CN103116287A - Avionics equipment running environment dynamic simulating device and method - Google Patents
Avionics equipment running environment dynamic simulating device and method Download PDFInfo
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Abstract
The invention relates to an avionics equipment running environment dynamic simulating device and a method. A hardware system of the avionics equipment running environment dynamic simulating device comprises a left incentive system and a right incentive system. The left incentive system and the right incentive system are connected through the internet. Circuit structures of the left incentive system and the right incentive system are same. Each incentive system comprises an industrial personal computer. A software system generates a variety of data in flight process through controlling an AFDX card, an ARINC 429 card and a discrete input/output card, and outputs the data to member systems of the avionics equipment through a signal conditioning box and an interface mapping device. The data of the member systems of the avionics equipment are outputted through the interface mapping device and the signal conditioning box. Conclusion of the system operation can be obtained through simulation. The troubles of managing and analyzing a large amount of data when the avionics system is tested as a whole are avoided, time needed for testing is greatly shortened and data test errors caused by artificial analysis and data process are effectively reduced.
Description
Technical field
The present invention relates to a kind of environment simulator, particularly relate to a kind of Aerial Electronic Equipment running environment dynamic analog device and method.
Background technology
Avionics system is a type systematic requisite and important on modern aircarrier aircraft, and it mainly is responsible for the functions such as communication, navigation, flight control, flight management and demonstration on aircraft.When traditional aircarrier aircraft designs, only have housing construction design by the time complete, after avionics system is installed on aircraft, could carry out integration test to whole avionics system.Along with development and the avionics system importance aboard of electronic technology increases day by day, traditional method of testing can't satisfy the design requirement of present generation aircraft, thereby need to carry out global design and the lab investigation of avionics system in the housing construction design.The lab investigation stage need to the avionics system on aircraft under lab face set up, simultaneously in order to make collaborative work between system, the dynamic environment when needing simulated aircraft flight.
Between avionics system on aircraft, main ARINC429 bus and the AFDX bus transfer data of relying on, also have a large amount of discrete magnitudes to carry out the transmission of status data simultaneously.Aircraft is in flight course, these data need a large amount of exchanges, and need to assess the performance of system's operation according to the feedback data of each Member Systems, and there is no special Apparatus and method for for the exchange of this a large amount of ARINC429 data, AFDX data and discrete data and information analysis, management at present.
Summary of the invention
In order to address the above problem, the object of the present invention is to provide a kind of Aerial Electronic Equipment running environment dynamic analog device and method of exchange of a large amount of ARINC429 data, AFDX data and the discrete data for management, analysis of aircraft simulation practical flight process.
In order to achieve the above object, the present invention realizes by such technical scheme: Aerial Electronic Equipment running environment dynamic analog device, comprise hardware system and software systems, it is characterized in that, hardware system comprises a left excitation system and a right excitation system, connects by the internet between system;
The circuit structure of left excitation system and right excitation system is identical, each excitation system by industrial computer, be inserted in 3 16 passage ARINC429 cards in the industrial computer expansion slot, 2 32 discrete output cards of passage, 1 32 discrete input card of passage and 1 AFDX card and consist of;
Software systems are used for Environment Dynamic Simulation, comprise main control module, synchrodata buffer module, FMS system emulation module, OMS system emulation module, ADIRS system emulation module, demonstration and Control System Imitation module, surveillance emulation module and interface modular converter program in the industrial computer that operates in left and right excitation system, realize data analysis and processing capacity, control ARINC429 card, discrete output card and AFDX card by respective side industrial control computer mainboard pci bus, needed various signals when producing the Aerial Electronic Equipment operation with simulation;
The industrial computer of left and right excitation system nurses one's health case by left signal respectively and right signal conditioning case output terminal is connected to interface mappings device input end, finally is connected respectively to navigation arrangement or its emulation module, communications component or its emulation module, tuning block or its emulation module, monitoring component or its emulation module of left avionics system and right avionics system by interface mappings device output terminal;
ARINC429 bus data, discrete input data and the AFDX bus data of left and right avionics system output are via the interface mappings device, and be transferred to ARINC429 card, discrete input and AFDX card by signal regulating device, then receive by industrial computer, with analysis and the processing of carrying out data, then display analysis result on the display of correspondence, finally reach a conclusion; Left industrial computer and right industrial computer are realized synchronous and mutual control display information synchronous of data by Ethernet;
