CN108092751A - Pneumatic gauging parameter information processing method - Google Patents
Pneumatic gauging parameter information processing method Download PDFInfo
- Publication number
- CN108092751A CN108092751A CN201611048794.4A CN201611048794A CN108092751A CN 108092751 A CN108092751 A CN 108092751A CN 201611048794 A CN201611048794 A CN 201611048794A CN 108092751 A CN108092751 A CN 108092751A
- Authority
- CN
- China
- Prior art keywords
- data
- capturing service
- processing method
- information processing
- parameter information
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L1/00—Arrangements for detecting or preventing errors in the information received
- H04L1/22—Arrangements for detecting or preventing errors in the information received using redundant apparatus to increase reliability
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F13/00—Interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units
- G06F13/38—Information transfer, e.g. on bus
- G06F13/42—Bus transfer protocol, e.g. handshake; Synchronisation
- G06F13/4282—Bus transfer protocol, e.g. handshake; Synchronisation on a serial bus, e.g. I2C bus, SPI bus
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L5/00—Arrangements affording multiple use of the transmission path
- H04L5/14—Two-way operation using the same type of signal, i.e. duplex
- H04L5/16—Half-duplex systems; Simplex/duplex switching; Transmission of break signals non-automatically inverting the direction of transmission
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/50—Reducing energy consumption in communication networks in wire-line communication networks, e.g. low power modes or reduced link rate
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Signal Processing (AREA)
- General Physics & Mathematics (AREA)
- Computer Networks & Wireless Communication (AREA)
- Theoretical Computer Science (AREA)
- Fluid Mechanics (AREA)
- General Engineering & Computer Science (AREA)
- Mobile Radio Communication Systems (AREA)
Abstract
The present invention provides a kind of pneumatic gauging parameter information processing method, for rudders pneumatic power parameter acquisition, transimission and storage.Pneumatic gauging parameter information processing method comprises the following steps：The data exported respectively to pneumatic pressure transmitter, gyro, accelerometer and navigation neceiver by 2 capturing service units in aircraft platforms information system are acquired, and 2 capturing service units mutually form backup；The data gathered using aircraft platforms day earth communication system to 2 capturing service units are transmitted；The data of 2 capturing service unit acquisitions are stored respectively using 2 black boxes.The method of the present invention has good redundancy properties, can improve the reliability of aerodynamic parameter measurement, reduces system resources consumption.
Description
Technical field
The present invention relates to rudders pneumatic power parameter metrical information System design technologies, and in particular to a kind of pneumatic gauging parameter
Information processing method belongs to flight vehicle aerodynamic field of measuring technique.
Background technology
The aerodynamic parameter of aircraft mainly includes the critical data of flow angle, dynamic pressure and aerodynamic force tripartite face.Such as fight
Aerospace flight vehicles such as machine, spaceship return capsule etc. are required for measuring aerodynamic parameter.During high-speed flight
Complete the acquisition of aerodynamic parameter, transimission and storage is that aerodynamic parameter metrical information system is successfully crucial.
Conventional metrical information system and aircraft platforms information system is relatively independent, and redundant configuration has to be strengthened so that
Platform resource is consumed conventional method and hardware reliability is more demanding.In conventional scheme, due to lacking redundant configuration, when certain
When a hardware breaks down, entire measurement scheme can be caused to fail.
The content of the invention
The object of the present invention is to provide a kind of pneumatic gauging parameter information processing method, for rudders pneumatic power parameter
Acquisition, transimission and storage.This method has good redundancy properties, improves the reliability of aerodynamic parameter measurement, reduces system money
Source consumes.
The technical solution used in the present invention is as follows：
A kind of pneumatic gauging parameter information processing method, for rudders pneumatic power parameter acquisition, transimission and storage, bag
Include following steps：By 2 capturing service units in aircraft platforms information system respectively to pneumatic pressure transmitter, top
The data of spiral shell, accelerometer and navigation neceiver output are acquired, and 2 capturing service units mutually form backup；Profit
The data gathered with aircraft platforms day earth communication system to 2 capturing service units are transmitted；It is black using 2
Case respectively stores the data of 2 capturing service unit acquisitions.
