CN112073278A - Airborne electromechanical integrated management system - Google Patents
Airborne electromechanical integrated management system Download PDFInfo
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- CN112073278A CN112073278A CN202010861193.5A CN202010861193A CN112073278A CN 112073278 A CN112073278 A CN 112073278A CN 202010861193 A CN202010861193 A CN 202010861193A CN 112073278 A CN112073278 A CN 112073278A
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L2012/40267—Bus for use in transportation systems
- H04L2012/4028—Bus for use in transportation systems the transportation system being an aircraft
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Abstract
The application provides an airborne electromechanical integrated management system, it includes: a first remote interface unit and a second remote interface unit; a first electromechanical integrated management computer and a second electromechanical integrated management computer; the first remote interface unit and the second remote interface unit which are arranged in parallel carry out data interaction with a first electromechanical comprehensive management computer and a second electromechanical comprehensive management computer which are arranged in parallel through a first bus, the remote interface units are connected through a second bus to realize data interaction, and the electromechanical comprehensive management computers are also connected through the second bus to realize data interaction; the first electromechanical comprehensive management computer and the second electromechanical comprehensive management computer perform data interaction with the avionic system through the first bus, wherein when the first electromechanical comprehensive management computer and the second electromechanical comprehensive management computer perform data interaction with the avionic system, at most one electromechanical comprehensive management computer performs data interaction with the avionic system.
Description
Technical Field
The application belongs to the technical field of aviation electromechanics, and particularly relates to an airborne electromechanical comprehensive management system.
Background
At present, electromechanical systems adopted by a traditional aircraft in the prior art are all independently developed, the degree of integration among the electromechanical systems is low, each electromechanical system is provided with an independent controller, the control mode and the control method are messy and complex, and the electromechanical systems are large in size and weight and poor in fault tolerance and reconstruction capability; for important and critical controlled systems, once the controller fails, the controller cannot continue to work normally, which seriously affects the reliability of the electromechanical system and even the flight safety of the airplane.
Disclosure of Invention
It is an object of the present application to provide an onboard electromechanical integrated management system to address or mitigate at least one of the problems of the background art.
The technical scheme of the application is as follows: an airborne electromechanical integrated management system, comprising:
a first remote interface unit and a second remote interface unit, the first and second remote interface units accessing a first set of electromechanical systems that are at least partially identical;
the system comprises a first electromechanical comprehensive management computer and a second electromechanical comprehensive management computer, wherein the first electromechanical comprehensive management computer and the second electromechanical comprehensive management computer are accessed to a second electromechanical system set which is at least partially the same;
the first remote interface unit and the second remote interface unit which are arranged in parallel carry out data interaction with a first electromechanical integrated management computer and a second electromechanical integrated management computer which are arranged in parallel through a first bus, the first remote interface unit and the second remote interface unit are connected through a second bus to realize data interaction, and the first electromechanical integrated management computer and the second electromechanical integrated management computer are connected through the second bus to realize data interaction;
the first electromechanical comprehensive management computer and the second electromechanical comprehensive management computer perform data interaction with the avionic system through the first bus, wherein when the first electromechanical comprehensive management computer and the second electromechanical comprehensive management computer perform data interaction with the avionic system, at most one electromechanical comprehensive management computer performs data interaction with the avionic system.
In the application, when any one of the first remote interface unit or the second remote interface unit fails to communicate with the first bus, the first remote interface unit and the second remote interface unit realize data backup through the second bus and then transmit the data to the electromechanical integrated management computer which communicates with the avionic system through the other remote interface unit which does not have communication failure.
In the present application, when a second bus communication between a first remote interface unit and a second remote interface unit fails, both the first remote interface unit and the second remote interface unit transmit data to an electromechanical integrated management computer in communication with an avionics system via a first bus.
In the application, when any one of the first electromechanical integrated management computer and the second electromechanical integrated management computer fails to communicate with the avionic system through the first bus, the first electromechanical integrated management computer and the second electromechanical integrated management computer realize data backup through the first bus or the second bus.
In the application, when any one of the first and second mechatronic integrated management computers fails to communicate with the remote interface unit through the first bus, the first and second mechatronic integrated management computers implement data backup through the second bus.
In the present application, when a second bus communication between the first electromechanical integrated management computer and the second electromechanical integrated management computer fails, the first electromechanical integrated management computer and the second electromechanical integrated management computer implement data backup through the first bus.
In this application, the first bus and the second bus are different types of buses.
In this application, the first bus is GJB 289A.
In this application, the second bus is a CCDL bus.