Described left signal conditioning case is identical with the circuit structure of right signal conditioning case, the interface of each signal process box by 3 DB78 connects 3 ARINC429 cartoon roads of corresponding excitation system, 2 discrete output card passages that connect corresponding excitation system by 2 DB78 interfaces, and the discrete input card passage that connects corresponding excitation system by 1 DB37 interface;
Signal process box is connected to the interface mappings device by two ZIF-156 interfaces with ARINC429 bus data, discrete output data and discrete input data respectively; Signal process box inside directly uses cable to be connected with between DB78 and DB37 interface and ZIF-156 interface, each signal process box provides altogether 3 * 16 passage * 4 tunnel=192 road ARINC429 data channel, 2 * 32 discrete output channels in passage * 1 tunnel=64 road, 1 * 32 discrete input channels in passage * 1 tunnel=32 road, these passages all are connected on the interface of two ZIF-156 via signal process box;
Described interface mappings device is connected with the ZIF-156 interface of left and right signal conditioning case respectively, and be connected with the AFDX cartoon road of left and right excitation system, be used for the ARINC429 data of Aerial Electronic Equipment operation state environment simulator, discrete inputoutput data and AFDX data are transmitted between excitation system and avionics system;
The interface mappings device can form situation according to the avionics system of different aircraft models, ARINC429 data in excitation system, discrete inputoutput data and AFDX data are connected respectively to left and right avionics system corresponding assembly or the emulation module that needs the corresponding data communication, these avionics system assemblies comprise navigation arrangement or emulation module, communications component or emulation module, tuning block or emulation module, monitoring component or emulation module; Like this, by changing the connected mode of interface mappings device, just can realize the dynamic similation to different Aerial Electronic Equipment running environment.
Utilize the running environment Dynamic Simulation Method of described Aerial Electronic Equipment running environment dynamic analog device, comprise the steps:
Step 1) generates aircraft flight management system produces in flight course all kinds of ARINC429 data, discrete data and AFDX data by left and right FMS system emulation module simulation, and processes all kinds of ARINC429 data, discrete data and the AFDX data that in flight course, flight management system receives;
Step 2) by left and right OMS system emulation module simulation aircraft in flight course and the airborne maintenance system function in the ground maintenance process, carry out the interaction process of service data;
Step 3) produces by left, center, right ADIRS system emulation module simulation the aircraft flight parameter information that aircraft atmosphere data and inertial navigation system in flight course produce;
Step 4) produces the control command of aircraft flight control system in flight course by left and right demonstration and Control System Imitation module simulation, and the corresponding data of processes and displays system and demonstration;
Step 5) produces by left and right surveillance emulation module simulation all kinds of unsafe condition parameters and the warning message that aircraft occurs in flight course;
Step 6), will be changed between AFDX data message and ARINC429 data message when the running environment dynamic similation mutually by left and right interface modular converter;
Step 7) is coordinated the work of FMS system emulation module, OMS system emulation module, ADIRS system emulation module, demonstration and Control System Imitation module, surveillance emulation module and interface modular converter by left and right main control module, and manages the data exchange process between them;
Step 8) is by the data message of FMS system emulation module, OMS system emulation module, ADIRS system emulation module, demonstration and Control System Imitation module, surveillance emulation module and interface modular converter in the left and right excitation system of synchrodata buffer module storage, and the synchronizing function of completing above-mentioned information in left and right excitation system.
Beneficial effect of the present invention: Aerial Electronic Equipment running environment dynamic analog device and method are to utilize industrial computer operation Aerial Electronic Equipment running environment dynamic similation program, produce various data in flight course by controlling AFDX card, ARINC429 card and discrete input-output card, and export to the Aerial Electronic Equipment of each Member Systems by signal process box and interface mappings device; Simultaneously the data of each Member Systems Aerial Electronic Equipment are transmitted via interface mappings device and signal process box, utilize AFDX card, ARINC429 card and discrete input-output card to carry out the collection of data, then the data that collect are carried out analysis, the processing of data by the Aerial Electronic Equipment running environment dynamic similation program in industrial computer, obtain the conclusion of system's operation.Can remove from like this when carrying out the avionics system integrated testability, need to manage and analyze the trouble of mass data, greatly shorten the test required time, the test mistake that minimizing is artificially analyzed effectively, deal with data causes.
