An in-flight wireless communication system and communication method for an aircraft electromechanical system

Abstract

The present application provides an aircraft electromechanical system in-flight wireless communication system and communication method. The aircraft electromechanical system in-flight wireless communication system provided by the present application realizes efficient and real-time information interaction between VMC and front wheel turning actuation, rudder actuation, spoiler actuation and perception processing unit by constructing four different communication links; by making wireless communication between RIU and gateway node, gateway node and protocol processing terminal, the need for complex wiring is reduced and the weight of electromechanical system is reduced; by making protocol processing terminal correspond to actuator or perception processing unit one by one, the accuracy of data processing and the consistency of system operation can be improved; each system is independently connected to VMC through bus, which is convenient for maintenance and upgrading, and adapting to different task requirements; each system supports access to multiple terminal devices, and each protocol processing terminal communicates with its corresponding terminal device separately, which is easy to expand new terminal devices according to needs.

Description

Technical Field

[0001] The present application relates to the field of wireless communication technology, and in particular to an in-flight wireless communication system and communication method for an aircraft electromechanical system. Background Art

[0002] As aircraft's requirements for electromechanical systems continue to increase, the independent and decentralized system structure of traditional aircraft electromechanical systems has been unable to meet the requirements. Related systems that focus on the generation, transmission, conversion and integrated utilization of secondary energy are developing in the direction of integration, intelligence, multi-electrification and energy optimization, forming intelligent aviation electromechanical systems to meet new development needs. The primary demand brought about by intelligent development is the dramatic increase in data volume. At this time, how to efficiently and real-time transmit data has become the focus of research on intelligent aviation electromechanical systems. Summary of the invention

[0003] In view of this, the present application provides an aircraft mechatronic system in-flight wireless communication system and communication method, which are used to clarify the data transmission requirements according to the working characteristics of each product, establish an in-flight wireless communication system for the mechatronic system, and transmit data efficiently and in real time.

[0004] Specifically, the present application is implemented through the following technical solutions:

[0005] A first aspect of the present application provides an aircraft mechatronic system in-flight wireless communication system, the aircraft mechatronic system in-flight wireless communication system comprising an active motion controller VMC, and a first system, a second system, a third system, and a fourth system respectively connected to the VMC through a bus;

[0006] The VMC and the first system constitute a first communication link from the VMC to the front wheel turning actuation system, for realizing information interaction between the VMC and the front wheel turning control system; the VMC and the second system constitute a second communication link from the VMC to the rudder actuation system, for realizing information interaction between the VMC and the rudder actuation system; the VMC and the third system constitute a third communication link from the VMC to the spoiler electrostatic hydraulic actuation system, for realizing information interaction between the VMC and the bypass liquid actuation system; the VMC and the fourth system constitute a fourth communication link from the VMC to the perception processing unit, for realizing information interaction between the VMC and the perception processing unit;

[0007] Any one of the first system, the second system, the third system and the fourth system includes a remote interface unit RIU connected to the VMC through a bus, a gateway node wirelessly communicating with the RIU, at least one protocol processing terminal communicating with the gateway node, and at least one terminal device; wherein, at least one terminal device in the first system, the second system and the third system is an actuator in the actuation system corresponding to the system, the number of protocol processing terminals in the first system, the second system and the third system is consistent with the number of actuators included in the actuation system corresponding to the system, and one protocol processing terminal is connected to one actuator; at least one terminal device in the fourth system is a perception processing unit, the number of protocol processing terminals in the fourth system is consistent with the number of perception processing units included in the system, and one protocol processing terminal is connected to one perception processing unit.

[0008] A second aspect of the present application provides an aircraft mechatronic system in-flight wireless communication method, the aircraft mechatronic system in-flight wireless communication method is implemented based on any aircraft mechatronic system in-flight wireless communication system described in the first aspect of the present application; the aircraft mechatronic system in-flight wireless communication method comprises:

[0009] The active motion controller VMC receives the control instruction from the flight control computer, parses the control instruction, and obtains the destination address of the control instruction; wherein the destination address points to the target actuator in the front wheel turning control system, the rudder actuation system, and the spoiler electrostatic hydraulic actuation system;

[0010] The VMC sends the control instruction to the target RIU in the target communication link where the target actuator pointed to by the destination address is located according to the destination address;

[0011] The target RIU forwards the control instruction to a target gateway node in the target communication link;

[0012] The target gateway node forwards the control instruction to a target protocol processing terminal in the communication link where the target gateway node is located according to the target address of the control instruction; wherein the target protocol processing terminal is a protocol processing terminal among all the protocol processing terminals in the communication link where the target gateway node is located, and is connected to the target actuator pointed to by the destination address through a bus;

[0013] The target protocol processing terminal sends the control instruction to the target actuator connected to the target protocol processing terminal to instruct the target actuator to execute the control instruction.

