CN112046773A - Avionics system of air traffic aircraft based on CAN network - Google Patents
Avionics system of air traffic aircraft based on CAN network Download PDFInfo
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Abstract
The invention relates to an avionics system of an air traffic aircraft based on a CAN (controller area network), which comprises a flight control system, a complete machine control system, a cockpit display and control system and a wireless communication system, wherein the flight control system is in communication connection with the complete machine control system through a triple-redundancy CAN bus; the three-redundancy CAN bus comprises three sets of independent CAN bus channels, the cockpit display and control system is respectively in communication connection with each set of CAN bus channel, and the wireless communication system is respectively in communication connection with each set of CAN bus channel; the flight control system comprises at least three flight control computers, each flight control computer is connected with two sets of CAN bus channels, and the two sets of CAN bus channels connected with each flight control computer are not identical; the whole machine control system comprises at least three whole machine controllers, each whole machine controller is connected with two sets of CAN bus channels, and the two sets of CAN bus channels connected with each whole machine controller are not identical.
Description
Technical Field
The invention relates to the technical field of avionics, in particular to an avionics system of an air traffic aircraft based on a CAN network.
Background
In recent years, the field of Urban Air traffic (UAM) has been spread comprehensively, and the field of Urban Air traffic includes manned and carried scenes, so that a new traffic mode can be brought for people going out, and meanwhile, the traffic jam condition is effectively reduced.
The avionic system can provide necessary energy for the air traffic aircraft, manage and control the air traffic aircraft to fly autonomously, and complete navigation, guidance and control of the air traffic aircraft so as to ensure the air traffic aircraft to fly accurately, reliably and stably according to a preset air route, and is an important component of the air traffic aircraft.
At present, the unmanned aerial vehicle has a great development due to the wide application prospect in the fields of disaster investigation and rescue, aerial monitoring, power transmission line inspection, aerial photography, aerial survey and military, and various solutions of the aerial electric system of the unmanned aerial vehicle are developed. In order to meet the requirements in the field of urban air traffic, the unmanned aerial vehicle is developing towards the airworthiness direction, but at present, the unmanned aerial vehicle is still basically in a starting stage, and the existing scheme of the avionic system of the unmanned aerial vehicle does not meet the airworthiness requirement and cannot meet the requirements of aviation regulations. Therefore, it is necessary to design an avionics system of an air traffic aircraft with high cost performance and meeting the requirements of aviation regulations for application in a wide range of operating scenarios for cargo and people.
Disclosure of Invention
In view of the above problems in the prior art, an object of the present invention is to provide an avionics system of an air traffic aircraft based on a CAN network, which CAN be applied to the air traffic aircraft and meet the safety requirements.
In order to solve the problems, the invention provides an avionics system of an air traffic aircraft based on a CAN network, which comprises a flight control system, a complete machine control system, a cockpit display and control system and a wireless communication system, wherein the flight control system is in communication connection with the complete machine control system through a triple redundant CAN bus; the three-redundancy CAN bus comprises three sets of independent CAN bus channels, the cockpit display and control system is respectively in communication connection with each set of CAN bus channel, and the wireless communication system is respectively in communication connection with each set of CAN bus channel; the flight control system comprises at least three redundant flight control computers, each flight control computer has a system architecture for realizing a complete flight control function, at least one flight control computer in the flight control system has a heterogeneous system architecture different from that of other flight control computers, each flight control computer is accessed to two sets of CAN bus channels, and the two sets of CAN bus channels accessed by each flight control computer are not identical; the whole machine control system comprises at least three redundant whole machine controllers, each whole machine controller is provided with a system architecture for realizing all other functions except flight control, at least one whole machine controller in the whole machine control system is provided with a heterogeneous system architecture different from that of other whole machine controllers, each whole machine controller is connected with two sets of CAN bus channels, and the two sets of CAN bus channels connected with each whole machine controller are not identical.
Furthermore, the flight control system also comprises a first voter, wherein the first voter is used for carrying out computer fault judgment according to the monitoring states of the at least three flight control computers to obtain a fault judgment result and carrying out redundancy switching according to the fault judgment result; wherein the monitoring states include self-monitoring states and mutual-monitoring states of the at least three flight control computers.