For above-mentioned pneumatic gauging parameter information processing method, the pneumatic pressure transmitter externally exports double using two point
Line designs, and every group of signal wire and loop line are connected with a capturing service unit；Pneumatic pressure transmitter data acquisition interface
It is both-end analog channel interface, using double level differential modes, a both-end analog channel is made of two input lines, and one is
Simulation signal generator low side is known as loop line, and one high-end for simulation signal generator, is known as signal wire, the high and low end of simulation signal generator
Compared with collection terminal analog references all float, and be connected to simultaneously in the specialized simulation input line of the collection terminal.
For above-mentioned pneumatic gauging parameter information processing method, every gyro, the accelerometer and the navigation
Receiver externally exports two-way measurement data, and measurement data described in per road is connected with a capturing service unit；The top
Communication between spiral shell, the accelerometer and the navigation neceiver and the capturing service unit uses asynchronous serial half-duplex
Mode, using RS-422 electric interfaces standards, baud rate 500kbps.
For above-mentioned pneumatic gauging parameter information processing method, the gyro, the accelerometer and the navigation receive
The communication information between machine and the capturing service unit represents that described information is transmitted by byte, low byte using complement form
Preceding, high byte is rear, and each byte is formed by 12,1 start bit, 8 data bit, 1 odd parity bit, 2 stop positions.
For above-mentioned pneumatic gauging parameter information processing method, every capturing service unit provides a set of RS-422 electricity
Gas interface, the RS-422 electric interfaces sequential of 2 capturing service units is identical, by sampling clock, sample command and
Data form.
As the improvement of the above-mentioned pneumatic gauging parameter information processing method of the present invention, in the data transmission step, 2 institutes
It states capturing service unit and is directly mounted on platform 1553B buses, will respectively be sent after the data framing of acquisition in being mounted on
After stating the engineering telemetry communication unit of platform 1553B buses and relaying comprehensive unit, then encoded, modulation treatment, respectively through USB
Answering machine channeling and trunking channel downstream is to ground, for follow-up data processing.
For above-mentioned pneumatic gauging parameter information processing method, the capturing service unit will be gathered using 40ms as the cycle
The data framing is the bus communication data packet of mono- frames of 160ms, is sent comprehensive in the engineering telemetry communication unit and the relaying
Close unit.
As the improvement of the above-mentioned pneumatic gauging parameter information processing method of the present invention, 2 capturing service units are external
The data of output are identical, and data described in 2 groups are by the way of parity frame multiplexing, alternating downlink.
As the improvement of the above-mentioned pneumatic gauging parameter information processing method of the present invention, 2 black boxes are articulated in flat
In platform 1553B buses, the storage of the data is completed using periodical communication.
The beneficial effects of the invention are as follows：For the present invention by carrying out hardware redundancy configuration, improve aerodynamic parameter measurement can
By property, in addition, the present invention is designed with platform information system globe area, system resources consumption is reduced.
Description of the drawings
Fig. 1 is aerodynamic parameter metrical information process chart.
Specific embodiment
Detailed description of the present invention specific embodiment below in conjunction with the accompanying drawings.
Fig. 1 is aerodynamic parameter metrical information process chart.As shown in Figure 1, in pneumatic gauging parameter information processing method
In, data acquisition, data transmission and data storage are carried out respectively, are as follows：
Step 1：By 2 capturing service units in aircraft platforms information system respectively to pneumatic pressure transmitter,
The data of gyro, accelerometer and navigation neceiver output are acquired, and 2 capturing service units mutually form backup.
Data collection task is completed by 2 capturing service units in aircraft platforms information system, 2 capturing services
Unit mutually forms backup, realizes hardware redundancy, adapts to the interface requirement of different aerodynamic parameter measuring apparatus.
Conventional pressure sensor externally exports 1 tunnel 1:1 loop line analog acquisition interface, in order to improve system reliability, this
Pneumatic pressure transmitter is externally exported in invention is set using two point two-wire (i.e. docking point and cable system carry out duplication redundancy backup)
Meter, every group of signal wire and loop line are connected with a capturing service unit, mutually form backup, realize hardware redundancy.