[0014] The present application provides an in-flight wireless communication system and communication method for an aircraft electromechanical system. On the one hand, by constructing four different communication links, the different communication links realize efficient and real-time information interaction between the VMC and the front wheel turning actuation, rudder actuation, spoiler actuation and perception processing unit, thereby improving the response capability. On the second hand, by enabling wireless communication between the remote interface unit RIU and the gateway node, and between the gateway node and the protocol processing terminal, the need for complex wiring can be reduced and the weight of the electromechanical system can be reduced. On the third hand, by enabling one-to-one correspondence between the protocol processing terminal and the actuator or perception processing unit, the accuracy of data processing and the consistency of system operation can be improved. On the fourth hand, each system is independently connected to the active motion controller VMC through a bus, which is convenient for maintenance and upgrading, and can adapt to different task requirements. On the fifth hand, each system supports the access of multiple terminal devices, and each protocol processing terminal communicates separately with its corresponding terminal device, making it easy to expand new terminal devices according to needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 A schematic diagram of an in-flight wireless communication system for an aircraft electromechanical system provided in Embodiment 1 of the present application;

[0016] Figure 2 This is a schematic diagram of the implementation principle of the in-flight wireless communication system of the aircraft electromechanical system exemplified in this application;

[0017] Figure 3 A flowchart of a method for wireless communication within an aircraft electromechanical system provided in Embodiment 2 of the present application. DETAILED DESCRIPTION

[0018] Here, exemplary embodiments are described in detail, and examples thereof are shown in the accompanying drawings. When the following description refers to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The implementations described in the following exemplary embodiments do not represent all implementations consistent with the present application.

[0019] The terms used in this application are only for the purpose of describing specific embodiments and are not intended to limit this application. The singular forms of "a", "said" and "the" used in this application are also intended to include plural forms, unless the context clearly indicates other meanings. It should also be understood that the term "and / or" used in this article refers to and includes any or all possible combinations of one or more associated listed items.

[0020] It should be understood that although the terms first, second, third, etc. may be used in the present application to describe various information, these information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of the present application, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Depending on the context, the word "if" as used herein may be interpreted as "at the time of" or "when" or "in response to determining".

[0021] Specific embodiments are given below to introduce the technical solution of the present application in detail.

[0022] Figure 1 This is a schematic diagram of an in-flight wireless communication system for an aircraft electromechanical system provided in Example 1 of the present application. Figure 1 The aircraft mechatronic system in-flight wireless communication system provided in this embodiment includes an active motion controller VMC, and a first system, a second system, a third system and a fourth system respectively connected to the VMC through a bus.

[0023] The VMC and the first system constitute a first communication link from the VMC to the front wheel turning actuation system, for realizing information interaction between the VMC and the front wheel turning control system; the VMC and the second system constitute a second communication link from the VMC to the rudder actuation system, for realizing information interaction between the VMC and the rudder actuation system; the VMC and the third system constitute a third communication link from the VMC to the spoiler electrostatic hydraulic actuation system, for realizing information interaction between the VMC and the spoiler electrostatic hydraulic actuation system; the VMC and the fourth system constitute a fourth communication link from the VMC to the perception processing unit, for realizing information interaction between the VMC and the perception processing unit;

[0024] Any one of the first system, the second system, the third system and the fourth system includes a remote interface unit RIU connected to the VMC through a bus, a gateway node wirelessly communicating with the RIU, at least one protocol processing terminal communicating with the gateway node, and at least one terminal device; wherein, at least one terminal device in the first system, the second system and the third system is an actuator in the actuation system corresponding to the system, the number of protocol processing terminals in the first system, the second system and the third system is consistent with the number of actuators included in the actuation system corresponding to the system, and one protocol processing terminal is connected to one actuator; at least one terminal device in the fourth system is a perception processing unit, the number of protocol processing terminals in the fourth system is consistent with the number of perception processing units included in the system, and one protocol processing terminal is connected to one perception processing unit.

[0025] For details, please refer to Figure 1 It can be seen that the aircraft mechatronic system in-flight wireless communication system provided by the present application includes an active motion controller VMC (Vehicle Motion Controller, referred to as VMC) and four subsystems, the four subsystems are respectively a first system, a second system, a third system and a fourth system, the VMC is connected to the four subsystems through a bus, respectively, to form four independent communication links, so that each communication link transmits action instructions and status information between different mechatronic systems, ensuring smooth information transmission of each communication link.

[0026] Furthermore, the VMC and the first system form a first communication link, which connects the VMC and the front wheel turning actuation system to realize information interaction between the VMC and the front wheel turning actuation system. Through the first communication link, the VMC can send control instructions to the front wheel turning actuation system to adjust the difficulty of the front wheel turning, thereby controlling the front wheel steering of the aircraft.