According to the airborne electromechanical integrated management system, the first and second buses are arranged between the two remote interface units and the two electromechanical integrated management computers, so that data can be backed up and uploaded when any unit or computer fails, and the fault tolerance of the electromechanical integrated management system is improved.
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 onboard electromechanical integrated management system according to the present application.
Fig. 2 is a schematic diagram of an electromechanical system set accessed by the onboard electromechanical integrated management system in the present application.
Fig. 3 is a schematic diagram illustrating a failure of the first bus communication between the second electromechanical integrated management computer and the avionics system according to an embodiment of the present application.
Fig. 4 is a schematic diagram illustrating a first bus communication failure between a first mechatronic integrated management computer and an avionics system according to an embodiment of the present application.
Fig. 5 is a schematic diagram illustrating a failure of a first bus communication between a first mechatronic integrated management computer and a remote interface unit according to an embodiment of the present application.
Fig. 6 is a schematic diagram of a first bus communication failure between a second mechatronic integrated management computer and a remote interface unit according to an embodiment of the present application.
Fig. 7 is a schematic diagram illustrating a second bus communication failure between the first mechatronic management computer and the first mechatronic management computer according to an embodiment of the present application.
Fig. 8 is a schematic diagram illustrating a failure of the first bus communication between the first interface unit and the electromechanical integrated management computer according to an embodiment of the present application.
Fig. 9 is a schematic diagram of a failure of the first bus communication between the second interface unit and the electromechanical integrated management computer according to an embodiment of the present application.
Fig. 10 is a schematic diagram illustrating a second bus communication failure between a first interface unit and a second interface unit according to an embodiment of 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.
In order to implement fault detection and report on a plurality of electromechanical systems, the application provides a bus-based airborne electromechanical integrated management system (UMS) for implementing monitoring, control and management of electromechanical systems.
As shown in fig. 1 and fig. 2, the onboard electromechanical integrated management system 10 provided in the present application mainly includes two electromechanical integrated management computers 11/12 (UMC) and two remote interface units 13/14 (RIU), where the two electromechanical integrated management computers UMC and the remote interface units RIU are connected to each electromechanical subsystem in a near-by manner, so as to reduce the length and weight of the cable and reduce the difficulty of cable installation.
The first remote interface unit 13 and the first remote interface unit 14 are connected to a part of electromechanical subsystems in the aircraft, where the part of electromechanical subsystems includes a power device system (an engine comprehensive adjusting machine, an engine automatic starting device), a hydraulic system (a pressure sensor, a temperature sensor), a fire alarm system (a fire sensor, etc.), and the like. The electromechanical subsystems may form a first set of electromechanical subsystems.
It should be noted that the first remote interface unit 13 and the first remote interface unit 14 are usually in a backup relationship with each other, and thus in the embodiment shown in fig. 2, the electromechanical subsystems are the same, but different electromechanical subsystems may be connected to the first remote interface unit 13 and the first remote interface unit 14. In the case that the first remote interface unit 13 and the first remote interface unit 14 are connected to different electromechanical subsystems, mutual backup can still be achieved by using the electromechanical integrated management system of the present application. In the embodiments described hereinafter, it will be explained that the first remote interface unit 13 and the first remote interface unit 14 are connected to the same electromechanical subsystem.
The first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 are also connected to a part of electromechanical subsystems in the aircraft, and the electromechanical subsystems include a pneumatic system (pressure sensor), a brake system (wheel speed sensor, command sensor, brake pressure sensor), a power supply system (direct current power distribution device, alternating current power distribution device, storage battery, etc.), an environmental control system (temperature relay, pressure annunciator, electromagnetic valve, etc.), a fuel system (differential pressure sensor, end position switch, fuel controller, etc.), and the like. The electromechanical subsystems may form a second set of electromechanical subsystems.
It should be noted that the first mechatronic management computer 11 and the second mechatronic management computer 12 are usually in a backup relationship with each other, and therefore in the embodiment shown in fig. 2, the connected electromechanical subsystems are the same, but different electromechanical subsystems may be connected to the first mechatronic management computer 11 and the second mechatronic management computer 12. Under the condition that the first electromechanical comprehensive management computer 11 and the second electromechanical comprehensive management computer 12 are connected with different electromechanical subsystems, mutual backup can still be realized by adopting the electromechanical comprehensive management system. In the following embodiments, the description will be made by connecting the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 to the same electromechanical subsystem.
The first remote interface unit 13 and the second remote interface unit 14 are arranged in parallel and are connected to a first electromechanical integrated management computer and a second electromechanical integrated management computer which are arranged in parallel through a first bus, the two remote interface units 13/14 and the two electromechanical integrated management computers 11/12 can perform data interaction pairwise through the first bus, meanwhile, the first remote interface unit 13 and the second remote interface unit 14 are connected through a second bus to achieve data interaction, and the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 are also connected through a second bus 16 to achieve data interaction.
