CN107944193A - Avionics semi-matter simulating system - Google Patents
Avionics semi-matter simulating system Download PDFInfo
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- CN107944193A CN107944193A CN201711345023.6A CN201711345023A CN107944193A CN 107944193 A CN107944193 A CN 107944193A CN 201711345023 A CN201711345023 A CN 201711345023A CN 107944193 A CN107944193 A CN 107944193A
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
Abstract
The present invention relates to a kind of avionics semi-matter simulating system, the system is designed using modular design concept completely, whole system all has configurability, autgmentability from structure, hardware interface, software function, disclosure satisfy that different scales, the validation test demand of model avionics system.As shown below, whole system mainly includes avionics real-time computer, management platform, pulpit and operating system, adapter, hardware interface device（I/O interfaces）, data injection, Interface integration, third party software expansion interface storehouse and network communication；It can meet configuration item in institute/system testing requirement, configuration item/system testers are coordinated to carry out avionics system semi-hardware type simulation test, reduce and repeat and mechanization work, optimal inspection process, makes demand tracking case designing test execution test data record test report several stages can implementation tool automation.
Description
Technical field
The present invention relates to avionics to emulate field, and in particular to a kind of avionics semi-matter simulating system.
Background technology
Avionics system full name " integrated avionics system ", is an important component for modernizing fighter plane, fights
The operational performance of machine and avionics system are closely related.Integrated avionic system is existing tens under demand pull and promoting technology
The developing history in year, particularly closely about ten years, achieves noticeable progress, promotes further carrying for airborne combat efficiency
It is high.However, integrated avionic system exposes many shortcomings in use at present, it would be highly desirable to is subject to improve and perfect;Together
When, the battle tactics of 21 century and the development of mode also propose integrated avionic system the requirement of more challenge.Therefore, not
10 years come, while eminently affordable sex chromosome mosaicism is solved, integrated avionic system will be towards more synthesization, information
Change, technicalization, modularization and intelligentized direction are developed, and the function of integrated avionic system, performance and reliability, maintenance
Property, protection, testability and comprehensive effectiveness also will appear from breakthrough leap.Will it is contemplated that Avionics are horizontal
It is continuously improved, avionics integration technology will develop both in depth and in breadth, obtain constantly improve.
Avionics system can't be applied to directly in fighter plane after developing, it is necessary first to avionics system progressive
It can emulate, be put into again in practice after its perfect performance；But for now, most avionics simulation system is equal
Be by software building simulated environment, and every time be required for according to the performance of avionics system carry out simulated environment building so that often
Secondary emulation is required for rebuilding simulated environment, causes substantial amounts of repetition and mechanization work, is required for every time to emulation
Environment could emulate avionics code after being debugged.
The content of the invention
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of avionics semi-matter simulating system, can subtract
Few to repeat to work with mechanization, optimal inspection process, makes demand tracking-case designing-test execution-test data record-survey
Examination report several stages can implementation tool automation, direct simulation running environment can be provided to avionics code.
The purpose of the present invention is what is be achieved through the following technical solutions：
Avionics semi-matter simulating system, the system include avionics real-time computer, management platform, pulpit and operation and are
System, adapter, hardware interface device, data injection unit, Interface integration module, third party software expansion interface storehouse and network
Communication；
The avionics real-time computer is the Simulation Test Environment of whole system；
Before the management platform test execution, by line or under line for avionics real-time computer provide test case be used as it is defeated
Enter；After test execution, test result and defect for formation, which are imported into management platform, is managed filing, and to data into
Generation test is summarized after row collects；
The pulpit is real-time for pilot or tester in analog simulation verification process and avionics with steerable system
The interworking of computer, data communication is carried out by reflective memory network and avionics real-time computer；
The software of the third party expansion interface storehouse provides external interface storehouse, supports the specific demand of user's specialty, realizes that avionics half is real
Thing analogue system Multi-function extension is developed；
The adapter is used to receive excitation injection information, simulates the action and logical operation of avionics system application program completely
Journey, produces corresponding IO and serial ports output, realizes the communication function of avionics system and input stimulus；
The hardware interface device is the in-kind portion in simulation software, is made of various types of I/O interfaces, it with it is real
System under test (SUT) connects, and is that test environment sends test data and receives the physical channel of test result data；
The data injection unit is used for use-case injection and two kinds of input modes of direct fault location by simulation software；
The Interface integration is directed to management platform on-line mode, and tester obtains in Cloud Server manage on the local computer
After the license of platform, by pre-configured enterprise's bus, data export/import operation can be carried out；
The communication network include avionics real-time computer with and platform management Ethernet and avionics real-time computer and seat
Reflective memory network between cabin/control simulation system.