Description of drawings
Fig. 1 is that Aerial Electronic Equipment running environment dynamic analog device provided by the invention consists of block diagram;
Fig. 2 is Aerial Electronic Equipment running environment dynamic simulation software system module figure provided by the invention.
In figure: 1. left excitation system shows, 2. left excitation system, and 3. left signal conditioning case, 4. right excitation system shows, 5. right excitation system, 6. right signal conditioning case, 7. interface mappings device, 8. left avionics system, 9. right avionics system.
Embodiment
Below in conjunction with the drawings and specific embodiments, Aerial Electronic Equipment running environment dynamic analog device provided by the invention and method are elaborated:
As shown in Figure 1, Aerial Electronic Equipment running environment dynamic analog device provided by the invention comprises: a left excitation system 2 and a right excitation system 5, for generation of the needed various signals of Aerial Electronic Equipment operation state simulation, the excitation system of each side is by industrial computer and be inserted in 3 16 passage ARINC429 cards of its cabinet inside, 2 32 discrete output cards of passage, 1 32 discrete input card of passage and 1 AFDX card and consist of.left, right industrial computer is used for the main control module of running environment dynamic simulation software system, the synchrodata buffer module, FMS system emulation module, OMS system emulation module, ADIRS system emulation module, show and the Control System Imitation module, surveillance emulation module and interface modular converter, realize data analysis and processing capacity, it controls the ARINC429 card by pci bus in the respective side machine, discrete output card and AFDX card, needed various signals when producing the Aerial Electronic Equipment operation with simulation, and nurse one's health case 3 and right signal conditioning case 6 by left signal and output to interface mappings device 7, finally export to corresponding assembly or the emulation module of left avionics system 8 and right avionics system 9, ARINC429 bus data, discrete input data and the AFDX bus data of left and right avionics system output are via the interface mappings device, and be transferred to ARINC429 card, discrete input and AFDX card by signal regulating device, then receive by industrial computer, with analysis and the processing of carrying out data, then display analysis result on the display of correspondence, finally reach a conclusion, left industrial computer and right industrial computer carry out synchronous and mutual control display information synchronous of data by Ethernet,
Left signal conditioning case 3 and a right signal conditioning case 6, each signal process box interface by 3 DB78 connect corresponding excitation system 3 ARINC429 cartoon roads, connect 2 discrete output card passages of corresponding excitation systems and the discrete input card passage that connects corresponding excitation system by 1 DB37 interface by 2 DB78 interfaces; Signal process box is connected to interface mappings device 7 by two ZIF-156 interfaces with ARINC429 bus data, discrete output data and discrete input data respectively; Signal process box inside directly uses cable to be connected with between DB78 and DB37 interface and ZIF-156 interface, each signal process box provides altogether 3 * 16 passage * 4 tunnel=192 road ARINC429 data channel, 2 * 32 discrete output channels in passage * 1 tunnel=64 road, 1 * 32 discrete input channels in passage * 1 tunnel=32 road, these passages all are connected on the interface of two ZIF-156 via signal process box;
An interface mappings device 7, be connected with the ZIF-156 interface of left and right signal conditioning case, and be connected with the AFDX cartoon road of left and right excitation system, be used for the ARINC429 data of Aerial Electronic Equipment operation state environment simulator, discrete inputoutput data and AFDX data are transmitted between excitation system and avionics system; The interface mappings device can form situation according to the avionics system of different aircraft models, ARINC429 data in excitation system, discrete inputoutput data and AFDX data are connected respectively to need the Member Systems of corresponding data communication assembly or emulation module, these Member Systems comprise navigation arrangement or emulation module, communications component or emulation module, tuning block or emulation module, monitoring component or emulation module; Like this, by changing the connected mode of interface mappings device 7, just can realize the dynamic similation to different Aerial Electronic Equipment running environment.
When the user need to simulate Aerial Electronic Equipment dynamic operation environment, at first the Aerial Electronic Equipment with each Member Systems was connected with Aerial Electronic Equipment running environment dynamic analog device provided by the invention, then opened industrial computer operation Aerial Electronic Equipment running environment dynamic similation program.What at first carry out is equipment self-inspection, and self check is used for checking whether analogue means exists fault, only just can carry out following dynamic similation work in the situation that analogue means itself is no problem.When the work of running environment dynamic similation is carried out, dynamic similation programmed control AFDX integrated circuit board, ARINC429 integrated circuit board and discrete I/O integrated circuit board carry out input, the output function of data, and utilize the dynamic similation program to carry out the analyzing and processing of data, the effect that obtains simulating, thus the avionics system integrated testability completed.