Furthermore, the complete machine control system also comprises a second voter, wherein the second voter is used for carrying out controller fault judgment according to the monitoring states of the at least three complete machine controllers to obtain a fault judgment result, and carrying out redundancy switching according to the fault judgment result; the monitoring states comprise self-monitoring states and mutual-monitoring states of the at least three complete machine controllers.
Furthermore, the cockpit display and control system comprises at least two cockpit display and control modules with non-similarity redundancy, each cockpit display and control module is connected with two sets of CAN bus channels, and the two sets of CAN bus channels connected with each cockpit display and control module are not identical; the wireless communication system comprises at least two communication control modules with non-similarity redundancy, wherein each communication control module is connected with two sets of CAN bus channels, and the two sets of CAN bus channels connected with each communication control module are not identical.
Furthermore, the system also comprises a perception and avoidance system and an environment control system, wherein the perception and avoidance system and the environment control system are respectively in communication connection with the triple-redundancy CAN bus.
Furthermore, the system also comprises an atmosphere data system and an integrated navigation system, wherein the atmosphere data system is in communication connection with the integrated navigation system, and the atmosphere data system and the integrated navigation system are respectively in communication connection with the flight control system.
Further, the air data system comprises at least two redundant air data machines, and the integrated navigation system comprises at least two redundant integrated navigation modules.
Specifically, the atmospheric data system is in communication connection with the integrated navigation system through a standard 422 bus, the atmospheric data system is in communication connection with the flight control system through a standard 485 bus, and the integrated navigation system is in communication connection with the flight control system through a standard 485 bus.
Further, the system also comprises an airborne wireless communication module, wherein the airborne wireless communication module is used for communicating with the ground control system; the airborne wireless communication module is in communication connection with the integrated navigation system, and the airborne wireless communication module is in communication connection with the triple-redundancy CAN bus.
Furthermore, the airborne wireless communication module comprises at least three airborne wireless communication terminals with non-similarity redundancy, each airborne wireless communication terminal is connected with two sets of CAN bus channels, and the two sets of CAN bus channels connected with each airborne wireless communication terminal are not identical.
Due to the technical scheme, the invention has the following beneficial effects:
the invention builds the avionics system of the aircraft by the heterogeneous triple-redundancy flight control system and the complete machine control system which are designed in a comprehensive modularized way, as well as other functional devices such as a cockpit display and control system, a wireless communication system and the like through the CAN bus network based on the redundancy design, CAN meet the safety requirement of aviation regulations, has strong expanded development space, CAN be applied to wide application scenes of manned and cargo carrying, and CAN reduce the cost of the avionics system of the air traffic aircraft.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings used in the description of the embodiment or the prior art will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a schematic structural diagram of an avionics system provided by an embodiment of the present invention;
FIG. 2 is a schematic diagram of a flight control computer provided in accordance with an embodiment of the present invention;
FIG. 3 is a functional operational logic diagram of a flight control computer provided in accordance with one embodiment of the present invention;
fig. 4 is a schematic structural diagram of a complete machine controller according to an embodiment of the present invention.
The system comprises a flight control system, a flight control computer, a first voter, a complete machine control system, a complete machine controller, a second voter, a control system, a cockpit display and control system, a wireless communication system, a triple redundant CAN bus, a 60-perception and avoidance system, an environment control system, an 80-atmospheric data system, a 90-combined navigation system and an onboard wireless communication module, wherein the flight control system is 10, the flight control computer is 101, the first voter is 102, the complete machine control system is 20, the complete machine controller is 201, the second voter is 202, the cockpit display and control system is 30.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
Referring to the specification and the drawings, fig. 1 shows the structure of an avionics system of an air traffic aircraft based on a CAN network according to an embodiment of the present invention. As shown in fig. 1, the system may include a flight control system 10, a complete machine control system 20, a cockpit display and control system 30 and a wireless communication system 40, wherein the flight control system 10 and the complete machine control system 20 are communicatively connected through a triple redundant CAN bus 50; the triple-redundancy CAN bus 50 comprises three sets of independent CAN bus channels, the cockpit display and control system 30 is respectively in communication connection with each set of CAN bus channel, and the wireless communication system 40 is respectively in communication connection with each set of CAN bus channel; the flight control system 10 comprises at least three redundant flight control computers 101, each flight control computer 101 has a system architecture for realizing a complete flight control function, at least one flight control computer 101 in the flight control system 10 has a heterogeneous system architecture different from that of the other flight control computers 101, each flight control computer 101 is accessed to two sets of CAN bus channels, and the two sets of CAN bus channels accessed by each flight control computer 101 are not identical; the complete machine control system 20 includes at least three redundant complete machine controllers 201, each complete machine controller 201 has a system architecture for realizing all other functions except flight control, at least one complete machine controller 201 in the complete machine control system 20 has a heterogeneous system architecture different from that of the other complete machine controllers 201, each complete machine controller 201 has two sets of CAN bus channels, and the two sets of CAN bus channels accessed by each complete machine controller 201 are not identical.