[0027] The VMC and the second system form a second communication link, which connects the VMC and the rudder actuation system to achieve information interaction between the VMC and the rudder actuation system. Through the second communication link, the VMC can issue instructions to control the angle of the rudder and the heading of the aircraft, thereby ensuring the stability and precise control of the aircraft's flight.

[0028] The VMC and the third system form a third communication link, which connects the VMC and the spoiler electrostatic-hydraulic actuation system, and can realize information exchange between the VMC and the spoiler electrostatic-hydraulic actuation system. The VMC sends instructions to the spoiler to control the spoiler. The spoiler can be used to adjust the airflow to improve the aerodynamic performance of the aircraft, thereby optimizing the flight stability of the aircraft.

[0029] Furthermore, the VMC and the fourth system form a fourth communication link, which connects the VMC and the perception processing unit to realize information exchange between the VMC and the perception processing unit. The perception processing unit can collect sensor data collected by sensors during the flight of the aircraft, and feed the sensor data back to the VMC through the fourth communication link, thereby assisting in making the best flight decision.

[0030] The following is a brief introduction to the fourth system:

[0031] Specifically, at least one terminal device in the fourth system is a perception processing unit, the number of protocol processing terminals in the fourth system is consistent with the number of perception processing units included in the system, and one protocol processing terminal is connected to one perception processing unit. In the working state, each perception processing unit transmits the collected raw data to the corresponding connected protocol processing terminal, and the protocol processing terminal processes or converts the format of the collected raw data so that it can be transmitted to the VMC for monitoring the flight status of the aircraft and making appropriate decisions.

[0032] Optionally, in a possible implementation, the perception processing unit includes any one of the following sensors: a first type of sensor provided in the hydraulic system, a second type of sensor provided in the fuel system, and a third type of sensor provided in the environmental control.

[0033] It should be noted that a sensing processing unit is composed of a sensor, and the number of sensing processing units can be set according to actual needs to collect various types of status data, which is not limited in this application. For example, in one embodiment, the fourth system includes three sensing processing units, and the three sensing processing units respectively include a first type of sensor set in the hydraulic system, a second type of sensor set in the fuel system, and a third type of sensor set in the environmental control, which are used to collect the working state of the hydraulic system inside the aircraft, the working state of the fuel system, and the environmental control of the aircraft (temperature, humidity, and air pressure inside the aircraft, etc.).

[0034] Furthermore, each sensing unit is connected to a protocol processing terminal. In combination with the above example, when the fourth system includes the first type of sensor, the second type of sensor and the third type of sensor, it may include three protocol processing terminals, and each sensor is connected to a protocol processing terminal.

[0035] The first system, the second system and the third system are introduced below:

[0036] Please continue to refer to Figure 1 Any of the first system, the second system, the third system and the fourth system includes a remote interface unit RIU (Remote Interface Unit, referred to as RIU) connected to the VMC through a bus, a gateway node for wireless communication with the RIU, at least one protocol processing terminal for communicating with the gateway node, and at least one terminal device. Among them, at least one terminal device of the first system, the second system and the third system is an actuator in the actuation system corresponding to the system, and accordingly, the first system, the second system and the third system have the same number of protocol processing units as the actuators.

[0037] It should be noted that one protocol processing terminal is connected to one actuator. As an electronic device responsible for receiving and processing data, the protocol processing terminal acts as a bridge between data communication and command execution within the system. By directly connecting each protocol processing terminal to an actuator, it can be ensured that each actuator can receive independent control instructions, making the operation of each actuator more precise. At the same time, it can also effectively avoid data conflicts or command conflicts that may occur when multiple actuators share one protocol processing terminal.

[0038] Please continue to refer to Figure 1 Specifically, the first system includes a first RIU, a first gateway node in wireless communication with the first RIU, a first protocol processing terminal in wireless communication with the first gateway node, and an electromechanical actuator of a front wheel turning control system connected to the first protocol processing terminal via a bus;

[0039] The second system includes a second RIU, a second gateway node in wireless communication with the second RIU, a first servo protocol processing terminal and a second servo protocol processing terminal in wireless communication with the second gateway node, and a first servo actuator of a rudder actuation system connected to the first servo protocol processing terminal via a bus and a second servo actuator of a rudder actuation system connected to the second servo protocol processing terminal via a bus;

[0040] The third system includes a third RIU, a third gateway node that wirelessly communicates with the third RIU, a first electrostatic hydraulic protocol processing terminal, a second electrostatic hydraulic protocol processing terminal, a third electrostatic hydraulic protocol processing terminal, and a fourth electrostatic hydraulic protocol processing terminal that wirelessly communicates with the third gateway node, and a first electrostatic hydraulic actuator of a spoiler electrostatic hydraulic actuation system connected to the first electrostatic hydraulic protocol processing terminal via a bus, a second electrostatic hydraulic actuator of a spoiler electrostatic hydraulic actuation system connected to the second electrostatic hydraulic protocol processing terminal via a bus, a third electrostatic hydraulic actuator of a spoiler electrostatic hydraulic actuation system connected to the third electrostatic hydraulic protocol processing terminal via a bus, and a fourth electrostatic hydraulic actuator of a spoiler electrostatic hydraulic actuation system connected to the fourth electrostatic hydraulic protocol processing terminal via a bus.