As shown in Figure 2, utilize the running environment dynamic simulation software system of Aerial Electronic Equipment running environment dynamic analog device that the invention described above provides to comprise following functional module:
(1) left and right FMS system emulation module: be used for simulation and generate all kinds of ARINC429 data, discrete data and the AFDX data that aircraft produces at the flight course flight management system, and process all kinds of ARINC429 data, discrete data and AFDX data that in flight course, flight management system receives.These data comprise the hands-off tuning frequency of navigation arrangement or navigation arrangement emulation module, FMS system emulation module is according to current aircraft location, choose available guidance station from its database, and the guidance station frequency of operation is sent to this side navigation arrangement or emulation module; If get the manufal tuning state by discrete input port, will receive the tuning information that comes from this side tuning block or tuning block emulation module, and send it to this side navigation arrangement or emulation module; If get mutual tuning state by discrete input port, will receive the tuning information that comes from heteropleural synchrodata buffer zone, these tuning informations can be from heteropleural FMS system emulation module, also can be from heteropleural tuning block or tuning block emulation module, the tuning information that then will come from heteropleural sends to this side navigation arrangement or emulation module.The data that FMS system emulation module receives comprise that aircraft arrives relative angle information, localizer runout information and the glide path runout information of aircraft in closely advancing process of range information, aircraft and the guidance station of guidance station, and these information all come from navigation arrangement or navigation arrangement emulation module; Utilize these information and in conjunction with the positional information of guidance station in FMS system emulation module database, calculate the position of current aircraft, then the aircraft position is used for choosing guidance station, also offer aobvious control system and surveillance simultaneously.
(2) left and right OMS system emulation module: be used for the airborne maintenance system function of simulated aircraft in flight course and ground maintenance process, carry out the interaction process of service data.In flight course, OMS system emulation module can constantly be monitored the working condition of navigation in avionics system, communication, tuning and monitoring component or its emulation module, if a certain assembly breaks down, failure message is offered aobvious control system; When the ground maintenance state, OMS system emulation module can be sent the self-test instruction, starts the self check of navigation in avionics system, communication, tuning and monitoring component or its emulation module, and obtains self-detection result, then self check information is offered aobvious control system; Simultaneously, during the ground maintenance state, OMS system emulation module can also be sent the order of reading the historical failure data that record in navigation in avionics system, communication, tuning and monitoring component or its emulation module, obtain the historical failure data of maximum 64 flight legs, then these data are offered aobvious control system.Above-mentioned OMS system emulation functions of modules all can be completed by ARINC429 data bus or AFDX data bus the transmission of data.
(3) left, center, right ADIRS system emulation module: be used for simulation and produce aircraft at the aircraft flight parameter information of flight course atmosphere data and inertial navigation system generation, these flight parameters comprise the angle of pitch, roll angle, driftage, air speed, ground velocity, barometer altitude, inertia height, barometer altitude rate of change, the Inertial Vertica1 Speed of aircraft, the generation of these parameters produces according to atmosphere data and the law of inertia, by the ARINC429 data bus, these information outputs is used to the monitoring component in avionics system or its emulation module simultaneously.
(4) left and right demonstration and Control System Imitation module: be used for simulation and produce aircraft in the control command of flight course flight control system, and the corresponding data of processes and displays system and demonstration.The control command of flight control system comprises that course maintenance, highly maintenance, speed keep, and the demonstration of vertical channel flight director and the demonstration that depart from the navigation channel, horizontal channel are completed in the aircraft position that utilizes FMS system emulation module to obtain.
(5) left and right surveillance emulation module: be used for simulation and produce all kinds of unsafe condition parameters and the warning message that aircraft occurs at flight course.The flight parameter that utilizes ADIRS system emulation module to provide, and the unsafe condition parameter of storing in surveillance emulation module database are compared both, if flight parameter surpasses the thresholding of unsafe condition parameter, produce warning message output; Otherwise the output aircraft state is normal.