Pneumatic pressure transmitter data acquisition interface is both-end analog channel interface, using double level differential modes, one
Both-end analog channel is made of two input lines, and one is simulation signal generator low side, is known as loop line；It is one high for simulation signal generator
End is known as signal wire.The high and low end of simulation signal generator compared with collection terminal analog references all float, and connect simultaneously
It is connected in the specialized simulation input line of collection terminal.The requirement of pneumatic pressure transmitter data acquisition interface circuit is as follows：
A) the high-end and low side of pneumatic pressure transmitter data acquisition interface should be at same state in synchronization, that is, lead
Switch is simultaneously in closure state when logical, and switch is off simultaneously when non-conduction.
B) during data acquisition, what the input gate of collection terminal was to turn on.
C) during non-data gathers, the input gate of collection terminal is to disconnect.
D) analog signal channel voltage range：It is high-end compared with analog signal channel low side be 0V~5.1V.
E) circuit-under-test output should be Low ESR under normal circumstances, and measuring circuit input should be high impedance, and powers up and break
Impedance operator should be consistent as far as possible in the case of electricity.
F) it is collected end output impedance and is not more than 5k Ω.
G) collection terminal input impedance is not less than 10M Ω.
H) overvoltage capabilities：
● during collection terminal powers up, application ± 12V's is excessively electric on the output line of analog signal channel or its line of return
Pressure (impedance for crossing potential source is 2k Ω ± 0.3k Ω) should not damage analog channel, be not more than 10mA by the electric current of analog channel；
● collection terminal during power-off, application ± 10V's is excessively electric on the output line of analog signal channel or its line of return
Pressure should not damage analog signal channel.
Every gyro, accelerometer and navigation neceiver externally export two-way measurement data, are gathered per circuit-switched data with one
Business unit connects, and realizes hardware redundancy.
Communication between gyro, accelerometer and navigation neceiver and capturing service unit uses asynchronous serial half-duplex side
Formula, using RS-422 electric interfaces standards, baud rate 500kbps.Information represents that information is passed by byte using complement form
It sending, low byte is preceding, and high byte is rear, and each byte is formed by 12,1 start bit, 8 data bit, 1 odd parity bit, and 2
Position stop position.
Every capturing service unit provides a set of 422 interface, the RS-422 electric interfaces sequential phases of 2 capturing service units
Together, it is made of sampling clock, sample command and data.
Specific sequential is as follows：
Capturing service unit provides sampling pulse letter to the sampling clock interface of gyro, accelerometer and navigation neceiver
Number, the sampling period is 40ms ± 0.5ms, and pulse width is more than 100 μ s.
By 1/9 sample period time (most short is 4.4ms) after square wave rising edge is sampled, capturing service unit sends list
Byte sample command signal (each cycle is only sent out once).
After gyro, accelerometer and navigation neceiver receive sample command signal, by receiving within 60~70 μ s times
The data-interface of sample command sends data message and self-test status information to capturing service unit.
Capturing service unit carries out framing to the valid data addition identifier word received after valid data.
Step 2：The data gathered using aircraft platforms day earth communication system to 2 capturing service units are transmitted.
The transmission of the spacecraft data world can be divided into direct transmission and trunking traffic over the ground.2 capturing service units are directly hung
Platform 1553B buses are connected to, by the bus communication number that the pneumatic gauging data framing gathered by the cycle of 40ms is mono- frames of 160ms
According to bag, sent respectively in the engineering telemetry communication unit and relaying comprehensive unit that are equally mounted on platform 1553B buses, then warp knit
After the processing such as code, modulation, respectively through USB answering machine channeling and trunking channel downstreams to ground, for follow-up data processing.2
The pneumatic gauging data that capturing service unit externally exports are identical, in order to improve system reliability, reduce system resource and disappear
Consumption, 2 groups of pneumatic gauging data are by the way of parity frame multiplexing, and alternately downlink, realizes that the hardware of pneumatic gauging data transmission is superfluous
It is remaining.
