CN111189470A - Backup instrument for canceling full static pressure pipeline - Google Patents
Backup instrument for canceling full static pressure pipeline Download PDFInfo
- Publication number
- CN111189470A CN111189470A CN201911117612.8A CN201911117612A CN111189470A CN 111189470 A CN111189470 A CN 111189470A CN 201911117612 A CN201911117612 A CN 201911117612A CN 111189470 A CN111189470 A CN 111189470A
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- Prior art keywords
- backup
- canceling
- instrument
- display
- heading
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- 230000003068 static effect Effects 0.000 title claims abstract description 14
- 238000001914 filtration Methods 0.000 claims abstract description 12
- 239000004973 liquid crystal related substance Substances 0.000 claims abstract description 11
- 238000005259 measurement Methods 0.000 claims abstract description 6
- 238000004146 energy storage Methods 0.000 claims abstract description 5
- 230000002706 hydrostatic effect Effects 0.000 claims description 9
- 238000006243 chemical reaction Methods 0.000 claims description 8
- 230000001133 acceleration Effects 0.000 claims description 6
- 239000000835 fiber Substances 0.000 claims description 3
- 239000000523 sample Substances 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 claims description 2
- 238000010438 heat treatment Methods 0.000 claims description 2
- 230000006698 induction Effects 0.000 claims description 2
- 239000010453 quartz Substances 0.000 claims description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 3
- 239000013307 optical fiber Substances 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Images
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C23/00—Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
Abstract
The invention belongs to the technical field of aviation, and relates to a backup instrument without a full static pressure pipeline. The instrument comprises a backup instrument display and a magnetic heading sensor; the magnetic heading sensor measures the magnetic heading and sends the data to the backup meter display. The backup instrument display comprises a liquid crystal display screen, a light guide plate, a navigation attitude resolving plate, a graphic interface board, an energy storage power supply board, a filtering connector and a navigation attitude measuring assembly, wherein the backup instrument display adopts an integrated design of a built-in navigation attitude measuring assembly. The invention solves the problem that the pipeline has the characteristic of hysteresis. The optical fiber gyroscope and the accelerometer which are higher in precision, lighter in weight and smaller in size are arranged in the display, so that the measurement precision is improved, the system weight is reduced and the man-machine effect is optimized compared with a separated backup instrument of an original flexible gyroscope.
Description
Technical Field
The invention belongs to the technical field of aviation, and relates to a backup instrument without a full static pressure pipeline.
Background
At present, backup instruments on large domestic aircrafts mainly adopt a separated structure, and a processor receives full pressure and static pressure provided by a full static pressure system so as to solve atmospheric parameters. At present, no integrated backup instrument for canceling a full static pressure pipeline is used on a large airplane in China. Because the total static pressure pipeline is a mechanical structure pipeline, the total static pressure pipeline has the characteristics of hysteresis, heavy weight, poor maintainability and the like.
Disclosure of Invention
Solves the technical problem
The invention provides an integrated backup instrument without a full static pressure pipeline.
Technical scheme
The invention is realized by the following technical scheme: a backup instrument for canceling a full static pressure pipeline comprises a backup instrument display and a magnetic heading sensor; the magnetic heading sensor measures the magnetic heading and sends the data to the backup meter display.
The backup instrument display comprises a liquid crystal display screen, a light guide plate, a navigation attitude resolving plate, a graphic interface board, an energy storage power supply board, a filtering connector and a navigation attitude measuring assembly, wherein the backup instrument display adopts an integrated design of a built-in navigation attitude measuring assembly.
On the premise of ensuring the precision, the navigation attitude measurement component selects a fiber optic gyroscope and an accelerometer which have proper precision, lighter weight and smaller volume to construct a miniaturized inertial instrument component, and the miniaturized inertial instrument component is arranged in a backup instrument display through an integrated design; the backup instrument display is crosslinked with the magnetic sensor, measures and outputs the instant course angle and the attitude angle of the carrier in real time, and converts the real-time course angle and the attitude angle into a horizon instrument picture through the graphic processing module to be displayed on the liquid crystal display; the backup instrument display can receive and display the parameter information of the intelligent probe at the same time. The overall design of the product has the characteristics of small volume, light weight and high measurement precision.