In the embodiment of the present invention, the flight control system 10 and the complete machine control system 20 may be both designed in a heterogeneous triple redundancy manner, so as to ensure that the safety thereof meets the requirements of SAE ARP 4761 "guidance and method for evaluating safety of civil onboard systems and equipment" safety analysis process, and the heterogeneous system architecture refers to a system architecture obtained by designing, developing and testing different organizations and members. The flight control computer 101 may be configured to perform the most important flight control function of the aircraft, and with reference to fig. 2 and fig. 3 of the specification, the flight control computer 101 may include a function module in which a Functional Development Assurance Level (FDAL) is an a-Level, such as a horizontal/vertical guidance (guidance), a perception information fusion calculation, an avoidance and route restoration, a control law calculation, a flight warning system (CAS), a three-dimensional map database, a performance calculation, a performance database, and a flight database. The complete machine controller 201 may be configured to complete all other functions of the aircraft flight operation except for the function implemented by the flight control computer 101, and with reference to fig. 4 in the specification, the complete machine controller 201 may include functional modules such as task management, mode management, health management, energy system management, lighting system control, and cooling system management.
In the embodiment of the present invention, the triple-redundant CAN bus 50 is a triple-redundant Controller Area Network (CAN) bus, and the triple-redundant CAN bus 50 CAN form a connection Network by the flight control system 10, the complete machine control system 20, the cockpit display and control system 30, and the wireless communication system 40. All the devices in the flight control system 10, the complete machine control system 20, the cockpit display and control system 30 and the wireless communication system 40 CAN be accessed to two sets of CAN bus channels through CAN buses, and the flight control system 10, the complete machine control system 20, the cockpit display and control system 30 and the wireless communication system 40 are ensured to be respectively in communication connection with three sets of CAN bus channels.
In one possible embodiment, the flight control system 10 may further include an aircraft operating system and flight control actuators, and each of the flight control computers 101 may further be communicatively coupled to a joystick displacement sensor, a seatbelt tie-down sensor, an intra-cabin environmental sensor, a door lock status sensor, and a propeller, respectively, the joystick displacement sensor may be of a triple redundant design, for detecting displacement of a joystick of the aircraft operating system, the propellers may comprise 1 thrust propeller and 8 lift propellers, flight control actuator includes left rudder, right rudder, left aileron, right aileron, left elevator and the right elevator of two redundant designs, every flight control computer 101 respectively with left rudder, right rudder, left aileron, right aileron, left elevator and the right elevator communication connection of two redundant designs.
Further, the flight control system 10 may further include a first voter 102, where the first voter 102 is configured to perform computer fault judgment according to the monitoring states of the at least three flight control computers 101 to obtain a fault judgment result, and perform redundancy switching according to the fault judgment result; wherein the monitoring states include a self-monitoring state and a mutual-monitoring state of the at least three flight control computers 101.
In the embodiment of the present invention, there may be three flight control computers 101, two flight control computers 101 may be communicatively connected through an ARINC 429 bus, one or more first voters 102 may be provided, which is not limited in the embodiment of the present invention, and the first voter 102 may include various voting logics therein. In one example, taking the "majority rule" as an example, the voting logic is shown in table 1.
TABLE 1 voting logic
The voting logic, which essentially performs self-tests and mutual tests of the computers, is very sensitive to the fact that there is a very small probability that two failing computers will simultaneously consider the other normal computer to be failing. Therefore, a heterogeneous triple redundancy mode can be adopted, and at least one of the three computers is heterogeneous with the other two computers (the other two computers can be heterogeneous or not), namely, the three computers are isolated from design, development, production, test, personnel, research and development processes, technologies and equipment, so that the reliability and the safety of the system are improved.