The first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 perform data interaction with the avionic system 20 through the first bus 15, and when the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 perform data interaction with the avionic system 20, at most one electromechanical integrated management computer performs data interaction with the avionic system 20.
The electromechanical integrated management system 10 is based on a control strategy of distributed acquisition, centralized calculation and distributed output, is internally provided with two UMCs and two RIUs, has the same structure and is backed up through a second bus, and has a system structure of different structures and communicating through a first bus, and carries out data interaction with an avionic system through the first bus, so that the nearby acquisition, output and centralized calculation of the electromechanical system are finally realized.
In the application, a redundancy backup strategy is adopted for a node machine (UMC or RIU) collected by an electromechanical system, so that the identification error or mistake of a fault can be reduced.
Specifically, input comparison monitoring and output comparison monitoring are respectively performed in the UMC. The input comparison monitoring is to compare and monitor an external input signal and to compare and monitor an analog input signal by using a threshold; the discrete magnitude input signal is monitored by consistent comparison. Before input comparison monitoring, synchronization between two channels is carried out, information acquisition is carried out after synchronization, and cross data comparison is carried out. If the comparison result is consistent, data processing is carried out; if the comparison results are not consistent, the two node machines carry out self-detection and obtain the data of the correct interface of the test result; and if the faults are not detected or detected, switching to the safety mode. The output comparison monitoring is to compare and monitor the calculation results of each node machine, and self-monitoring software and hardware circuits are designed on each node machine to complete the monitoring and management of the system resources, so that only one channel is output and controlled at any time when the dual-channel control is carried out.
In the present application, the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 form a dual-channel communication interface with the avionic system 20 through the first bus 15, but the first electromechanical integrated management computer 11 or the second electromechanical integrated management computer 12 having only one node at any time communicates with the avionic system 20 through a bus in an RT (remote terminal) manner, so as to ensure information transmission between the electromechanical integrated management system 10 and the avionic system 20. Meanwhile, two buses are also adopted in the electromechanical integrated management system 20 to realize data exchange among the four node machines, that is, the electromechanical integrated management computer and the remote interface unit communicate with each other through the first bus, and the same structure communicates with each other through the second bus, so that data can still be interacted and uploaded when any one of the same structures has a communication fault.
The redundancy strategy of the electromechanical integrated management system is as follows:
strategy 1: as shown in fig. 3, when the communication interfaces between the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 and the avionics system 20 are normal, the first electromechanical integrated management computer 11 is usually used as a normal machine, the first electromechanical integrated management computer 11 realizes information transmission with the avionics system 20 in an RT manner, and the second electromechanical integrated management system 12 is used as a standby machine. Meanwhile, the first electromechanical integrated management computer 11 serves as a BC of a bus in the electromechanical integrated management system 10, sends avionic information to be received to each node machine (the second electromechanical integrated management system 12, the first remote interface unit 13, and the first remote interface unit 14), collects information of the electromechanical subsystems of each node machine, such as states, faults, maintenance and the like, and uploads the information to the avionic system 20.
In the process of collecting the electromechanical system states of the node machines, the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 may perform data transmission via a first bus or may perform data transmission via a second bus, and the first remote interface unit 13 and the second remote interface unit 14 may perform data backup via the second bus or may perform data transmission to the first electromechanical integrated management computer 11 via the first bus, respectively.
Strategy 2: as shown in fig. 4, when a communication channel needs to be reconfigured when the first integrated electromechanical management computer 11 and the avionics system 20 have a communication failure, the second integrated electromechanical management computer 12 is switched to an RT mode to communicate with the avionics system 20, and meanwhile, a bus controller in the integrated electromechanical management system is switched from the first integrated electromechanical management computer 11 to the second integrated electromechanical management computer 12, and the second integrated electromechanical management computer 12 sends avionic information to be received to each node (the first integrated electromechanical management system 11, the first remote interface unit 13, and the first remote interface unit 14), collects information of electromechanical system states, failures, maintenance, and the like of each node, and uploads the information to the avionics system 20.
In the process of collecting the electromechanical system states of the node machines, the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 may perform data transmission via a first bus or may perform data transmission via a second bus, and the first remote interface unit 13 and the second remote interface unit 14 may perform data backup via the second bus or may perform data transmission to the second electromechanical integrated management computer 11 via the first bus, respectively.