Advantageous technical effects
The invention provides a backup instrument design without a full static pressure pipeline, which reduces the weight of an airplane and solves the problem that the pipeline has the characteristic of hysteresis. The optical fiber gyroscope and the accelerometer which are higher in precision, lighter in weight and smaller in size are arranged in the display, so that the measurement precision is improved, the system weight is reduced and the man-machine effect is optimized compared with a separated backup instrument of an original flexible gyroscope.
Drawings
Fig. 1 is a functional block diagram of a backup meter display structure.
Detailed Description
The design of a backup instrument for canceling a full static pressure pipeline is explained in detail by combining the accompanying drawings:
a backup meter is provided that eliminates a fully hydrostatic circuit, consisting of 2 Line Replaceable Units (LRUs), each of which is described as follows:
1) backup instrument display
The backup instrument display mainly comprises a liquid crystal display screen, a light guide plate, a navigation attitude resolving plate, a graphic interface plate, an energy storage power supply plate, a filtering connector, a navigation attitude measuring component and the like.
The liquid crystal display is used for displaying flight parameter information and realizing man-machine conversation.
The graphics interface board has the function of a multi-channel bus data interface and receives parameters and data from equipment such as an intelligent probe and the like through an ARINC429 bus interface; and the attitude and heading reference system is crosslinked with an attitude and heading reference system through an RS422 serial interface. The graphic interface board has data and graphic processing functions, mainly completes data resolving and graphic processing driving, converts the data and graphic processing driving into displayed data and graphic instructions through resolving, and drives the liquid crystal display screen to display; meanwhile, the LED display panel has the functions of light guide plate key processing, liquid crystal screen heating control and the like.
The attitude heading resolving board mainly receives information sent by the graphic interface board, completes data processing and calculation of parameters such as heading and attitude, and sends working parameters to the graphic interface board.
In order to meet the requirements of voltage, power configuration and power quality of a product and ensure that the product can normally work in the sudden change process of an aircraft power supply, the energy storage power supply board is designed and selected with a power supply module which has a wide input voltage range and meets the power requirement, and input and output filtering processing is carried out to ensure that the product can normally work under the condition of aircraft power supply fluctuation.
The attitude and heading measurement component measures the angular velocity and the acceleration of the carrier in real time and converts the angular velocity and the acceleration into electric signals through an inertial instrument component which is composed of three closed-loop fiber optic gyroscopes which are installed in an orthogonal mode and three quartz accelerometers which are installed in an orthogonal mode.
The filter connector carries out anti-surge filtering processing on an input power supply, so that instantaneous high voltage is suppressed, input ripples are reduced, and anti-electromagnetic interference capability is improved; and meanwhile, all signals which are externally crosslinked with the backup instrument display are filtered, so that the signal interference is reduced, and the anti-electromagnetic interference capability is improved.
2) Magnetic heading sensor
The magnetic heading sensor is internally composed of 2 functional modules, a filtering conversion plate module and a sensor plate module. The filtering conversion board mainly has the functions of signal filtering, signal conversion, power supply conversion and the like, the sensor board is mainly provided with a magnetic compass which comprises a magnetic induction type sensor, an acceleration sensor, a temperature sensor and the like, and the tilt compensation technology is adopted to output information such as azimuth angles, pitch angles, roll angles, magnetic field components, internal temperature and the like.
Claims (9)
1. A spare instrument for canceling a full static pressure pipeline is characterized in that: the device comprises a backup instrument display and a magnetic heading sensor; the magnetic heading sensor is arranged in the backup instrument display to form an integrated design, measures the magnetic heading and sends the data to the backup instrument display.
2. The backup meter for canceling a full hydrostatic circuit of claim 1, wherein: the backup instrument display comprises a liquid crystal display screen, a light guide plate, a navigation attitude resolving plate, a graphic interface plate, a filtering connector and a navigation attitude measuring assembly.
3. The backup meter for canceling a full hydrostatic circuit of claim 2, wherein: and an energy storage power panel is also arranged in the backup instrument display.
4. The backup meter for canceling a full hydrostatic circuit of claim 2, wherein: the graphics interface board has the function of a multi-channel bus data interface and receives parameters and data from the intelligent probe through an ARINC429 bus interface; and the attitude and heading reference system is crosslinked with an attitude and heading reference system through an RS422 serial interface.
