CN112562305A - Aircraft test bus system based on power line carrier communication - Google Patents
Aircraft test bus system based on power line carrier communication Download PDFInfo
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- CN112562305A CN112562305A CN202011406682.8A CN202011406682A CN112562305A CN 112562305 A CN112562305 A CN 112562305A CN 202011406682 A CN202011406682 A CN 202011406682A CN 112562305 A CN112562305 A CN 112562305A
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- carrier communication
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- 238000004891 communication Methods 0.000 title claims abstract description 38
- 238000012360 testing method Methods 0.000 title claims abstract description 23
- 230000001133 acceleration Effects 0.000 claims description 8
- 230000003068 static effect Effects 0.000 claims description 6
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 4
- 238000013480 data collection Methods 0.000 claims description 4
- 238000013461 design Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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- G—PHYSICS
- G08—SIGNALLING
- G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
- G08C19/00—Electric signal transmission systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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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
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B3/00—Line transmission systems
- H04B3/54—Systems for transmission via power distribution lines
- H04B3/546—Combination of signalling, telemetering, protection
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Power Engineering (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Small-Scale Networks (AREA)
Abstract
The application provides an aircraft test bus system based on power line carrier communication includes: at least one data recording device; the data acquisition node equipment is connected to the data recording equipment through a power cable and is used for acquiring state information of the airplane; the data acquisition node equipment is provided with a carrier communication module, the carrier communication module can quantize the acquired airplane state information and then carry out carrier communication so as to transmit the information to the data recording equipment, the data recording equipment carries out data receiving and transmitting through a power cable, and the information collected by the data acquisition node equipment distributed on the whole airplane is recorded and stored. The aircraft test bus system provided by the application replaces the traditional bus communication cable by using power cable carrier communication, so that the weight of the cable is greatly reduced, the area of a panel of equipment interface equipment is reduced, and the cost is saved.
Description
Technical Field
The application belongs to the technical field of aircraft testing, and particularly relates to an aircraft testing bus system based on power line carrier communication.
Background
In the prior art, buses such as RS422, HB6096, IEEE1394 and the like are generally used as communication protocols, and a special communication cable needs to be laid between the data acquisition node device and the data recording device. The bus communication scheme needs a special bus cable, the weight of the bus cable is heavy, the coordination workload of the interface and the laying is large, and the hardware design needs to be changed after the interface is changed.
Disclosure of Invention
It is an object of the present application to provide an aircraft test bus system based on power carrier communication to solve or mitigate at least one of the problems of the background art.
The technical scheme of the application is as follows: an aircraft test bus system based on power line carrier communication, comprising:
at least one data recording device; and
the system comprises a plurality of data acquisition node devices, a data recording device and a data processing device, wherein the data acquisition node devices are connected to the data recording device through power cables and are used for acquiring state information of an airplane;
the data acquisition node equipment is provided with a carrier communication module, the carrier communication module can quantize the acquired airplane state information and then carry out carrier communication so as to transmit the information to the data recording equipment, the data recording equipment carries out data receiving and transmitting through a power cable, and the information collected by the data acquisition node equipment distributed on the whole airplane is recorded and stored.
Further, the aircraft state information comprises aircraft static pressure, pulsating pressure, surface temperature, internal temperature, strain, vibration, acceleration, angular velocity, speed, attitude, position, system working state and switching value state.
Furthermore, the system also comprises a plurality of types of sensors, and the sensors are in data transmission with the data acquisition nodes through communication lines.
Further, the sensor and information source device types include a static pressure sensor, a dynamic pressure sensor, a strain sensor, a humidity sensor, a temperature sensor, an acceleration sensor, a vibration sensor, inertial navigation equipment, a flight control computer and a switch.
Further, the data recording device and the data acquisition node device realize DC power supply through the power cable.
Further, the DC power source is derived from aircraft power.
The aircraft test bus system provided by the application replaces the traditional bus communication cable by using power cable carrier communication, so that the weight of the cable is greatly reduced, the area of a panel of equipment interface equipment is reduced, and the cost is saved.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic diagram of an aircraft test bus system based on power carrier communication according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
To overcome the problems identified in the background, the present application provides an aircraft test bus system based on power carrier communication. As shown in fig. 1, the aircraft test bus system based on power carrier communication provided by the present application includes: the system comprises at least one data recording device and a plurality of data acquisition node devices.
The data acquisition node equipment is used for acquiring or receiving state information of the aircraft, wherein the state information comprises information such as aircraft static pressure, pulsating pressure, surface temperature, internal temperature, strain, vibration, acceleration, angular rate, speed, attitude, position, system working state and switching value state.
It is understood that the status information is usually collected by various types of sensors and information source devices, such as static pressure sensors, dynamic pressure sensors, strain sensors, humidity sensors, temperature sensors, acceleration sensors, vibration sensors, inertial navigation devices, flight control computers and switches. And the sensors transmit information to corresponding lower data acquisition node equipment through power cables. For example, the data collection node device 1 is connected with an acceleration sensor, a vibration sensor, a strain sensor and the like through a power cable to collect corresponding data of acceleration, vibration, strain and the like, and the data collection node device 4 is connected with a load switch through the power cable to collect state data of the load switch. Other data acquisition node devices are not described in detail.
In addition, the data acquisition node device may also acquire or receive state information sent by the onboard device through a communication bus such as an RS422, for example, the data acquisition node device n acquires control data of the flight control computer through the RS422 bus, and acquires working state data of the servo controller through the RS485 bus.