[0041] Figure 2 This is an implementation principle diagram of the aircraft electromechanical system in-flight wireless communication system exemplified in this application. Figure 2It can be seen that by connecting the flight control computer with the aircraft electromechanical system in-flight wireless communication system, the pilot can issue action instructions to the VMC through the flight control computer, which are transmitted via the RIU, and then the gateway node communicates wirelessly with the RIU to send the action instructions to each protocol processing terminal, and the actuator or perception processing unit connected to the protocol processing terminal through the bus performs the corresponding operation task according to the action instruction issued by the pilot (the operation task corresponding to the action instruction issued by the pilot can be to instruct the actuator to adjust the aircraft's front wheel steering, adjust the rudder or spoiler, etc., or to control the perception processing unit to perceive and collect the aircraft's status information, etc.); afterwards, the status information of the actuator after executing the operation task corresponding to the action instruction or the status information collected by the perception processing unit is fed back to the flight control computer controlled by the pilot through the protocol processing terminal, gateway node, RIU, and VMC in turn, so that the pilot can adjust subsequent operations.

[0042] Specifically, for example, for a front wheel turning control system, the pilot sends an action command from the flight control computer to the VMC, which is then transmitted to the electromechanical actuator via the first RIU, the first gateway node, and the first protocol processing terminal. The electromechanical actuator can correctly execute the action command, wherein the action command signal is transmitted from the VMC to the first RIU, from the first protocol processing terminal to the electromechanical actuator through the data bus, and from the first RIU to the first gateway node, and from the first gateway node to the first protocol processing terminal through wireless communication.

[0043] For the two servo actuators of the rudder actuation system, the pilot sends an action command from the flight control computer to the VMC, which is transmitted to the first servo actuator and the second servo actuator via the second RIU, the second gateway node, and then respectively via the first servo protocol processing terminal and the second servo protocol processing terminal. The first servo actuator and the second servo actuator can correctly execute the command, wherein the action command signal is transmitted from the VMC to the second RIU, from the first protocol processing terminal to the first servo actuator, and from the second protocol processing terminal to the second servo actuator through the data bus, and from the second RIU to the second gateway node, and from the second gateway node to the first servo protocol processing terminal and the second servo protocol processing terminal through wireless communication.

[0044] For the four electric clean hydraulic actuators of the spoiler electrostatic hydraulic actuation system, the pilot sends an action command from the flight control computer to the VMC, which is transmitted to the first electrostatic hydraulic actuator, the second electrostatic hydraulic actuator, the third electrostatic hydraulic actuator and the fourth electrostatic hydraulic actuator through the third RIU, the third gateway node, and then through the first electrostatic hydraulic protocol processing terminal, the second electrostatic hydraulic protocol processing terminal, the third electrostatic hydraulic protocol processing terminal and the fourth electrostatic hydraulic protocol processing terminal. The actuator can correctly execute instructions, wherein signals are transmitted from VMC to the third RIU, from the first protocol processing terminal to the first electrostatic hydraulic actuator, from the second protocol processing terminal to the second electrostatic hydraulic actuator, from the third protocol processing terminal to the third electrostatic hydraulic actuator and from the fourth protocol processing terminal to the fourth electrostatic hydraulic actuator through the data bus, and from the third RIU to the third gateway node, from the third gateway node to the first electrostatic hydraulic protocol processing terminal, the second electrostatic hydraulic protocol processing terminal, the third electrostatic hydraulic protocol processing terminal and the fourth electrostatic hydraulic protocol processing terminal through wireless communication.

[0045] Furthermore, for the collection of information on hydraulics, fuel, and environmental control, signals can be sent from the perception processing device to the protocol processing terminal, and then sent to the VMC after passing through the fourth gateway node and the fourth RIU. The signals are sent from the perception processing device to the protocol processing terminal, from the fourth RIU to the VMC through the data bus, from the protocol processing terminal to the fourth gateway node, and from the fourth gateway node to the fourth RIU through wireless communication.

[0046] It should be noted that wireless communication is not limited by transmission space, transmission distance, transmission rate, etc., and can realize fast wireless transmission of electromechanical equipment information; in addition, wireless communication can not only reduce unnecessary additional weight of the system, but also reduce the complexity of system deployment, greatly improving the mobility of the system; further, the application of wireless communication technology's low latency, massive data communication and other characteristics can provide electromechanical systems with wireless fast communication capabilities, and realize lightweight and intelligent configuration of electromechanical systems.