Further as this programme is improved, the avionics real-time computer according to before test, test when and test after three
In a stage, it is respectively completed herein below：
Before test：Simulation model needed for test is formed by Simulation Model Development instrument, while automatically generates respective code；By surveying
This implantation tool of training imports test script, and test script is generated by script compiler；With reference to management platform, by line and
Two ways obtains test input data under line；
Task management and the Real-Time Scheduling mechanism of whole test environment are provided during test by avionics real-time computer；By testing automatically
Control software, inputs various signals according to use-case step and encourages, realize real-time use-case function of injecting；Controlled by direct fault location soft
Part is soft with reference to the experience bag of expert's fault database, such as main display and control software failure bag, navigation management software fault bag and sensor management
Part failure bag etc., realizes the logic control input of failure；The test script of importing is parsed by test script resolver；It is imitative
Loading, transmission, collection and the display of data during true test；Test command is added by test monitoring panel in real time；According to reality
Real-time display is needed to specify data；Hard real time communication mechanism between real-time computer and system under test (SUT)；Driving simulation model is defeated
Go out data, system under test (SUT) is sent to by I/O drivings；Using the three-level management mechanism of project-engineering-test cell；Project pair
A model system is answered, multiple engineerings can be established below, each engineering corresponds to a crosslinked test environment model；Test is single
First result for each crosslinking environmental model preserves, it is achieved thereby that the preservation of each test scene and the multiplexing of test experience；
By the test result data being collected into after test run compared with expected results, analysis and playback, obtain testing whether to lead to
The conclusion crossed；
After test：Result data is imported from avionics real-time computer to management platform.
Further as this programme is improved, and the real-time display specifies the mode of data to be shown including such as tendency chart, column
Shape figure is shown, traffic light system etc..
Further as this programme is improved, and the adapter is used to be connected with pulpit with steerable system, passes through
The manipulation signal of cockpit system is sent to avionics real-time computer by A/D conversions, while is generated necessary avionics information and passed through D/A
Or D/D passes it to pilot block cabin system.
Further as this programme is improved, and the avionics information includes radar information, sensor information.
Further as this programme is improved, and the communication network is further included between avionics real-time computer and system under test (SUT)
Hard real time communication mechanism.
Further as this programme is improved, the hardware interface device include 1553B, CAN/AD, DA, RS232,
RS422, RS485, DI, DO, RELAY, Ethernet, and user's custom interface.
Further as this programme is improved, and the direct fault location crosses the specific serial ports bag of software pouring, each failure by
Corresponding failure and occupy-place uniquely determine, sent through real-time computer to system under test (SUT).In combination with experience failure in experts database
Bag, parses corresponding failure title and provides the possible cause that corresponding failure produces, realize the verification to avionics system failure.
Further as this programme is improved, and the use-case injection passes through the specific interface data bag of software pouring, described
Data content is signal ID and its original physics numerical quantity, and use-case input is parsed according to respective algorithms through real-time computer
Sent to induction signal, and by I/O hardware interfaces to system under test (SUT).
The beneficial effects of the invention are as follows：Compare with traditional avionics simulation system system, advantage of the invention is that：
（1）A variety of data entry modes；
（2）Realize that information monitoring shows, runs Control ＆ data acquisition, processing and storage；
（3）External interface storehouse is provided, supports to carry out Function Extension exploitation to real-time emulation system；
（4）Realize the verification to avionics system failure；
（5）Realization automatically analyzes test result；
（6）Realize the in-stockroom operation to analysis result；
（7）Realize avionics semi-hardware type simulation test automatic test.
Brief description of the drawings
Fig. 1 is the system block diagram of the present invention；
Fig. 2 is the system block diagram of avionics real-time computer of the present invention.
Embodiment
Technical scheme is described in further detail with reference to specific embodiment, but protection scope of the present invention is not
It is confined to as described below.