(6) left and right interface modular converter: be used for mutually to change between AFDX data message and ARINC429 data message when the running environment dynamic similation;
(7) left and right main control module: be used for coordinating the work of FMS system emulation module, OMS system emulation module, ADIRS system emulation module, demonstration and Control System Imitation module, surveillance emulation module and interface modular converter, and manage the data exchange process between them;
(8) synchrodata buffer module: be used for storing the data message of left and right excitation system FMS system emulation module, OMS system emulation module, ADIRS system emulation module, demonstration and Control System Imitation module, surveillance emulation module and interface modular converter, and the synchronizing function of completing above-mentioned information in left and right excitation system.
Can reproduce the present invention in conjunction with professional knowledge according to the above description.
Claims (2)
1.
A kind ofAerial Electronic Equipment running environment dynamic analog device comprises hardware system and software systems, it is characterized in that, hardware system comprises a left excitation system (2) and a right excitation system (5), connects by the internet between system;
Left excitation system (2) is identical with the circuit structure of right excitation system (5), each excitation system by industrial computer, be inserted in 3 16 passage ARINC429 cards in the industrial computer expansion slot, 2 32 discrete output cards of passage, 1 32 discrete input card of passage and 1 AFDX card and consist of;
Software systems are used for Environment Dynamic Simulation, comprise main control module, synchrodata buffer module, FMS system emulation module, OMS system emulation module, ADIRS system emulation module, demonstration and Control System Imitation module, surveillance emulation module and interface modular converter program in the industrial computer that operates in left and right excitation system, realize data analysis and processing capacity, control ARINC429 card, discrete output card and AFDX card by respective side industrial control computer mainboard pci bus, needed various signals when producing the Aerial Electronic Equipment operation with simulation;
The industrial computer of left and right excitation system nurses one's health case (3) by left signal respectively and right signal conditioning case (6) output terminal is connected to interface mappings device (7) input end, finally is connected respectively to navigation arrangement or its emulation module, communications component or its emulation module, tuning block or its emulation module, monitoring component or its emulation module of left avionics system (8) and right avionics system (9) by interface mappings device (7) output terminal;
ARINC429 bus data, discrete input data and the AFDX bus data of left and right avionics system output are via the interface mappings device, and be transferred to ARINC429 card, discrete input and AFDX card by signal regulating device, then receive by industrial computer, with analysis and the processing of carrying out data, then display analysis result on the display of correspondence, finally reach a conclusion; Left industrial computer and right industrial computer are realized synchronous and mutual control display information synchronous of data by Ethernet;
Described left signal conditioning case (3) is identical with the circuit structure of right signal conditioning case (6), the interface of each signal process box by 3 DB78 connects 3 ARINC429 cartoon roads of corresponding excitation system, 2 discrete output card passages that connect corresponding excitation system by 2 DB78 interfaces, and the discrete input card passage that connects corresponding excitation system by 1 DB37 interface;
Signal process box is connected to interface mappings device (7) by two ZIF-156 interfaces with ARINC429 bus data, discrete output data and discrete input data respectively; Signal process box inside directly uses cable to be connected with between DB78 and DB37 interface and ZIF-156 interface, each signal process box provides altogether 3 * 16 passage * 4 tunnel=192 road ARINC429 data channel, 2 * 32 discrete output channels in passage * 1 tunnel=64 road, 1 * 32 discrete input channels in passage * 1 tunnel=32 road, these passages all are connected on the interface of two ZIF-156 via signal process box;
Described interface mappings device (7) is connected with the ZIF-156 interface of left and right signal conditioning case respectively, and be connected with the AFDX cartoon road of left and right excitation system, be used for the ARINC429 data of Aerial Electronic Equipment operation state environment simulator, discrete inputoutput data and AFDX data are transmitted between excitation system and avionics system;
Interface mappings device (7) can form situation according to the avionics system of different aircraft models, ARINC429 data in excitation system, discrete inputoutput data and AFDX data are connected respectively to left and right avionics system corresponding assembly or the emulation module that needs the corresponding data communication, these avionics system assemblies comprise navigation arrangement or emulation module, communications component or emulation module, tuning block or emulation module, monitoring component or emulation module; Like this, by changing the connected mode of interface mappings device (7), just can realize the dynamic similation to different Aerial Electronic Equipment running environment.
