CN108241358A - A kind of method for the interaction of airplane complete machine avionics data - Google Patents
A kind of method for the interaction of airplane complete machine avionics data Download PDFInfo
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- CN108241358A CN108241358A CN201711293259.XA CN201711293259A CN108241358A CN 108241358 A CN108241358 A CN 108241358A CN 201711293259 A CN201711293259 A CN 201711293259A CN 108241358 A CN108241358 A CN 108241358A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0208—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
- G05B23/0213—Modular or universal configuration of the monitoring system, e.g. monitoring system having modules that may be combined to build monitoring program; monitoring system that can be applied to legacy systems; adaptable monitoring system; using different communication protocols
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24048—Remote test, monitoring, diagnostic
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Small-Scale Networks (AREA)
Abstract
The present invention provides a kind of methods for the interaction of airplane complete machine avionics data.In order to acquire the data of complete airplane complete machine avionic device, interface of the cable plug end as data interaction of flight parameter recording equipment will be connected, it is connected with test equipment, when the signals such as reality data acquisition bus, discrete magnitude, switching value, while the simulation excitation function of test equipment can be passed through and input respective bus data.By data above interactive mode, achieve the purpose that closed loop on-line checking.Former machine avionic device gathered data is made to be not required to through transfer and processing, ensure that its integrality and reliability.
Description
Technical field
This patent is related to airplane complete machine avionic device on-line testing technique field, and aircraft is used in particular to one kind
The method of complete machine avionics data interaction.
Background technology
The avionic device of aircraft is broadly divided into avionics system, flight control system, power supply, Mechatronic Systems etc., is filled in aircraft
With must be detected to ensure Aircraft Quality and flight safety to function, the performance of avionic device in the process.
At present, avionic device before final assembly using in laboratory to component or system detectio by the way of carry out,
Final assembly is carried out after detection again；After the completion of assembling, complete machine avionic device is closed loop states, is only capable of showing by machine
Show that control function carries out simple functions inspection.In practical work, it is only capable of using the former machine avionic device of decomposition or its connecting line
Complete machine avionics system is become open loop situations by the mode of cable from closed loop states, and then by transferring cable or adapter connects
Enter test equipment, achieve the purpose that data interaction.For example, certain in-situ test equipment when being tested, need to disconnect former machine cable,
It is tested with test equipment cable connection airborne equipment, but the method cannot meet requirement of the user to complete machine closed loop test,
Also it can not ensure the primitiveness of data, reliability is low, is only capable of a kind of means as fault diagnosis, can not be applied to production assembling
Process.Summary, problem of the existing technology essentially consist in 1, are not decomposing former machine avionic device and its connecting line
Under the premise of cable, complete machine online data can not be acquired, extra order or simulation excitation can not also be inputted, caused in on-line testing
Hold imperfect, it is impossible to achieve the purpose that airplane complete machine avionics system closed loop detects.2nd, part aircraft can be used is joined by flying
The detection mouth of number scale recording apparatus carries out data acquisition, but this data passes through the processing of flight parameter recording equipment, can not collect
Complete data.3rd, it is only capable of not realizing bus excitation emulation into row energization by sensor, can not realizing more multi-functional test
Card.
Invention content
To solve the above-mentioned problems, the data of complete airplane complete machine avionic device can be acquired, are realized for whole
Machine avionic device closed loop on-line test is used for what airplane complete machine avionics data interacted the present invention provides a kind of
Method includes the following steps：
1 using the test cable that the connector of flight parameter recording equipment matches is connect with aircraft, and connection aircraft is with surveying
Try equipment；
2 acquired in real time by test equipment without the processed engine system of flight parameter recording equipment, hydraulic system,
Fuel system, Landing Gear System, bay door system, seat system, avionics system, flight control system, task system, power supply system
System, the HB6096 buses of Mechatronic Systems, discrete magnitude, switching value original signal realize former machine avionic device initial data
Acquisition；
It is each the signal is input to aircraft by cable by test equipment simulation excitation signal while 3 acquisition initial data
System encourages each system function, by data above interactive mode, realizes Airplane Avionics closed loop test.
If GJB289A buses are employed simultaneously on aircraft, using GJB289A Bussing connectors on aircraft as GJB289A
The interface of bus data interaction, is connected with test equipment, when acquire GJB289A bus datas in fact, while can be set by test
Standby simulation excitation function input bus data.If employing FC, AFDX bus simultaneously on aircraft, network on aircraft is handed over
Change planes the interface that the connector of (or equivalent of the apparatus) is interacted as FC, AFDX bus data, by network switch port with
Line testing device is connected, when acquire FC, AFDX bus data in fact, while the simulation excitation function number of test equipment can be passed through
Enter bus data.
Advantageous effect in this way is：
1st, former machine avionic device gathered data ensures its integrality and reliability without transfer and processing.
2nd, bus data simulation excitation is realized.
3rd, it can be achieved for complete machine avionic device closed loop on-line test, disclosure satisfy that user detected complete machine closed loop
Quality control requirement.