As shown in Figs. 1-2：
Configuration item/system testing requirement in meet, coordinates configuration item/system testers to carry out avionics system half in kind imitative
True test, reduces repetition and mechanization work, optimal inspection process, makes demand tracking-case designing-test execution-test number
Can implementation tool automation according to record-test report several stages.We integrate in one avionics HWIL simulation of Program Construction
Platform, the platform can provide direct simulation running environment to avionics code.For the content of above-mentioned realization, avionics half is established
Matter simulating system, the system are designed using modular design concept completely, and whole system is from structure, hardware interface, soft
Part function all has configurability, autgmentability, disclosure satisfy that different scales, the validation test demand of model avionics system.
Avionics semi-matter simulating system, the system include avionics real-time computer, management platform, pulpit and operation
System, adapter, hardware interface device, data injection unit, Interface integration module, third party software expansion interface storehouse and net
Network communicates；
The avionics real-time computer is the Simulation Test Environment of whole system；
Before the management platform test execution, by line or under line for avionics real-time computer provide test case be used as it is defeated
Enter；After test execution, test result and defect for formation, which are imported into management platform, is managed filing, and to data into
Generation test is summarized after row collects；
The pulpit is real-time for pilot or tester in analog simulation verification process and avionics with steerable system
The interworking of computer, data communication is carried out by reflective memory network and avionics real-time computer；
The software of the third party expansion interface storehouse provides external interface storehouse, supports the specific demand of user's specialty, realizes that avionics half is real
Thing analogue system Multi-function extension is developed；
The adapter is used to receive excitation injection information, simulates the action and logical operation of avionics system application program completely
Journey, produces corresponding IO and serial ports output, realizes the communication function of avionics system and input stimulus；
The hardware interface device is the in-kind portion in simulation software, is made of various types of I/O interfaces, it with it is real
System under test (SUT) connects, and is that test environment sends test data and receives the physical channel of test result data；
The data injection unit is used for use-case injection and two kinds of input modes of direct fault location by simulation software；
The Interface integration is directed to management platform on-line mode, and tester obtains in Cloud Server manage on the local computer
After the license of platform, by pre-configured enterprise's bus, data export/import operation can be carried out；
The communication network include avionics real-time computer with and platform management Ethernet and avionics real-time computer and seat
Reflective memory network between cabin/control simulation system.
The concrete application of each link is as follows：
Avionics real-time computer：Avionics real-time computer be whole system Simulation Test Environment, according to test before, test when and
Three phases after test, are respectively completed herein below：
Before test
Simulation model needed for test is formed by Simulation Model Development instrument, while automatically generates respective code；
Test script is imported by test script implantation tool, test script is generated by script compiler；
With reference to management platform, test input data is obtained by online and offline two ways.
During test
Task management and the Real-Time Scheduling mechanism of whole test environment are provided by avionics real-time computer；
By automatic testing and control software, input various signals according to use-case step and encourage, realize real-time use-case function of injecting；
By Fault Insertion Control Software, with reference to the experience bag of expert's fault database, such as main display and control software failure bag, navigation management software
Failure bag and sensor management software fault bag etc., realize the logic control input of failure；
The test script of importing is parsed by test script resolver；
Loading, transmission, collection and the display of data during emulation testing.Test command is added by test monitoring panel in real time；Root
According to actual needs in a different manner（Such as tendency chart is shown, block diagram is shown, traffic light system）Real-time display specifies data；
Hard real time communication mechanism between real-time computer and system under test (SUT)；
Driving simulation model output data, system under test (SUT) is sent to by I/O drivings；
Using the three-level management mechanism of project-engineering-test cell.Project corresponds to a model system, can establish below more
A engineering, each engineering correspond to a crosslinked test environment model.Result of the test cell for each crosslinking environmental model
Preserve, it is achieved thereby that the preservation of each test scene and the multiplexing of test experience；
By the test result data being collected into after test run compared with expected results, analysis and playback, obtaining test is
The no conclusion passed through.
After test
Result data is imported from avionics real-time computer to management platform.