Step 3：The data of 2 capturing service unit acquisitions are stored respectively using 2 black boxes.
Recoverable spacecraft is configured with black box and carries out significant data storage, and operation on orbit situation is analyzed after return
Processing.In order to carry out complete documentation to pneumatic gauging data, the present invention is configured with 2 black boxes, respectively to 2 capturing service lists
The pneumatic gauging data of member acquisition are stored, and realize hardware redundancy.In order to reduce system resources consumption, 2 black boxes are hung
It is connected in platform 1553B buses, completing pneumatic gauging data using periodical communication stores.
The present invention be suitable for it is interplanetary reenter, LEO reentry vehicle and aviation aircraft.
It is not specified in the present invention and partly belongs to techniques known.
Embodiments of the present invention are explained in detail above in association with attached drawing, but the present invention is not limited to described reality
Apply mode.For a person skilled in the art, without departing from the principles and spirit of the present invention to embodiment
The change, modification, replacement and modification of progress are still fallen in protection scope of the present invention.
Claims (9)
1. a kind of pneumatic gauging parameter information processing method, for rudders pneumatic power parameter acquisition, transimission and storage, it is special
Sign is, comprises the following steps：
By 2 capturing service units in aircraft platforms information system respectively to pneumatic pressure transmitter, gyro, acceleration
Meter and the data of navigation neceiver output are acquired, and 2 capturing service units mutually form backup；
The data of 2 capturing service unit acquisitions are transmitted using aircraft platforms day earth communication system；
The data of 2 capturing service unit acquisitions are stored respectively using 2 black boxes.
2. pneumatic gauging parameter information processing method according to claim 1, which is characterized in that the Pneumatic pressure sensing
Device is externally exported to be designed using two point two-wire, and every group of signal wire and loop line are connected with a capturing service unit；Pneumatic pressure
Force sensor data acquisition interface is both-end analog channel interface, using double level differential modes, a both-end analog channel by
Two input lines are formed, and one is simulation signal generator low side, is known as loop line, and one is high-end for simulation signal generator, is known as signal wire,
The high and low end of simulation signal generator compared with collection terminal analog references all float, and be connected to the acquisition simultaneously
In the specialized simulation input line at end.
3. pneumatic gauging parameter information processing method according to claim 2, which is characterized in that every gyro, institute
It states accelerometer and the navigation neceiver externally exports two-way measurement data, measurement data described in per road and an acquisition
Business unit connects；It is logical between the gyro, the accelerometer and the navigation neceiver and the capturing service unit
Letter is using asynchronous serial half-duplex mode, using RS-422 electric interfaces standards, baud rate 500kbps.
4. pneumatic gauging parameter information processing method according to claim 3, which is characterized in that the gyro, it is described plus
The communication information between speedometer and the navigation neceiver and the capturing service unit is using complement form expression, the letter
Breath is transmitted by byte, and low byte is preceding, and high byte is rear, and each byte is formed by 12,1 start bit, 8 data bit, 1
Odd parity bit, 2 stop positions.
5. pneumatic gauging parameter information processing method according to claim 3, which is characterized in that every capturing service
Unit provides a set of RS-422 electric interfaces, and the RS-422 electric interfaces sequential of 2 capturing service units is identical, by
Sampling clock, sample command and data composition.
6. pneumatic gauging parameter information processing method according to any one of claim 1 to 5, which is characterized in that described
In data transmission step, 2 capturing service units are directly mounted on platform 1553B buses, by the data group of acquisition
It is sent respectively after frame in the engineering telemetry communication unit for being mounted on the platform 1553B buses and relays comprehensive unit, then encoded,
After modulation treatment, respectively through USB answering machine channeling and trunking channel downstreams to ground, for follow-up data processing.
7. pneumatic gauging parameter information processing method according to claim 6, which is characterized in that the capturing service unit
The bus communication data packet that the data framing gathered by the cycle of 40ms is mono- frames of 160ms is sent in the engineering telemetering
Communication unit and the relaying comprehensive unit.
8. pneumatic gauging parameter information processing method according to claim 6, which is characterized in that 2 capturing services
The data that unit externally exports are identical, and data described in 2 groups are by the way of parity frame multiplexing, alternating downlink.