In another example, on the basis of table 1, the embodiment of the present invention further provides a logic strategy after the triple redundancy system fails, which includes a switching logic and a decision logic and a switching logic under the dual redundancy operation mode. For example, the switching logic is shown in table 2, and the decision logic and the switching logic in the dual redundancy operation mode are shown in table 3.
TABLE 2 switch logic
Voting logic and switching logic under table 3 dual redundancy working mode
Further, the complete machine control system 20 may further include a second voter 202, where the second voter 202 is configured to perform controller fault judgment according to the monitoring states of the at least three complete machine controllers 201 to obtain a fault judgment result, and perform redundancy switching according to the fault judgment result; the monitoring states include a self-monitoring state and a mutual-monitoring state of the at least three overall controllers 201.
In the embodiment of the present invention, there may be three complete machine controllers 201, every two of the three complete machine controllers 201 may be connected through ARINC 429 bus communication, and the second voter 202 may include a plurality of voting logics therein. In particular, the voting logic and the switching logic described in tables 1 to 3 may be referred to.
Further, the cockpit display and control system 30 may include at least two cockpit display and control modules with non-similarity redundancy, each cockpit display and control module is accessed to two sets of CAN bus channels, and the two sets of CAN bus channels accessed by each cockpit display and control module are not identical; the wireless communication system 40 may include at least two communication control modules with non-similarity redundancy, each of the communication control modules is connected to two sets of CAN bus channels, and the two sets of CAN bus channels connected to each of the communication control modules are not identical.
In the embodiment of the invention, the number of the cockpit display and control modules can be two, and the number of the communication control modules can also be two. Each cockpit display and control module CAN be accessed into two sets of CAN bus channels through a CAN bus, and each communication control module CAN also be accessed into two sets of CAN bus channels through the CAN bus, and the cockpit display and control system 30 and the wireless communication system 40 are respectively in communication connection with three sets of CAN bus channels. For example, assuming that one cockpit display and control module is connected to the CAN bus channel 1 and the CAN bus channel 2, the other cockpit display and control module may be connected to the CAN bus channel 1 and the CAN bus channel 3, or may be connected to the CAN bus channel 2 and the CAN bus channel 3, and it is only necessary to comprehensively consider the connection condition of the whole system, so as to avoid over-busy of a certain set of CAN bus channels.
Further, the system may further include a sense and avoidance system 60 and a climate control system 70, wherein the sense and avoidance system 60 and the climate control system 70 are respectively communicatively connected to the triple-redundant CAN bus 50.
In an embodiment of the present invention, the awareness and avoidance system 60 may include a radar and a camera, which may form a redundant sensor structure. The perception and avoidance system 60 may be connected to three sets of CAN bus channels through a CAN bus, and specifically, the radar and the camera may be respectively accessed to two sets of CAN bus channels, and the two sets of CAN bus channels accessed by the radar and the camera are not identical. The environmental control system 70 may be connected to any two sets of CAN bus channels through the CAN bus, and it is only necessary to consider the connection condition of the whole system comprehensively, so as to avoid that a certain set of CAN bus channel is too busy. Exemplarily, assuming that the radar is connected to the CAN bus channel 1 and the CAN bus channel 3, the camera may be connected to the CAN bus channel 1 and the CAN bus channel 2, and may also be connected to the CAN bus channel 2 and the CAN bus channel 3.
The triple-redundancy CAN bus 50 of the invention forms a connection network with other functional devices such as the flight control system 10, the complete machine control system 20, the cockpit display and control system 30, the wireless communication system 40, the perception and avoidance system 60 and the environmental control system 70, and ensures that any single device is connected to two sets of CAN bus channels, and any system comprising a plurality of devices is connected to three sets of CAN bus channels. By the design, any single point of failure can be guaranteed, and the safety requirement of triple redundancy cannot be influenced.
Further, the system may further include an atmosphere data system 80 and a combined navigation system 90, the atmosphere data system 80 being communicatively connected to the combined navigation system 90, and the atmosphere data system 80 and the combined navigation system 90 being communicatively connected to the flight control system 10, respectively.
Further, the air data system 80 may include at least two air data machines that are redundant, and the integrated navigation system 90 may include at least two integrated navigation modules that are redundant.
Specifically, the air data system 80 and the integrated navigation system 90 may be communicatively connected through a standard 422 bus, the air data system 80 and the flight control system 10 may be communicatively connected through a standard 485 bus, and the integrated navigation system 90 and the flight control system 10 may be communicatively connected through a standard 485 bus.