Strategy 3: when the second electromechanical integrated management computer 12 and the avionics system 20 have a communication failure, since the second electromechanical integrated management computer 12 is generally used as a standby machine, the communication process is the same as the strategy 1 shown in fig. 3, and details are not described herein.
Strategy 4: as shown in fig. 5, when the first bus communication between the first mechatronic management computer 11 and the remote interface unit fails, the communication channel is reconfigured. The second electromechanical integrated management computer 12 is switched to an RT mode to communicate with the avionic system 20, and meanwhile, the bus controller in the electromechanical integrated management system is switched from the first electromechanical integrated management computer 11 to the second electromechanical integrated management computer 12, and the second electromechanical integrated management computer 12 sends avionic information to be received to each node computer (the first electromechanical integrated management system 11, the first remote interface unit 13, and the first remote interface unit 14), collects information of electromechanical system states, faults, maintenance and the like of each node computer, and uploads the avionic system 20.
In the process of collecting the electromechanical system states of the node machines, the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 perform data transmission backup through the second bus, the first remote interface unit 13 and the second remote interface unit 14 may perform data backup through the second bus, or may perform data transmission to the second electromechanical integrated management computer 12 through the first bus, respectively.
Strategy 5: as shown in fig. 6, when the second electromechanical integrated management computer 12 and the first bus of the remote interface unit have a communication failure, the communication channel is reconfigured, the first electromechanical integrated management computer 11 communicates with the avionic system 20 in an RT manner, and simultaneously the bus controller in the electromechanical integrated management system is switched to the first electromechanical integrated management computer 11, and the first electromechanical integrated management computer 11 sends avionic information to be received to each node (the second electromechanical integrated management system 12, the first remote interface unit 13, and the first remote interface unit 14), collects information of electromechanical system state, failure, maintenance, and the like of each node, and uploads the avionic system 20.
In the process of collecting the electromechanical system states of the node machines, data transmission backup is performed between the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 through the second bus, data backup may be performed between the first remote interface unit 13 and the second remote interface unit 14 through the second bus, and data transmission may also be performed to the first electromechanical integrated management computer 11 through the first bus, respectively.
Strategy 6: as shown in fig. 7, when a second bus communication fault occurs between the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12, the communication channel is reconfigured, the first electromechanical integrated management computer 11 communicates with the avionic system 20 in an RT manner, and simultaneously the bus controller in the electromechanical integrated management system is switched to the first electromechanical integrated management computer 11, and the first electromechanical integrated management computer 11 sends avionic information to be received to each node (the second electromechanical integrated management system 12, the first remote interface unit 13, and the first remote interface unit 14), collects information of electromechanical system states, faults, maintenance, and the like of each node, and uploads the avionic system 20.
In the process of collecting the electromechanical system states of the node machines, data transmission backup is performed between the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 through a first bus, data backup may be performed between the first remote interface unit 13 and the second remote interface unit 14 through a second bus, and data transmission may also be performed to the first electromechanical integrated management computer 11 through the first bus, respectively.
Strategy 7: as shown in fig. 8, when the first bus communication of the first remote interface unit 13 fails, the communication channel is reconfigured, the first integrated management computer 11 communicates with the avionics system 20 in an RT manner, and at the same time, the first integrated management computer 11 sends avionics information to be received to each node (the second integrated management computer 12, the first remote interface unit 13, and the first remote interface unit 14), collects information of the electromechanical system state, failure, maintenance, and the like of each node, and uploads the avionics system 20.
In the process of collecting the electromechanical system states of the node machines, the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 may perform data transmission backup through a first bus or perform data communication through a second bus, and after performing data backup through the second bus between the first remote interface unit 13 and the second remote interface unit 14, the second remote interface unit 14 performs data transmission to the first electromechanical integrated management computer 11 through the first bus.
Strategy 8: as shown in fig. 9, when the first bus communication of the second remote interface unit 14 fails, the communication channel is reconfigured, the first integrated management computer 11 communicates with the avionics system 20 in an RT manner, and at the same time, the first integrated management computer 11 sends avionics information to be received to each node (the second integrated management computer 12, the first remote interface unit 13, and the first remote interface unit 14), collects information of the electromechanical system state, failure, maintenance, and the like of each node, and uploads the avionics system 20.
In the process of collecting the electromechanical system states of the node machines, the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 may perform data transmission backup through the first bus, or may perform data communication through the second bus, and after performing data backup through the first bus between the first remote interface unit 13 and the second remote interface unit 14, the first remote interface unit 14 performs data transmission to the first electromechanical integrated management computer 11 through the first bus.