Management platform：Before test execution, by line or under line for avionics real-time computer provide test case be used as it is defeated
Enter.After test execution, test result and defect for formation, which can be imported into management platform, is managed filing, and to data
Generation test is summarized after being collected；
Pulpit and steerable system：Pilot or tester and avionics real-time computer in analog simulation verification process
Interworking, data communication is carried out by reflective memory network and avionics real-time computer；
Third party software expansion interface storehouse：External interface storehouse is provided, supports the specific demand of user's specialty, realizes that avionics half is in kind
Analogue system Multi-function extension is developed；
Adapter：For receiving to encourage injection information, action and the logical operation process of avionics system application program are simulated completely,
Corresponding IO and serial ports output is produced, realizes the communication function of avionics system and input stimulus.It is main to complete three parts task：
It is connected with pulpit with steerable system, changes that the manipulation signal of cockpit system is sent to avionics is real-time by A/D
Computer；
The necessary avionics information of generation, such as radar/sensor information, pulpit system is passed it to by D/A or D/D
System.
Hardware interface device（I/O interfaces）：Hardware interface device is the in-kind portion in simulation software, by various types of
I/O interfaces form, it is connected with real system under test (SUT), are that test environment sends test data and receives test result data
Physical channel.Studied through discussing, the bus and I/O interface that this platform can be supported have：
1553B/ CAN/AD/DA/RS232/RS422/RS485/DI/DO/RELAY/ Ethernets, and user's custom interface etc.；
Data injection unit：Use-case injection and two kinds of input modes of direct fault location are used for by simulation software：
Direct fault location：Pass through the specific serial ports bag of software pouring（Each failure is uniquely determined by corresponding failure and occupy-place）, warp
Real-time computer is sent to system under test (SUT).In combination with experience failure bag in experts database（Such as main display and control software failure bag, navigation pipe
Manage software fault bag and sensor management software fault bag etc.）, parse corresponding failure title and provide corresponding failure generation
Possible cause, realize the verification to avionics system failure；
Use-case injects：Pass through the specific interface data bag of software pouring（Data content is signal ID and its original physical quantity number
Value）.Through real-time computer according to respective algorithms parse use-case input to induction signal, and by I/O hardware interfaces send to
System under test (SUT).
Interface integration：For management platform on-line mode, tester obtains Cloud Server middle pipe on the local computer
After the license of platform, by pre-configured enterprise's bus, data export/import operation can be carried out；
Communication network：Including avionics real-time computer with and platform management Ethernet and avionics real-time computer and cockpit/
Reflective memory network between control simulation system.Except, further include the strong reality between avionics real-time computer and system under test (SUT)
When communication mechanism.
The above is only the preferred embodiment of the present invention, it should be understood that the present invention is not limited to described herein
Form, is not to be taken as the exclusion to other embodiment, and can be used for various other combinations, modification and environment, and can be at this
In the text contemplated scope, it is modified by the technology or knowledge of above-mentioned teaching or association area.And those skilled in the art institute into
Capable modifications and changes do not depart from the spirit and scope of the present invention, then all should be in the protection domain of appended claims of the present invention
It is interior.
Claims (9)
1. avionics semi-matter simulating system, it is characterised in that the system includes avionics real-time computer, management platform, pilot
Cockpit connects with operating system, adapter, hardware interface device, data injection unit, Interface integration module, third party software extension
Mouth storehouse and network communication；
The avionics real-time computer is the Simulation Test Environment of whole system；
Before the management platform test execution, by line or under line for avionics real-time computer provide test case be used as it is defeated
Enter；After test execution, test result and defect for formation, which are imported into management platform, is managed filing, and to data into
Generation test is summarized after row collects；
The pulpit is real-time for pilot or tester in analog simulation verification process and avionics with steerable system
The interworking of computer, data communication is carried out by reflective memory network and avionics real-time computer；
The software of the third party expansion interface storehouse provides external interface storehouse, supports the specific demand of user's specialty, realizes that avionics half is real
Thing analogue system Multi-function extension is developed；
The adapter is used to receive excitation injection information, simulates the action and logical operation of avionics system application program completely
Journey, produces corresponding IO and serial ports output, realizes the communication function of avionics system and input stimulus；
The hardware interface device is the in-kind portion in simulation software, is made of various types of I/O interfaces, it with it is real
System under test (SUT) connects, and is that test environment sends test data and receives the physical channel of test result data；
The data injection unit is used for use-case injection and two kinds of input modes of direct fault location by simulation software；
The Interface integration is directed to management platform on-line mode, and tester obtains in Cloud Server manage on the local computer
After the license of platform, by pre-configured enterprise's bus, data export/import operation can be carried out；
The communication network include avionics real-time computer with and platform management Ethernet and avionics real-time computer and seat
Reflective memory network between cabin/control simulation system.