And after the data acquisition node equipment acquires or receives the state information, the state information is converted into a carrier communication signal so as to be transmitted conveniently.
The data acquisition node equipment is divided into a plurality of node equipment according to the on-board position of the test point in the airplane test project and then arranged near the test point. And the data acquisition node equipment uploads the quantized or collected data to the data recording equipment through the power cable.
The data recording equipment is connected with the data acquisition node equipment through a power cable, and the data recording equipment collects, summarizes and records data uploaded by the data acquisition node equipment of the whole machine.
The data recording equipment is powered by a power distribution device, and the power supply by using a 28V DC power supply on the airplane is realized. The data recording equipment transmits a power supply to each data acquisition node equipment through a power cable, data receiving and transmitting are carried out through a carrier communication technology, information collected by the data acquisition equipment distributed in the whole machine is recorded, and finally the dual purposes of weight reduction and flexible arrangement of a bus system are achieved.
The aircraft test bus system provided by the application relies on a power line carrier communication technology, so that the data acquisition node equipment is flexibly arranged, and the required information can be acquired only by connecting the data recording equipment through a power supply cable for power supply as long as space permits; data acquisition node equipment can be flexibly added according to the needs without adding corresponding data recording equipment interfaces; the weight of the communication cable is reduced, and the panel area and the equipment weight of the data acquisition node equipment and the data recording equipment are reduced; the production and laying cost of the test cable is reduced; design coordination of physical interfaces is reduced, and design flexibility is improved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. An aircraft test bus system based on power line carrier communication, comprising:
at least one data recording device; and
the system comprises a plurality of data acquisition node devices, a plurality of data acquisition node devices and a plurality of data recording devices, wherein the data acquisition node devices are connected to the data recording devices through power cables and are used for acquiring or receiving airplane state information;
the data acquisition node equipment is provided with a carrier communication module, the carrier communication module can quantize the acquired airplane state information and then carry out carrier communication so as to transmit the information to the data recording equipment, the data recording equipment carries out data receiving and transmitting through a power cable, and the information collected by the data acquisition node equipment distributed on the whole airplane is recorded and stored.
2. The power carrier communication-based aircraft test bus system of claim 1 wherein the aircraft state information comprises aircraft static pressure, pulsating pressure, surface temperature, interior temperature, strain, vibration, acceleration, angular rate, velocity, attitude, position, system operating state, and switching value state.
3. An aircraft test bus system based on power carrier communication as claimed in claim 2, further comprising a plurality of types of sensors, the sensors communicating with the data collection nodes via communication lines.
4. An aircraft test bus system based on power line carrier communication as claimed in claim 3, wherein the sensor and information source device types include static pressure sensors, dynamic pressure sensors, strain sensors, humidity sensors, temperature sensors, acceleration sensors, vibration sensors, inertial navigation devices, flight control computers and switches. .
5. An aircraft test bus system based on power carrier communication as claimed in claim 1, wherein the data logging device and the data collection node device are powered by a DC power source via the power cable.
6. An aircraft test bus system over power carrier communication as defined in claim 1, wherein the DC power source is derived from aircraft power.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011406682.8A CN112562305A (en) | 2020-12-04 | 2020-12-04 | Aircraft test bus system based on power line carrier communication |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011406682.8A CN112562305A (en) | 2020-12-04 | 2020-12-04 | Aircraft test bus system based on power line carrier communication |
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| Publication Number | Publication Date |
|---|---|
| CN112562305A true CN112562305A (en) | 2021-03-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011406682.8A Pending CN112562305A (en) | 2020-12-04 | 2020-12-04 | Aircraft test bus system based on power line carrier communication |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114577241A (en) * | 2022-03-02 | 2022-06-03 | 北京卫星环境工程研究所 | Optical fiber multi-module multi-parameter airborne independent test method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203689062U (en) * | 2013-12-25 | 2014-07-02 | 河南辉煌科技股份有限公司 | Separation type portable signal monitor |
| CN203942545U (en) * | 2014-05-29 | 2014-11-12 | 西安中飞航空测试技术发展有限公司 | The aircraft test data collection system serial data exchange bus architecture of autonomous definition |
| CN105634893A (en) * | 2015-12-28 | 2016-06-01 | 中国石油天然气集团公司 | Petroleum downhole signal real-time transmission control system |
| CN209410084U (en) * | 2018-11-01 | 2019-09-20 | 北京全路通信信号研究设计院集团有限公司 | Monitoring platform |
-
2020
- 2020-12-04 CN CN202011406682.8A patent/CN112562305A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203689062U (en) * | 2013-12-25 | 2014-07-02 | 河南辉煌科技股份有限公司 | Separation type portable signal monitor |
| CN203942545U (en) * | 2014-05-29 | 2014-11-12 | 西安中飞航空测试技术发展有限公司 | The aircraft test data collection system serial data exchange bus architecture of autonomous definition |
| CN105634893A (en) * | 2015-12-28 | 2016-06-01 | 中国石油天然气集团公司 | Petroleum downhole signal real-time transmission control system |
| CN209410084U (en) * | 2018-11-01 | 2019-09-20 | 北京全路通信信号研究设计院集团有限公司 | Monitoring platform |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114577241A (en) * | 2022-03-02 | 2022-06-03 | 北京卫星环境工程研究所 | Optical fiber multi-module multi-parameter airborne independent test method |
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Application publication date: 20210326 |