2. utilize the running environment of the described Aerial Electronic Equipment running environment of claim 1 dynamic analog device to carry out Dynamic Simulation Method, it is characterized in that, comprise the steps:
Step 1) generates aircraft flight management system produces in flight course all kinds of ARINC429 data, discrete data and AFDX data by left and right FMS system emulation module simulation, and processes all kinds of ARINC429 data, discrete data and the AFDX data that in flight course, flight management system receives;
Step 2) by left and right OMS system emulation module simulation aircraft in flight course and the airborne maintenance system function in the ground maintenance process, carry out the interaction process of service data;
Step 3) produces by left, center, right ADIRS system emulation module simulation the aircraft flight parameter information that aircraft atmosphere data and inertial navigation system in flight course produce;
Step 4) produces the control command of aircraft flight control system in flight course by left and right demonstration and Control System Imitation module simulation, and the corresponding data of processes and displays system and demonstration;
Step 5) produces by left and right surveillance emulation module simulation all kinds of unsafe condition parameters and the warning message that aircraft occurs in flight course;
Step 6), will be changed between AFDX data message and ARINC429 data message when the running environment dynamic similation mutually by left and right interface modular converter;
Step 7) is coordinated the work of FMS system emulation module, OMS system emulation module, ADIRS system emulation module, demonstration and Control System Imitation module, surveillance emulation module and interface modular converter by left and right main control module, and manages the data exchange process between them;
Step 8) is by the data message of FMS system emulation module, OMS system emulation module, ADIRS system emulation module, demonstration and Control System Imitation module, surveillance emulation module and interface modular converter in the left and right excitation system of synchrodata buffer module storage, and the synchronizing function of completing above-mentioned information in left and right excitation system.
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| CN103760439B (en) * | 2013-09-24 | 2016-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of Auto-Test System of avionics system |
| CN103760439A (en) * | 2013-09-24 | 2014-04-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Automatic test system of avionic system |
| CN105653346B (en) * | 2014-11-19 | 2019-01-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of general driver frame design method assisting avionics software development |
| CN105653346A (en) * | 2014-11-19 | 2016-06-08 | 中国航空工业集团公司西安飞机设计研究所 | Universal exciter frame design method for assisting avionics software development |
| CN106054663A (en) * | 2016-03-21 | 2016-10-26 | 南京航空航天大学 | Design method of power electronic device dynamic simulation system |
| CN106054663B (en) * | 2016-03-21 | 2020-05-12 | 南京航空航天大学 | Design method of dynamic simulation system of power electronic device |
| CN106325262A (en) * | 2016-10-11 | 2017-01-11 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Interface data generation system and method of member system and onboard maintenance system |
| CN106325262B (en) * | 2016-10-11 | 2018-08-14 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of interface data generation system and method for Member Systems and onboard maintenance system |
| CN106598032B (en) * | 2016-12-28 | 2019-05-14 | 中国航空工业集团公司西安飞机设计研究所 | A kind of test macro of automatic flight control system |
| CN106598032A (en) * | 2016-12-28 | 2017-04-26 | 中国航空工业集团公司西安飞机设计研究所 | Test system of automatic flight control system |
| CN109033522A (en) * | 2018-06-25 | 2018-12-18 | 中国民航大学 | More electricity aircraft electrical route interacted system cabling scenarios assess device and method |
| CN109033522B (en) * | 2018-06-25 | 2023-04-18 | 中国民航大学 | Device and method for evaluating wiring scheme of multi-electric-aircraft electric circuit interconnection system |
| CN109743241A (en) * | 2018-12-26 | 2019-05-10 | 中国民航大学 | A kind of long-range aeronautical data bus switch equipment based on high-performance processor |
| 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 |
| 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 |
| CN112737872A (en) * | 2020-12-11 | 2021-04-30 | 中国航空工业集团公司西安航空计算技术研究所 | ARINC664P7 end system cross-network testing system and method |
| CN112737872B (en) * | 2020-12-11 | 2022-07-26 | 中国航空工业集团公司西安航空计算技术研究所 | ARINC664P7 end system cross-network testing system and method |
| CN112612297A (en) * | 2020-12-29 | 2021-04-06 | 中国民航大学 | Airworthiness verification system and method for civil aircraft automatic flight control system |
| CN114006951A (en) * | 2021-10-25 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Aircraft data transferring method and device |
| 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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