9. the pneumatic gauging parameter information processing method according to any one of claim 1,2,3,4,5,7,8, feature
It is, 2 black boxes are articulated in platform 1553B buses, and the storage of the data is completed using periodical communication.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611048794.4A CN108092751A (en) | 2016-11-22 | 2016-11-22 | Pneumatic gauging parameter information processing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611048794.4A CN108092751A (en) | 2016-11-22 | 2016-11-22 | Pneumatic gauging parameter information processing method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108092751A true CN108092751A (en) | 2018-05-29 |
Family
ID=62170254
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611048794.4A Pending CN108092751A (en) | 2016-11-22 | 2016-11-22 | Pneumatic gauging parameter information processing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108092751A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030130767A1 (en) * | 2002-01-07 | 2003-07-10 | Carroll Ernest A. | Method of and apparatus for acquiring aerial imagery for precision farming |
| CN103868545A (en) * | 2013-12-11 | 2014-06-18 | 中国航天空气动力技术研究院 | Multi-parameter flight dynamometry test data collection system |
| CN104991982A (en) * | 2015-04-16 | 2015-10-21 | 北京理工大学 | Aircraft aeroelasticity inertia sensor layout method |
-
2016
- 2016-11-22 CN CN201611048794.4A patent/CN108092751A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030130767A1 (en) * | 2002-01-07 | 2003-07-10 | Carroll Ernest A. | Method of and apparatus for acquiring aerial imagery for precision farming |
| CN103868545A (en) * | 2013-12-11 | 2014-06-18 | 中国航天空气动力技术研究院 | Multi-parameter flight dynamometry test data collection system |
| CN104991982A (en) * | 2015-04-16 | 2015-10-21 | 北京理工大学 | Aircraft aeroelasticity inertia sensor layout method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103925853B (en) | A kind of carrier rocket ground testing system device | |
| CN103744002B (en) | A kind of fault section recognition methods of cable based on current temporary state amount classified analysis on major constituents-line mixed power transmission line | |
| CN102833132B (en) | Detection method of onboard data multiplexer | |
| CN105896489A (en) | Differential protection method and system for multi-end T connected transmission line | |
| CN204761602U (en) | Machine carries general video acquisition system | |
| CN103279109A (en) | Locomotive digital value collecting device based on MVB bus | |
| CN101937031B (en) | Electric simulator for star sensor | |
| CN102394655B (en) | Manchester code converting method on MIC bus | |
| CN105915404B (en) | The test macro of SpaceWire network link signal quality and the evaluation method of signal quality | |
| CN108092751A (en) | Pneumatic gauging parameter information processing method | |
| CN201708806U (en) | Clock synchronous signal transmission circuit | |
| CN203720312U (en) | Universal ground test equipment for spaceborne computer | |
| CN102422599A (en) | Control architecture and interfacing methodology for cockpit control panel systems | |
| CN209728040U (en) | A kind of contact net shows lamp device again | |
| CN204389917U (en) | A kind of test platform for testing interlocking system connected by relay | |
| CN109286550A (en) | Multifunctional vehicle bus repeater based on FPGA technology | |
| CN102306444B (en) | Receiving circuit of meter-BUS (M-BUS) master station and data receiving method for receiving circuit | |
| CN101577598A (en) | Multiple signal multiplexing and demultiplexing methods, devices and systems | |
| CN202267951U (en) | FPGA (field-programmable gate array)-based multi-CPU (central processing unit) shared data sampling system | |
| CN110254475B (en) | Train operation monitoring system | |
| CN109828142A (en) | A kind of contact net shows lamp device and display methods again | |
| CN202940892U (en) | Flight data video overlap device | |
| CN105488007B (en) | Spaceborne HSSI High-Speed Serial Interface device and data transmission method | |
| CN201654249U (en) | Electrode conversion equipment of high density electrcal instrument | |
| CN202126902U (en) | Resistance device with adjustable digital quantity |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180529 |
|
| WD01 | Invention patent application deemed withdrawn after publication |