2. avionics semi-matter simulating system according to claim 1, it is characterised in that the avionics real-time computer foundation
Before test, test when and test after three phases, be respectively completed herein below：
Before test：Simulation model needed for test is formed by Simulation Model Development instrument, while automatically generates respective code；By surveying
This implantation tool of training imports test script, and test script is generated by script compiler；With reference to management platform, by line and
Two ways obtains test input data under line；
Task management and the Real-Time Scheduling mechanism of whole test environment are provided during test by avionics real-time computer；By testing automatically
Control software, inputs various signals according to use-case step and encourages, realize real-time use-case function of injecting；Controlled by direct fault location soft
Part is soft with reference to the experience bag of expert's fault database, such as main display and control software failure bag, navigation management software fault bag and sensor management
Part failure bag etc., realizes the logic control input of failure；The test script of importing is parsed by test script resolver；It is imitative
Loading, transmission, collection and the display of data during true test；Test command is added by test monitoring panel in real time；According to reality
Real-time display is needed to specify data；Hard real time communication mechanism between real-time computer and system under test (SUT)；Driving simulation model is defeated
Go out data, system under test (SUT) is sent to by I/O drivings；Using the three-level management mechanism of project-engineering-test cell；Project pair
A model system is answered, multiple engineerings can be established below, each engineering corresponds to a crosslinked test environment model；Test is single
First result for each crosslinking environmental model preserves, it is achieved thereby that the preservation of each test scene and the multiplexing of test experience；
By the test result data being collected into after test run compared with expected results, analysis and playback, obtain testing whether to lead to
The conclusion crossed；
After test：Result data is imported from avionics real-time computer to management platform.
3. avionics semi-matter simulating system according to claim 2, it is characterised in that the real-time display specifies data
Mode is including such as tendency chart is shown, block diagram is shown, traffic light system.
4. avionics semi-matter simulating system according to claim 1, it is characterised in that the adapter is used for and pilot
Cockpit is connected with steerable system, is changed by A/D the manipulation signal of cockpit system being sent to avionics real-time computer, raw at the same time
Pilot block cabin system is passed it to by D/A or D/D into necessary avionics information.
5. avionics semi-matter simulating system according to claim 1, it is characterised in that the avionics information is believed including radar
Breath, sensor information.
6. avionics semi-matter simulating system according to claim 1, it is characterised in that the communication network further includes avionics
Hard real time communication mechanism between real-time computer and system under test (SUT).
7. avionics semi-matter simulating system according to claim 1, it is characterised in that the hardware interface device includes
1553B, CAN/AD, DA, RS232, RS422, RS485, DI, DO, RELAY, Ethernet, and user's custom interface.
8. avionics semi-matter simulating system according to claim 1, it is characterised in that the direct fault location crosses software pouring
Specific serial ports bag, each failure are uniquely determined by corresponding failure and occupy-place, sent through real-time computer to system under test (SUT)；
In combination with experience failure bag in experts database, parse corresponding failure title and provide the possible cause that corresponding failure produces,
Realize the verification to avionics system failure.