5. The backup meter of claim 4, eliminating a full hydrostatic circuit, wherein: the graphic interface board also has data and graphic processing functions, completes data resolving and graphic processing driving, converts the data and graphic processing driving into displayed data and graphic instructions through resolving, and drives the liquid crystal display screen to display; meanwhile, the device has the functions of light guide plate key processing and liquid crystal screen heating control.
6. The backup meter for canceling a full hydrostatic circuit of claim 2, wherein: the attitude heading resolving board mainly receives information sent by the graphic interface board, completes data processing and calculation of heading and attitude parameters, and sends working parameters to the graphic interface board.
7. The backup meter for canceling a full hydrostatic circuit of claim 2, wherein: the liquid crystal display is used for displaying flight parameter information and realizing man-machine conversation.
8. The backup meter for canceling a full hydrostatic circuit of claim 2, wherein: the attitude and heading measurement assembly is an inertial instrument assembly formed by three closed-loop fiber optic gyroscopes which are installed in an orthogonal mode and three quartz accelerometers which are installed in an orthogonal mode, and is used for measuring the motion angular rate and the motion acceleration of a carrier in real time and converting the motion angular rate and the motion acceleration into electric signals.
9. The backup meter for canceling a full hydrostatic circuit of claim 1, wherein: the magnetic heading sensor is internally composed of two functional modules, namely a filtering conversion plate module and a sensor plate module; the filtering conversion board module is used for signal filtering, signal conversion and power supply conversion, the sensor board module is provided with a magnetic compass, the magnetic compass is composed of a magnetic induction type sensor, an acceleration sensor and a temperature sensor, and an inclination compensation technology is adopted to output azimuth angle, pitch angle, roll angle, magnetic field component and internal temperature information.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911117612.8A CN111189470A (en) | 2019-11-15 | 2019-11-15 | Backup instrument for canceling full static pressure pipeline |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911117612.8A CN111189470A (en) | 2019-11-15 | 2019-11-15 | Backup instrument for canceling full static pressure pipeline |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111189470A true CN111189470A (en) | 2020-05-22 |
Family
ID=70707215
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911117612.8A Pending CN111189470A (en) | 2019-11-15 | 2019-11-15 | Backup instrument for canceling full static pressure pipeline |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111189470A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120303184A1 (en) * | 2010-11-23 | 2012-11-29 | Thales | Combined Stand-by Instrument and Method for Calibrating the Combined Stand-by Instrument |
| CN202783787U (en) * | 2012-04-13 | 2013-03-13 | 哈尔滨飞机工业集团有限责任公司 | Helicopter backup atmosphere navigational posture system |
| CN202915931U (en) * | 2012-08-20 | 2013-05-01 | 中航华东光电有限公司 | Display of airplane emergency electronic backup instrument |
| US20150015422A1 (en) * | 2013-07-12 | 2015-01-15 | Gulfstream Aerospace Corporation | Standby flight display system |
| CN205619938U (en) * | 2016-03-23 | 2016-10-05 | 深圳市南航电子工业有限公司 | Spare flight display and spare instrument of integration |
-
2019
- 2019-11-15 CN CN201911117612.8A patent/CN111189470A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120303184A1 (en) * | 2010-11-23 | 2012-11-29 | Thales | Combined Stand-by Instrument and Method for Calibrating the Combined Stand-by Instrument |
| CN202783787U (en) * | 2012-04-13 | 2013-03-13 | 哈尔滨飞机工业集团有限责任公司 | Helicopter backup atmosphere navigational posture system |
| CN202915931U (en) * | 2012-08-20 | 2013-05-01 | 中航华东光电有限公司 | Display of airplane emergency electronic backup instrument |
| US20150015422A1 (en) * | 2013-07-12 | 2015-01-15 | Gulfstream Aerospace Corporation | Standby flight display system |
| CN205619938U (en) * | 2016-03-23 | 2016-10-05 | 深圳市南航电子工业有限公司 | Spare flight display and spare instrument of integration |
Non-Patent Citations (2)
| Title |
|---|
| 余朝宇等: "基于ARM的备份导航系统控显仪设计", 《计算机测量与控制》, vol. 23, no. 8, 31 August 2015 (2015-08-31), pages 2904 - 2907 * |
| 黄俊钦: "创意之星 模块化机器人设计与竞赛 第2版", 北京航空航天大学出版社, pages: 207 * |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200522 |