[0047] The aircraft electromechanical system in-flight wireless communication system provided by this embodiment has at least the following advantages:

[0048] (1) Reduce the complexity of the electromechanical system and reduce the difficulty and workload of maintenance. At the physical level, each subsystem is independently distributed. During the maintenance process, there is no need to consider the mutual influence between equipment, nor the possibility of difficult-to-check cable failures, thereby reducing the difficulty and workload of maintenance.

[0049] (2) Save space on the aircraft. After adopting wireless communication, there is no need to consider the wiring problem inside the aircraft, thus saving the original wiring space.

[0050] (3) Improving the efficiency of information transmission in electromechanical systems. Wireless communication has achieved qualitative improvements in information transmission rate and transmission reliability, which can effectively improve the efficiency of information transmission in electromechanical systems.

[0051] (4) Increase the flexibility and mobility of electromechanical systems. Through wireless communication, the wiring, networking, and testing of electromechanical systems will become more convenient, thereby improving work efficiency and reducing the cycle of system research and development, improvement, and upgrade.

[0052] In addition, the aircraft mechatronic system in-flight wireless communication system provided in the present embodiment transmits the action instructions issued by the aircraft pilot to the actuator or the sensing processing unit at the end of the system through the aircraft mechatronic system in-flight wireless communication system to execute the action instructions or the status information collection instructions, and feeds back the status information of the actuator after executing the action instructions and the status information of the aircraft collected by the sensing processing unit to the flight control computer. The aircraft pilot can issue new action instructions through the flight control computer as needed based on his understanding of the current status of the aircraft. The system has strong independence and high efficiency in instruction transmission and operation execution through the independent connection of multiple subsystems within the system and the integration of each subsystem by the VMC. In addition, the wireless communication between the RIU and the protocol processing terminal is realized by setting a gateway node, which greatly enhances the stability and real-time performance of data transmission, and can realize the communication between the flight control computer and the end effector of the system in a short time.

[0053] Furthermore, in the aircraft electromechanical system in-flight wireless communication system, each subsystem has an independent RIU inside, which can serve as a communication bridge between the system and the VMC, thereby improving the system's fault detection and response capabilities; further, each subsystem realizes remote communication with the RIU by setting up a wireless gateway node, thereby avoiding complex system wiring and providing a flexible deployment method; further, in each subsystem, by setting up a protocol processing terminal that is connected one-to-one with the actuator or perception processing unit, the redundancy and scalability of the system can be effectively improved. In this way, the modular design can effectively improve the reliability of communication and has strong scalability, thereby providing greater convenience for future technical upgrades. At the same time, by setting up gateway nodes in multiple subsystems to communicate wirelessly with the corresponding RIU, the system can reduce the complexity of wiring while effectively improving the independence and coordination of each subsystem, thereby ensuring that the aircraft can communicate reliably in complex environments.

[0054] The in-flight wireless communication system of the aircraft electromechanical system provided in this embodiment, firstly, by constructing four different communication links, different communication links realize efficient and real-time information interaction between the VMC and the front wheel turning actuation, rudder actuation, spoiler actuation and perception processing unit, thereby improving the response capability; secondly, by making the remote interface unit RIU and the gateway node, and the gateway node and the protocol processing terminal communicate wirelessly, the need for complex wiring can be reduced and the weight of the electromechanical system can be reduced; thirdly, by making the protocol processing terminal correspond one-to-one with the actuator or perception processing unit, the accuracy of data processing and the consistency of system operation can be improved; fourthly, each system is independently connected to the active motion controller VMC through the bus, which is convenient for maintenance and upgrading, and can adapt to different task requirements; fifthly, each system supports the access of multiple terminal devices, and each protocol processing terminal communicates separately with its corresponding terminal device, which is easy to expand new terminal devices according to needs.

[0055] Furthermore, in a possible implementation, any RIU in the first system, the second system, the third system and the fourth system is also used to reconstruct the communication link where the RIU is located when a failure of the communication link where the RIU is located is detected, so as to ensure the smoothness of the communication link where the RIU is located.

[0056] In a specific implementation, in a possible implementation manner, the communication link where the RIU is located may be reconstructed according to the following steps:

[0057] Step 1: Select a gateway node from other communication links other than the communication link where the RIU is located as a target gateway node, and establish a wireless communication connection with the target gateway node;

[0058] Step 2: Instruct the target gateway node to establish a wireless communication connection with the protocol processing terminal in the communication link where the RIU is located, so as to establish a communication link from the RIU to the target gateway node, and from the target gateway node to the protocol processing terminal in the communication link where the RIU is located, so as to reconstruct the communication link where the RIU is located through the target gateway node.