In the embodiment of the present invention, both the atmospheric data system 80 and the integrated navigation system 90 may be designed in a dual redundancy manner, each atmospheric data machine in the atmospheric data system 80 may be respectively in communication connection with two integrated navigation modules in the integrated navigation system 90 through a standard 422 bus (RS422 bus), the atmospheric data system 80 may be directly in communication connection with the flight control system 10 through a dual redundancy standard 485 bus (RS485 bus), and the integrated navigation system 90 may also be directly in communication connection with the flight control system 10 through the dual redundancy RS485 bus. Specifically, each air data machine may be communicatively connected to any one flight control computer 101 in the flight control system 10 through one of the RS485 buses, and may be communicatively connected to two other flight control computers 101 in the flight control system 10 through another RS485 bus. Each combined navigation module can be in communication connection with any one flight control computer 101 in the flight control system 10 through one of the RS485 buses, and can be in communication connection with the other two flight control computers 101 in the flight control system 10 through the other RS485 bus, and the master node of the RS485 bus can be the flight control computer 101 in the flight control system 10. In this way, a master-slave network CAN be formed comprising devices with class B FDAL levels, such as air modems, integrated navigation modules, etc., to the flight control system 10, as a supplement to the triple redundant CAN bus network.
Further, the system may further include an onboard wireless communication module 100, wherein the onboard wireless communication module 100 is used for communicating with a ground control system; the onboard wireless communication module 100 is in communication connection with the integrated navigation system 90, and the onboard wireless communication module 100 is in communication connection with the triple-redundant CAN bus 50.
Further, the airborne wireless communication module 100 may include at least three airborne wireless communication terminals with non-similarity redundancy, each airborne wireless communication terminal accesses two sets of CAN bus channels, and the two sets of CAN bus channels accessed by each airborne wireless communication terminal are not identical.
In the embodiment of the present invention, the airborne wireless communication module 100 may be designed for non-similarity triple redundancy. Each airborne wireless communication terminal in the airborne wireless communication module 100 CAN be in communication connection with each integrated navigation module in the integrated navigation system 90 through an RS422 bus, and each airborne wireless communication terminal in the airborne wireless communication module 100 CAN be accessed into two sets of CAN bus channels through a CAN bus, and the airborne wireless communication module 100 is ensured to be in communication connection with three sets of CAN bus channels. Thus, a point-to-multipoint data transmission network among the atmospheric data system 80, the integrated navigation system 90 and the airborne wireless communication module 100 can be established through the RS422 bus network.
In one possible embodiment, the ground control system may include two ground wireless communication terminals, a meteorological information acquisition device, an RTK base station, two display and control systems, a flight data recorder, a voice recorder, and the like, and the respective devices of the ground control system may be communicatively connected through a redundant CAN bus, and the master node of the CAN bus may be the two display and control systems.
The actual effect of the avionics system provided by the embodiment of the invention is tested, so that the avionics system provided by the embodiment of the invention can realize the safety index shown in the table 4, and meets the requirements of civil aviation regulations on the aircraft with the magnitude and the function.
TABLE 4 avionics system reliability data
In conclusion, the avionics system of the air traffic aircraft has the following beneficial effects:
the avionics system provided by the embodiment of the invention takes a three-redundancy CAN bus network as a basis, integrates a heterogeneous three-redundancy flight control system and a whole control system which are designed in a modularized way, and other functional devices such as a cockpit display and control system, a wireless communication system, a perception and avoidance system, an environment control system and the like form a connection network, then, an atmospheric data system, a combined navigation system and the like are built to a master-slave network of a flight control system through a dual-redundancy RS485 bus network, a data information transmission network with quick point-to-multipoint response is built through an RS422 bus network, and integrates and optimizes the avionics system of the aircraft to meet the safety requirement of meeting aviation regulations, and the method has a strong expanded development space, can be applied to wide application scenes of people and cargo carrying, and can also reduce the cost of an aerial electric system of the air traffic aircraft.
The foregoing description has disclosed fully preferred embodiments of the present invention. It should be noted that those skilled in the art can make modifications to the embodiments of the present invention without departing from the scope of the appended claims. Accordingly, the scope of the appended claims is not to be limited to the specific embodiments described above.