Strategy 9: as shown in fig. 10, when the second bus communication between the first remote interface unit 13 and the second remote interface unit 14 fails, the communication channel is reconfigured, the first mechatronic integrated management computer 11 communicates with the avionic system 20 in an RT manner, and at the same time, the first mechatronic integrated management computer 11 sends avionic information to be received to each node machine (the second mechatronic integrated management system 12, the first remote interface unit 13, and the first remote interface unit 14), collects information of the mechatronic system state, failure, maintenance, and the like of each node machine, and uploads the avionic system 20.
In the process of collecting the electromechanical system states of the node machines, the first electromechanical integrated management computer 11 and the second electromechanical integrated management computer 12 may perform data transmission backup through the first bus, or may perform data communication through the second bus, and both the first remote interface unit 13 and the second remote interface unit 14 perform data transmission to the first electromechanical integrated management computer 11 through the first bus.
In some embodiments of the present application, the first bus may be a GBJ289A bus, and the second bus may be a CCDL (cross channel data link) bus.
The bus-based airborne electromechanical integrated management system can realize fault tolerance and reconfiguration under the condition that components and cables are hardly added, not only can the integrated control, management and fault monitoring of an aircraft electromechanical system be realized, the whole electromechanical system is taken as a control and management object, the electromechanical system architecture is optimized, the electromechanical system control management capability is improved, meanwhile, both a node machine and a bus of the electromechanical integrated management system have redundancy, and when the electromechanical integrated management system has a fault, the electromechanical subsystem can still be ensured to normally work through fault tolerance and reconfiguration management for important or key electromechanical subsystems, and the safety of the aircraft 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 (9)
1. An airborne electromechanical integrated management system, characterized in that the airborne electromechanical integrated management system comprises:
a first remote interface unit and a second remote interface unit, the first and second remote interface units accessing a first set of electromechanical systems that are at least partially identical;
the system comprises a first electromechanical comprehensive management computer and a second electromechanical comprehensive management computer, wherein the first electromechanical comprehensive management computer and the second electromechanical comprehensive management computer are accessed to a second electromechanical system set which is at least partially the same;
the first remote interface unit and the second remote interface unit which are arranged in parallel carry out data interaction with a first electromechanical integrated management computer and a second electromechanical integrated management computer which are arranged in parallel through a first bus, the first remote interface unit and the second remote interface unit are connected through a second bus to realize data interaction, and the first electromechanical integrated management computer and the second electromechanical integrated management computer are connected through the second bus to realize data interaction;
the first electromechanical comprehensive management computer and the second electromechanical comprehensive management computer perform data interaction with the avionic system through the first bus, wherein when the first electromechanical comprehensive management computer and the second electromechanical comprehensive management computer perform data interaction with the avionic system, at most one electromechanical comprehensive management computer performs data interaction with the avionic system.
2. The system according to claim 1, wherein when a communication between the first remote interface unit and the first bus fails, the first remote interface unit and the second remote interface unit perform data backup via the second bus and then transmit data to the mechatronic management computer communicating with the avionic system via the other remote interface unit that does not have the communication failure.
3. The on-board mechatronic integrated management system of claim 1, wherein the first remote interface unit and the second remote interface unit each communicate data over the first bus to the mechatronic integrated management computer in communication with the avionics system when a failure occurs in the second bus communication between the first remote interface unit and the second remote interface unit.
4. The on-board mechatronic integrated management system of claim 1, wherein the first mechatronic integrated management computer and the second mechatronic integrated management computer perform data backup via the first bus or the second bus when any one of the first mechatronic integrated management computer and the second mechatronic integrated management computer fails to communicate with the avionic system via the first bus.
5. The on-board mechatronic integrated management system of claim 1, wherein the first mechatronic integrated management computer and the second mechatronic integrated management computer implement data backup via the second bus in the event of a failure of either one of the first mechatronic integrated management computer and the second mechatronic integrated management computer to communicate with the remote interface unit via the first bus.
6. The on-board mechatronic management system of claim 1, wherein the first mechatronic management computer and the second mechatronic management computer perform data backup via the first bus in the event of a failure of the second bus communication between the first mechatronic management computer and the second mechatronic management computer.
7. The on-board electromechanical integrated management system of claim 1, wherein the first bus and the second bus are different types of buses.
8. The on-board electromechanical integrated management system of claim 7, wherein the first bus is GJB 289A.
9. The on-board electromechanical integrated management system of claim 7, wherein the second bus is a CCDL bus.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113497663A (en) * | 2021-05-28 | 2021-10-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Distributed network architecture and time synchronization method thereof |
| CN114116279A (en) * | 2021-11-08 | 2022-03-01 | 陕西千山航空电子有限责任公司 | Electromechanical management system |
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