[0059] Specifically, for example, after detecting a communication link failure corresponding to a certain subsystem, a gateway node is selected from the gateway nodes in other communication links as the target gateway node, and the RIU in the faulty communication link is instructed to establish a wireless communication connection with the target gateway node. Further, the target gateway node is instructed to establish a wireless communication connection with the protocol processing terminal in the faulty communication link. In this way, the wireless gateway nodes in other communication links can be used to replace the wireless gateway nodes in the faulty communication link, thereby realizing the reconstruction of the faulty communication link.

[0060] It should be noted that, according to actual needs, a suitable gateway node can be selected as the target gateway node from other communication links other than the communication link where the RIU is located, and this is not limited in the present application. For example, in one embodiment, a gateway node with the strongest signal strength can be selected as the target gateway node from all the gateway nodes included in other communication links other than the communication link where the RIU is located; in another embodiment, a gateway node with the lightest load can be selected as the target gateway node from all the gateway nodes included in other communication links other than the communication link where the RIU is located; for another example, in another possible implementation, a gateway node closest to the RIU can be selected as the target gateway node from all the gateway nodes included in other communication links other than the communication link where the RIU is located.

[0061] For example, in one embodiment, when the first RIU finds that the first gateway node fails and cannot communicate, the first RIU may select the nearest gateway node (to ensure the reliability of the wireless transmission signal) as the target gateway node based on the principle of proximity, for example, select the second gateway node, and reconstruct the communication links from the VMC to the first RIU, from the first RIU to the second gateway node, from the second gateway node to the first protocol processing terminal, and from the first protocol processing terminal to the electromechanical actuator, to ensure that the action instructions of the flight control computer can be sent to the electromechanical actuator in a timely manner, thereby ensuring the normal operation of the aircraft.

[0062] Specifically, the RIU in each communication link serves as a fault detection device, and performs real-time detection on the communication link in which it is located. When it is detected that a fault occurs in the communication link and normal communication cannot be achieved, a reconstruction operation can be performed to restore the communication function.

[0063] Optionally, in a possible implementation, when it is detected that the faulty communication link can restore the communication function, the reconstructed communication link is controlled to be disconnected, and the original communication link is restored to perform the communication function to ensure normal communication of other communication links.

[0064] In combination with the previous example, when the first RIU finds that the first gateway node resumes communication, the first RIU re-establishes a connection with the first gateway node, disconnects from the second gateway node, and instructs the second gateway node to disconnect from the first protocol processing terminal, thereby restoring the original first communication link. The wireless communication system in the aircraft electromechanical system provided in this embodiment, on the one hand, when the communication link where the RIU in any subsystem is located fails, selects the gateway node in other communication links as a new bridge, establishes wireless communication with the RIU in the failed communication link, and then establishes wireless communication with the protocol processing terminal in the failed communication link to restore the communication function of the failed communication link, thereby ensuring the normal communication of the communication link and ensuring the safe and stable operation of the aircraft. On the other hand, the RIU is used as a fault detection device. When the communication link where it is located fails, it can control the failed communication link to reconstruct the connection with the gateway nodes in other communication links to restore the communication function. When it is detected that the communication is restored in the original failed communication link, the reconstructed communication link is disconnected. In this way, it can ensure that the original functions of each original communication link are restored, avoid the concentration of a large amount of data on a certain gateway node, and reduce the load pressure of the gateway node. In addition, the communication path of the original communication link is shorter and the delay is less, which can improve the real-time response capability.

[0065] Corresponding to the aforementioned embodiment of an aircraft electromechanical system in-machine wireless communication system, the present application also provides an embodiment of an aircraft electromechanical system in-machine wireless communication method. The aircraft electromechanical system in-machine wireless communication method provided by the present application is introduced below:

[0066] Figure 3 Please refer to the flowchart of the wireless communication method for the aircraft electromechanical system provided in the second embodiment of the present application. Figure 3 The aircraft mechatronic system in-flight wireless communication method provided in this embodiment is implemented based on the aircraft mechatronic system in-flight wireless communication system in any one of the above embodiments; the aircraft mechatronic system in-flight wireless communication method includes:

[0067] S301, the active motion controller VMC receives the control instruction from the flight control computer, parses the control instruction, and obtains the destination address of the control instruction; wherein the destination address points to the target actuator in the front wheel turning control system, the rudder actuation system, and the spoiler electrostatic hydraulic actuation system.

[0068] S302. The VMC sends the control instruction to a target RIU in a target communication link where a target actuator pointed to by the destination address is located according to the destination address.

[0069] S303: The target RIU forwards the control instruction to a target gateway node in the target communication link.

[0070] S304. The target gateway node forwards the control instruction to the target protocol processing terminal of the communication link where the target gateway node is located according to the target address of the control instruction; wherein the target protocol processing terminal is a protocol processing terminal among all the protocol processing terminals in the communication link where the target gateway node is located, and is connected to the target actuator pointed to by the destination address through a bus.

