interfaces:
1) course angle transmitted using RS422 data bus signal on 2 tunnels, pitch angle, roll angle information can at least be received；
2) 2 tunnels can be at least sent out using 57V signal voltage, the three-phase synchronous device signal of 36V excitation voltage is bowed to transmit
Elevation information；
3) 2 tunnels can be at least sent out and use 57V signal voltage, the three-phase synchronous device signal of 36V excitation voltage, to transmit cross
Roll angle information；
4) 2 tunnels can be at least sent out and use 16V signal voltage, the three-phase synchronous device signal of 36V excitation voltage, to transmit boat
To angle information；
5) it can at least be sent out 1 tunnel and use 11.8V signal voltage, the three-phase synchronous device signal of 26V excitation voltage, to transmit
Pitch angle information；
6) it can at least be sent out 1 tunnel and use 11.8V signal voltage, the three-phase synchronous device signal of 26V excitation voltage, to transmit
Roll angle information.
3. a kind of box adapter of aircraft navigation attitude instrument system, which is characterized in that be equipped with number/synchronizer in the box adapter
The RS422 data bus signal of received mark navigation attitude data can be converted and be exported as three-phase synchronous device signal by conversion module,
Box adapter has following electric interfaces:
1) course angle transmitted using RS422 data/address bus on 2 tunnels, pitch angle, roll angle information can at least be received；
2) 2 tunnels can be at least sent out using 57V signal voltage, the three-phase synchronous device signal of 36V excitation voltage is bowed to transmit
Elevation information；
3) 2 tunnels can be at least sent out and use 57V signal voltage, the three-phase synchronous device signal of 36V excitation voltage, to transmit cross
Roll angle information；
4) 2 tunnels can be at least sent out and use 16V signal voltage, the three-phase synchronous device signal of 36V excitation voltage, to transmit boat
To angle information；
5) it can at least be sent out 1 tunnel and use 11.8V signal voltage, the three-phase synchronous device signal of 26V excitation voltage, to transmit
Pitch angle information；
6) it can at least be sent out 1 tunnel and use 11.8V signal voltage, the three-phase synchronous device signal of 26V excitation voltage, to transmit
Roll angle information.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811566484.0A CN109533359A (en) | 2018-12-20 | 2018-12-20 | A kind of optical fiber navigation attitude instrument system using electromechanical data indicating equipment |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811566484.0A CN109533359A (en) | 2018-12-20 | 2018-12-20 | A kind of optical fiber navigation attitude instrument system using electromechanical data indicating equipment |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111274185A (en) * | 2020-01-10 | 2020-06-12 | 中国地质科学院地质研究所 | Method and system for solving communication interface data compatibility in instrument old part replacement |
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102135430A (en) * | 2010-01-25 | 2011-07-27 | 北京三驰科技发展有限公司 | Strapdown attitude and heading reference system (AHRS) based on fiber optic gyro (FOG) |
| CN202158858U (en) * | 2010-12-04 | 2012-03-07 | 国营红峰机械厂 | Navigation attitude system based on optical fiber gyro |
| CN105371837A (en) * | 2015-12-25 | 2016-03-02 | 重庆华渝电气集团有限公司 | Sync-output system and sync-output method for triaxial fiber optic gyros |
| CN108657450A (en) * | 2018-05-07 | 2018-10-16 | 上海海鹰机械厂 | Aircraft optical fiber aviation attitude system method of modifying |
-
2018
- 2018-12-20 CN CN201811566484.0A patent/CN109533359A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102135430A (en) * | 2010-01-25 | 2011-07-27 | 北京三驰科技发展有限公司 | Strapdown attitude and heading reference system (AHRS) based on fiber optic gyro (FOG) |
| CN202158858U (en) * | 2010-12-04 | 2012-03-07 | 国营红峰机械厂 | Navigation attitude system based on optical fiber gyro |
| CN105371837A (en) * | 2015-12-25 | 2016-03-02 | 重庆华渝电气集团有限公司 | Sync-output system and sync-output method for triaxial fiber optic gyros |
| CN108657450A (en) * | 2018-05-07 | 2018-10-16 | 上海海鹰机械厂 | Aircraft optical fiber aviation attitude system method of modifying |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111274185A (en) * | 2020-01-10 | 2020-06-12 | 中国地质科学院地质研究所 | Method and system for solving communication interface data compatibility in instrument old part replacement |
| 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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Application publication date: 20190329 |