Claims (10)
1. The avionics system of the air traffic aircraft based on the CAN network is characterized by comprising a flight control system (10), a complete machine control system (20), a cockpit display and control system (30) and a wireless communication system (40), wherein the flight control system (10) is in communication connection with the complete machine control system (20) through a triple redundant CAN bus (50);
the three-redundancy CAN bus (50) comprises three sets of independent CAN bus channels, the cockpit display and control system (30) is respectively in communication connection with each set of CAN bus channel, and the wireless communication system (40) is respectively in communication connection with each set of CAN bus channel;
the flight control system (10) comprises at least three redundant flight control computers (101), each flight control computer (101) has a system architecture for realizing a complete flight control function, at least one flight control computer (101) in the flight control system (10) has a heterogeneous system architecture different from that of other flight control computers (101), each flight control computer (101) is connected with two sets of CAN bus channels, and the two sets of CAN bus channels connected with each flight control computer (101) are not identical;
the whole machine control system (20) comprises at least three redundant whole machine controllers (201), each whole machine controller (201) is provided with a system architecture for realizing all other functions except flight control, at least one whole machine controller (201) in the whole machine control system (20) is provided with a heterogeneous system architecture different from the rest whole machine controllers (201), two sets of CAN bus channels are connected to each whole machine controller (201), and the two sets of CAN bus channels connected to each whole machine controller (201) are not identical.
2. The system according to claim 1, wherein the flight control system (10) further comprises a first voter (102), the first voter (102) is configured to perform a computer fault judgment according to the monitoring states of the at least three flight control computers (101), obtain a fault judgment result, and perform redundancy switching according to the fault judgment result; wherein the monitoring states comprise a self-monitoring state and a mutual-monitoring state of the at least three flight control computers (101).
3. The system according to claim 1 or 2, wherein the overall control system (20) further comprises a second voter (202), the second voter (202) is configured to perform controller fault judgment according to the monitoring states of the at least three overall controllers (201), obtain a fault judgment result, and perform redundancy switching according to the fault judgment result; wherein, the monitoring state comprises a self-monitoring state and a mutual-monitoring state of the at least three complete machine controllers (201).
4. The system of claim 1, wherein said cockpit display and control system (30) includes at least two cockpit display and control modules that are non-similarly redundant, each of said cockpit display and control modules having access to two sets of CAN bus channels that are not identical; the wireless communication system (40) comprises at least two communication control modules with non-similarity redundancy, each communication control module is connected with two sets of CAN bus channels, and the two sets of CAN bus channels connected with each communication control module are not identical.
5. The system of claim 1, further comprising a sense and avoidance system (60) and a climate control system (70), the sense and avoidance system (60) and the climate control system (70) each communicatively coupled to the triple redundant CAN bus (50).
6. The system of claim 1 or 5, further comprising an air data system (80) and a combined navigation system (90), the air data system (80) communicatively coupled to the combined navigation system (90), the air data system (80) and the combined navigation system (90) communicatively coupled to the flight control system (10), respectively.
7. The system of claim 6, wherein the air data system (80) includes at least two air data machines that are redundant and the integrated navigation system (90) includes at least two integrated navigation modules that are redundant.
8. The system of claim 7, wherein the air data system (80) is communicatively coupled to the integrated navigation system (90) via a standard 422 bus, the air data system (80) is communicatively coupled to the flight control system (10) via a standard 485 bus, and the integrated navigation system (90) is communicatively coupled to the flight control system (10) via a standard 485 bus.
9. The system of claim 6, further comprising an onboard wireless communication module (100), the onboard wireless communication module (100) for communicating with a ground control system; the airborne wireless communication module (100) is in communication connection with the integrated navigation system (90), and the airborne wireless communication module (100) is in communication connection with the triple-redundancy CAN bus (50).
10. The system according to claim 9, characterized in that said onboard wireless communication module (100) comprises at least three onboard wireless communication terminals with non-similarity redundancy, each of said onboard wireless communication terminals accessing two sets of CAN bus channels, the two sets of CAN bus channels accessed by each of said onboard wireless communication terminals being not identical.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113009933A (en) * | 2021-03-10 | 2021-06-22 | 广东汇天航空航天科技有限公司 | Control device and control method of aircraft and aircraft |
| CN114261522A (en) * | 2022-01-08 | 2022-04-01 | 邓懿轩 | Airborne system architecture and aircraft |
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