[0071] S305: The target protocol processing terminal sends the control instruction to the target actuator connected to the target protocol processing terminal to instruct the target actuator to execute the control instruction.

[0072] The present application provides an in-flight wireless communication method for an aircraft electromechanical system, in which an aviation pilot issues a control instruction in a flight control computer, an active motion controller VMC receives the control instruction, and parses the control instruction to obtain a destination address of the control instruction, and the VMC sends the control instruction to a target RIU of a target communication link where a target actuator pointed to by the destination address is located, and then the control instruction is transmitted to a target gateway node through wireless communication via the target RIU, and then transmitted by the target gateway node to a target protocol processing terminal that establishes communication with the target gateway node, and then the target protocol processing terminal sends the target instruction to a target actuator that corresponds one-to-one with the target protocol processing terminal, instructing the target actuator to execute the control instruction.

[0073] Furthermore, the aircraft electromechanical system in-flight wireless communication method further includes:

[0074] The sensing processing unit collects status data, and transmits the collected status data to the VMC via the fourth communication link;

[0075] And / or, the actuator collects its own state parameters, and reports the collected state parameters to the VMC via the communication link where the actuator is located.

[0076] The in-flight wireless communication method for an aircraft electromechanical system provided in this embodiment collects aircraft status parameters through a sensing processing unit, and transmits the collected aircraft status data to the VMC through a fourth communication link, or collects its own status parameters through an actuator, and reports them to the VMC through the communication link where the actuator is located. After that, the VMC transmits all the collected status information to the flight control computer, and the aircraft pilot makes the next decision based on the transmitted status parameters. The high-speed transmission efficiency of wireless communication in the communication link can realize real-time transmission of control instructions and feedback status information, thereby ensuring the rapid response and control accuracy of the aircraft pilot to the aircraft flight control.

[0077] Optionally, in a possible implementation, when the target RIU detects that the communication link where the RIU is located has a fault, the target RIU reconstructs the communication link where the RIU is located to ensure smooth operation of the communication link where the RIU is located.

[0078] Specifically, the specific implementation principle and implementation process of reconstructing the communication link refer to the description in the previous embodiment, which will not be repeated here.

[0079] The in-flight wireless communication method for an aircraft mechatronic system provided in this embodiment can ensure smooth operation of the communication link where the RIU is located by reconstructing the communication link where the RIU is located when the target RIU detects a failure in the communication link where the RIU is located, thereby ensuring the real-time control of the aircraft by the aircraft pilot and enhancing the stability of the in-flight communication system of the aircraft mechatronic system.

[0080] The above description is only a preferred embodiment of the present application and is not intended to limit the present application. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application shall be included in the scope of protection of the present application.

Claims

1. An aircraft electromechanical system in-flight wireless communication system, characterized in that: The aircraft electromechanical system in-flight wireless communication system comprises an active motion controller VMC, and a first system, a second system, a third system and a fourth system respectively connected to the VMC via a bus; The VMC and the first system constitute a first communication link from the VMC to the front wheel turning actuation system, for realizing information interaction between the VMC and the front wheel turning actuation system; the VMC and the second system constitute a second communication link from the VMC to the rudder actuation system, for realizing information interaction between the VMC and the rudder actuation system; the VMC and the third system constitute a third communication link from the VMC to the spoiler electro-hydraulic actuation system, for realizing information interaction between the VMC and the spoiler electro-hydraulic actuation system; the VMC and the fourth system constitute a fourth communication link from the VMC to the perception processing unit, for realizing information interaction between the VMC and the perception processing unit; Any one of the first system, the second system, the third system and the fourth system comprises a remote interface unit RIU connected to the VMC via a bus, a gateway node wirelessly communicating with the RIU, at least one protocol processing terminal communicating with the gateway node, and at least one terminal device; wherein at least one terminal device in the first system, the second system and the third system is an actuator in an actuation system corresponding to the system, the number of protocol processing terminals in the first system, the second system and the third system is consistent with the number of actuators included in the actuation system corresponding to the system, and one protocol processing terminal is connected to one actuator; at least one terminal device in the fourth system is a perception processing unit, the number of protocol processing terminals in the fourth system is consistent with the number of perception processing units included in the system, and one protocol processing terminal is connected to one perception processing unit; Any RIU in the first system, the second system, the third system and the fourth system is further configured to reconstruct the communication link where the RIU is located when a failure of the communication link where the RIU is located is detected, so as to ensure smoothness of the communication link where the RIU is located; The reconstructing the communication link where the RIU is located includes: Selecting a gateway node from other communication links other than the communication link where the RIU is located as a target gateway node, and establishing a wireless communication connection with the target gateway node; Instruct the target gateway node to establish a wireless communication connection with the protocol processing terminal in the communication link where the RIU is located, so as to establish a communication link from the RIU to the target gateway node, and from the target gateway node to the protocol processing terminal in the communication link where the RIU is located, so as to reconstruct the communication link where the RIU is located through the target gateway node.