9. avionics semi-matter simulating system according to claim 8, it is characterised in that the use-case injection is noted by software
Enter specific interface data bag, the data content is signal ID and its original physics numerical quantity, through real-time computer according to
Respective algorithms parse being sent to induction signal, and by I/O hardware interfaces to system under test (SUT) for use-case input.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108873738A (en) * | 2018-08-06 | 2018-11-23 | 中国科学院长春光学精密机械与物理研究所 | Electronics pattern closed-loop simulation method |
| CN112581850A (en) * | 2019-09-27 | 2021-03-30 | 李晓华 | Virtual debugging system of multifunctional production line and equipment |
| CN112824229A (en) * | 2019-11-20 | 2021-05-21 | 中国商用飞机有限责任公司 | Avionics function test testing system |
| CN113219856A (en) * | 2021-04-25 | 2021-08-06 | 西北工业大学 | Virtual testing device and simulation method for civil aircraft airborne information system |
| CN113342693A (en) * | 2021-07-06 | 2021-09-03 | 阳光电源股份有限公司 | Test data generation method, device and system and controller |
| CN113448257A (en) * | 2021-06-01 | 2021-09-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Simulation test method and platform for avionics cabin display system |
| CN113534680A (en) * | 2021-07-20 | 2021-10-22 | 中航机载系统共性技术有限公司 | Adapter and hybrid test system based on ED-247 standard |
| CN115499321A (en) * | 2022-08-23 | 2022-12-20 | 成都飞机工业（集团）有限责任公司 | Design and implementation method of simulation test equipment signal switching system |
| CN115567564A (en) * | 2022-12-06 | 2023-01-03 | 东方空间(西安)宇航技术有限公司 | Testing method, device, system and equipment of aerospace equipment |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080220862A1 (en) * | 2007-03-06 | 2008-09-11 | Aiseek Ltd. | System and method for the generation of navigation graphs in real-time |
| CN201829074U (en) * | 2010-09-28 | 2011-05-11 | 北京赛四达科技股份有限公司 | Avionics simulation testing and training device |
| CN103760780A (en) * | 2014-02-17 | 2014-04-30 | 中国航空无线电电子研究所 | Universal simulation platform of cockpit display control system |
| CN103869707A (en) * | 2012-12-13 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Semi-physical simulation test system applied to commercial aero engine control system |
| CN104765681A (en) * | 2015-03-18 | 2015-07-08 | 株洲南车时代电气股份有限公司 | Automated train drive control software testing system and method |
-
2017
- 2017-12-15 CN CN201711345023.6A patent/CN107944193A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080220862A1 (en) * | 2007-03-06 | 2008-09-11 | Aiseek Ltd. | System and method for the generation of navigation graphs in real-time |
| CN201829074U (en) * | 2010-09-28 | 2011-05-11 | 北京赛四达科技股份有限公司 | Avionics simulation testing and training device |
| CN103869707A (en) * | 2012-12-13 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Semi-physical simulation test system applied to commercial aero engine control system |
| CN103760780A (en) * | 2014-02-17 | 2014-04-30 | 中国航空无线电电子研究所 | Universal simulation platform of cockpit display control system |
| CN104765681A (en) * | 2015-03-18 | 2015-07-08 | 株洲南车时代电气股份有限公司 | Automated train drive control software testing system and method |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108873738A (en) * | 2018-08-06 | 2018-11-23 | 中国科学院长春光学精密机械与物理研究所 | Electronics pattern closed-loop simulation method |
| CN112581850A (en) * | 2019-09-27 | 2021-03-30 | 李晓华 | Virtual debugging system of multifunctional production line and equipment |
| CN112824229B (en) * | 2019-11-20 | 2023-01-17 | 中国商用飞机有限责任公司 | Avionics function test testing system |
| CN112824229A (en) * | 2019-11-20 | 2021-05-21 | 中国商用飞机有限责任公司 | Avionics function test testing system |
| CN113219856A (en) * | 2021-04-25 | 2021-08-06 | 西北工业大学 | Virtual testing device and simulation method for civil aircraft airborne information system |
| CN113219856B (en) * | 2021-04-25 | 2022-09-09 | 西北工业大学 | Virtual testing device and simulation method for civil aircraft airborne information system |
| CN113448257A (en) * | 2021-06-01 | 2021-09-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Simulation test method and platform for avionics cabin display system |
| CN113342693A (en) * | 2021-07-06 | 2021-09-03 | 阳光电源股份有限公司 | Test data generation method, device and system and controller |
| CN113534680A (en) * | 2021-07-20 | 2021-10-22 | 中航机载系统共性技术有限公司 | Adapter and hybrid test system based on ED-247 standard |
| CN113534680B (en) * | 2021-07-20 | 2024-04-05 | 中航机载系统共性技术有限公司 | Adapter and hybrid test system based on ED-247 standard |
| CN115499321A (en) * | 2022-08-23 | 2022-12-20 | 成都飞机工业（集团）有限责任公司 | Design and implementation method of simulation test equipment signal switching system |
| CN115499321B (en) * | 2022-08-23 | 2023-12-08 | 成都飞机工业（集团）有限责任公司 | Design and implementation method of simulation test equipment signal switching system |
| CN115567564A (en) * | 2022-12-06 | 2023-01-03 | 东方空间(西安)宇航技术有限公司 | Testing method, device, system and equipment of aerospace equipment |
| CN115567564B (en) * | 2022-12-06 | 2023-09-08 | 东方空间(西安)宇航技术有限公司 | Method, device, system and equipment for testing aerospace equipment |
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