Description of the drawings
Fig. 1 avionics data interaction logic figures
Explanation is numbered in figure：1st, discrete magnitude, on-off model 2, bus signals
Specific embodiment
As shown in the figure, a kind of method for the interaction of airplane complete machine avionics data, includes the following steps：
1 using the test cable that the connector of flight parameter recording equipment matches is connect with aircraft, and connection aircraft is with surveying
Try equipment；
2 acquired in real time by test equipment without the processed engine system of flight parameter recording equipment, hydraulic system,
Fuel system, Landing Gear System, bay door system, seat system, avionics system, flight control system, task system, power supply system
System, the bus signals 2 of Mechatronic Systems and discrete magnitude, on-off model 1 realize adopting for former machine avionic device initial data
Collection；
By test equipment simulation excitation signal while 3 acquisition initial data, by cable by bus signals 2 and discrete
Amount, on-off model 1 are input to each system of aircraft, encourage each system function, by data above interactive mode, realize Aircraft
Empty electronic equipment closed loop test.
If GJB289A buses are employed simultaneously on aircraft, using GJB289A Bussing connectors on aircraft as GJB289A
The interface of bus data interaction, is connected with test equipment, when acquire GJB289A bus datas in fact, while can be set by test
Standby simulation excitation function input bus data.If employing FC, AFDX bus simultaneously on aircraft, network on aircraft is handed over
Change planes the interface that the connector of (or equivalent of the apparatus) is interacted as FC, AFDX bus data, by network switch port with
Line testing device is connected, when acquire FC, AFDX bus data in fact, while the simulation excitation function number of test equipment can be passed through
Enter bus data.
When defining the p-wire to match using such as Fig. 1 and the cable plug and core wire of aircraft flight reference record equipment
Cable connects aircraft and test equipment.By engine system, hydraulic system, fuel system, Landing Gear System, bay door system, seat
System, avionics system, flight control system, task system, electric power system, Mechatronic Systems bus signals 1, discrete magnitude, switch
Amount signal 2 leads to test equipment, realizes the acquisition of former machine avionics data.Meanwhile test equipment can be imitated
True excited data is entered data by bus to avionics system, flight control system, task system, electric power system, electromechanical system
System.It realizes and does not decompose former machine avionic device and its connection cables, using the access side of former machine Avionics Interface
Formula carries out complete machine avionics system grade closed loop on-line test, and complete machine boat can not be carried out at present so as to effectively solve
The problem of empty electronic equipment closed loop on-line test.
Claims (3)
- A kind of 1. method for the interaction of airplane complete machine avionics data, it is characterised in that include the following steps：1-1 is using the test cable that the connector of flight parameter recording equipment matches is connect with aircraft, and connection aircraft is with testing Equipment；1-2 is acquired by test equipment in real time without the processed engine system of flight parameter recording equipment, hydraulic system, combustion Oil system, Landing Gear System, bay door system, seat system, avionics system, flight control system, task system, electric power system, Bus signals and discrete magnitude, the on-off model of Mechatronic Systems realize the acquisition of former machine avionic device initial data；By test equipment simulation excitation signal while 1-3 acquires initial data, by cable by bus signals and discrete magnitude, open Pass amount signal is input to each system of aircraft, encourages each system function, by data above interactive mode, realizes aircraft avionics Equipment closed loop test.
- 2. a kind of method for the interaction of airplane complete machine avionics data according to claim 1, feature exist In employing GJB289A buses on aircraft, then interacted GJB289A Bussing connectors on aircraft as GJB289A bus datas Interface, be connected with test equipment, when acquire GJB289A bus signals and discrete magnitude, on-off model in fact, while can pass through The simulation excitation function input bus data of test equipment.
- 3. a kind of method for the interaction of airplane complete machine avionics data according to claim 1, feature exist In employing FC, AFDX bus on aircraft, then interacted the connector of the network switch on aircraft as FC, AFDX bus data Interface, be connected by network switch port with on-line testing equipment, when acquire FC, AFDX bus signals and discrete in fact Amount, on-off model, while can bus data be inputted by the simulation excitation function of test equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711293259.XA CN108241358A (en) | 2017-12-08 | 2017-12-08 | A kind of method for the interaction of airplane complete machine avionics data |
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| CN201711293259.XA CN108241358A (en) | 2017-12-08 | 2017-12-08 | A kind of method for the interaction of airplane complete machine avionics data |
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| CN108241358A true CN108241358A (en) | 2018-07-03 |
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| CN201711293259.XA Pending CN108241358A (en) | 2017-12-08 | 2017-12-08 | A kind of method for the interaction of airplane complete machine avionics data |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109189046A (en) * | 2018-09-03 | 2019-01-11 | 西安飞机工业（集团）有限责任公司 | A kind of large aircraft Mechatronic Systems all-around test stand |
| CN109279048A (en) * | 2018-11-20 | 2019-01-29 | 中航通飞华南飞机工业有限公司 | A kind of engine and APU revolving speed and avionics system are crosslinked closed loop detection method |
| CN109359051A (en) * | 2018-11-21 | 2019-02-19 | 哈尔滨飞机工业集团有限责任公司 | A kind of airborne helmet sight detection device |
| CN112462169A (en) * | 2020-11-05 | 2021-03-09 | 陕西飞机工业（集团）有限公司 | System and method for testing shielding effectiveness of whole airplane |
| CN114486310A (en) * | 2021-12-31 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Dynamic simulation comprehensive test system and method for aircraft electromechanical management system |
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Application publication date: 20180703 |