2. The aircraft electromechanical system in-flight wireless communication system according to claim 1, characterized in that: The sensing processing unit includes any one of the following sensors: a first type of sensor provided in a hydraulic system, a second type of sensor provided in a fuel system, and a third type of sensor provided in an environmental control system; The perception processing unit is used to collect status data and transmit the collected data to the VMC via the fourth communication link.

3. The aircraft electromechanical system in-flight wireless communication system according to claim 1, characterized in that: The selecting a gateway node as a target gateway node from other communication links other than the communication link where the RIU is located includes: A gateway node closest to the RIU is selected from all gateway nodes included in other communication links except the communication link where the RIU is located as the target gateway node.

4. The aircraft electromechanical system in-flight wireless communication system according to claim 1, characterized in that: The selecting a gateway node as a target gateway node from other communication links other than the communication link where the RIU is located includes: Selecting a gateway node with the strongest signal strength from all gateway nodes included in other communication links other than the communication link where the RIU is located as the target gateway node; or, A gateway node with the lightest load is selected from all gateway nodes included in other communication links except the communication link where the RIU is located as the target gateway node.

5. The aircraft electromechanical system in-flight wireless communication system according to claim 1, characterized in that: The first system includes a first RIU, a first gateway node in wireless communication with the first RIU, a first protocol processing terminal in wireless communication with the first gateway node, and an electromechanical actuator of a front wheel turning control system connected to the first protocol processing terminal via a bus; The second system includes a second RIU, a second gateway node in wireless communication with the second RIU, a first servo protocol processing terminal and a second servo protocol processing terminal in wireless communication with the second gateway node, and a first servo actuator of a rudder actuation system connected to the first servo protocol processing terminal via a bus and a second servo actuator of a rudder actuation system connected to the second servo protocol processing terminal via a bus; The third system includes a third RIU, a third gateway node that wirelessly communicates with the third RIU, a first clean liquid protocol processing terminal, a second clean liquid protocol processing terminal, a third clean liquid protocol processing terminal, and a fourth clean liquid protocol processing terminal that wirelessly communicates with the third gateway node, and a first electric clean liquid actuator of a spoiler electric clean liquid actuation system connected to the first clean liquid protocol processing terminal via a bus, a second electric clean liquid actuator of a spoiler electric clean liquid actuation system connected to the second clean liquid protocol processing terminal via a bus, a third electric clean liquid actuator of a spoiler electric clean liquid actuation system connected to the third clean liquid protocol processing terminal via a bus, and a fourth electric clean liquid actuator of a spoiler electric clean liquid actuation system connected to the fourth clean liquid protocol processing terminal via a bus.

6. A method for wireless communication within an aircraft electromechanical system, characterized in that: The aircraft electromechanical system in-machine wireless communication method is implemented based on the aircraft electromechanical system in-machine wireless communication system according to any one of claims 1 to 5; the aircraft electromechanical system in-machine wireless communication method comprises: The active motion controller VMC receives the control instruction from the flight control computer, parses the control instruction, and obtains the destination address of the control instruction; wherein the destination address points to the target actuator in the front wheel turning control system, the rudder actuation system, and the spoiler electro-hydraulic actuation system; The VMC sends the control instruction to the target RIU in the target communication link where the target actuator pointed to by the destination address is located according to the destination address; The target RIU forwards the control instruction to a target gateway node in the target communication link; The target gateway node forwards the control instruction to a target protocol processing terminal in the communication link where the target gateway node is located according to the target address of the control instruction; wherein the target protocol processing terminal is a protocol processing terminal among all the protocol processing terminals in the communication link where the target gateway node is located, and is connected to the target actuator pointed to by the destination address through a bus; The target protocol processing terminal sends the control instruction to the target actuator connected to the target protocol processing terminal to instruct the target actuator to execute the control instruction.

7. The method for in-flight wireless communication of an aircraft electromechanical system according to claim 6, characterized in that: The method for wireless communication within an aircraft electromechanical system further comprises: The sensing processing unit collects status data, and transmits the collected status data to the VMC via the fourth communication link; and / or, The actuator collects its own state parameters, and reports the collected state parameters to the VMC via the communication link where the actuator is located.

8. The method for in-flight wireless communication of an aircraft electromechanical system according to claim 6, characterized in that: The method for wireless communication within an aircraft electromechanical system further comprises: When the target RIU detects that the communication link where the RIU is located is faulty, the target RIU reconstructs the communication link where the RIU is located to ensure smooth operation of the communication link where the RIU is located.

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