CN212861887U - Multi-protocol interactive communication system of hybrid electric propulsion system of unmanned aerial vehicle - Google Patents
Multi-protocol interactive communication system of hybrid electric propulsion system of unmanned aerial vehicle Download PDFInfo
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- CN212861887U CN212861887U CN202021707561.2U CN202021707561U CN212861887U CN 212861887 U CN212861887 U CN 212861887U CN 202021707561 U CN202021707561 U CN 202021707561U CN 212861887 U CN212861887 U CN 212861887U
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Abstract
The utility model provides an interactive communication system of unmanned aerial vehicle hybrid electric propulsion system multiprotocol, this interactive communication system of multiprotocol includes: an unmanned hybrid electric propulsion system; a flight control system; the unmanned aerial vehicle hybrid electric propulsion system is in communication connection with the flight control system through the communication system; the communication system includes a main communication unit and a standby communication unit. In order to ensure the reliability of flight, the flight control system and the key signals of the hybrid electric propulsion system of the unmanned aerial vehicle are designed in a redundancy mode, and the unmanned aerial vehicle out of control caused by faults of a main communication unit is prevented.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle hybrid field, concretely relates to unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication system.
Background
Along with the wider application of microcontrollers in the field of power control, the electronization degree of a power system is higher and higher. In order to reduce cost and simplify wiring harness connection, various bus control technologies are adopted by various manufacturers to achieve the purpose of realizing complex real-time data exchange among a plurality of electronic control units, a bus is one of the most main bus protocols, and the bus has the characteristics of high transmission rate, low cost, reliable error processing and detection mechanisms and the like, so the bus is naturally widely applied to the field of power system control.
In the communication network in the prior art, the network nodes mainly comprise an engine electronic fuel injection control unit, a machine body control unit and the like. The network load is low, the communication requirement is not high, and only one layer of the diagnosis subnet is provided. Compared with the traditional power system, the hybrid power system has a large number of high-voltage components, such as high-voltage power batteries, motors, DC/DC (direct current/direct current) and other devices, so that serious interference can be generated on weak current devices of the hybrid power system, and various control signals are required to have strong anti-interference capability in the transmission process. Meanwhile, the hybrid system power assembly not only comprises an engine system, but also comprises an electric drive system, a battery management system and the like, so that a power assembly control system is very complex. The large increase of control nodes increases the information that the control devices of the power system need to exchange with each other, and the control of the power system is required to have high real-time performance. Therefore, the CAN bus becomes the inevitable choice for data communication of the hybrid system.
The application of the CAN bus in the hybrid power system is described in the patent publication No. 201811562751.7, which relates to the control method of the whole hybrid power system, but the above patent only adopts the CAN bus communication, and the single communication protocol CAN not ensure the safety and reliability of the key information transmission when the fault occurs.
Disclosure of Invention
In view of this, in order to guarantee the reliability of information transmission, avoid unmanned aerial vehicle out of control to damage when CAN bus communication trouble, this design has invented an unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication system.
The utility model discloses an aspect provides an unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication system, this multiprotocol interaction communication system includes:
an unmanned hybrid electric propulsion system;
a flight control system; and
the unmanned aerial vehicle hybrid electric propulsion system is in communication connection with the flight control system through the communication system;
the communication system includes a main communication unit and a standby communication unit.
Preferably, the main communication unit adopts a CAN communication mode; the standby communication unit adopts a PWM communication mode.
Preferably, the hybrid electric propulsion system of the unmanned aerial vehicle is connected with the flight control system through a CAN bus isolation chip ISO1050 and a common mode choke coil DLW43SH510XK2, and the CAN bus isolation chip ISO1050 and the common mode choke coil DLW43SH510XK2 form a main communication unit between the hybrid electric propulsion system of the unmanned aerial vehicle and the flight control system.
Preferably, the unmanned aerial vehicle hybrid electric propulsion system is connected with the flight control system through a PWM communication unit through an optocoupler tlp281, and the PWM communication unit forms a standby communication unit between the unmanned aerial vehicle hybrid electric propulsion system and the flight control system.
Preferably, the hybrid electric propulsion system of the drone comprises an internal communication system comprising an internal primary communication unit and an internal backup communication unit.
Preferably, the internal main communication unit adopts a CAN communication mode; and the internal standby communication unit adopts an RS485 communication mode.
Preferably, the unmanned hybrid electric propulsion system further comprises; an energy management system, an engine controller; an ISG controller; and a battery management system.
Preferably, the energy management system, the engine controller, the ISG controller and the battery management system are all connected with a CAN transceiver TLE6250GV33, and the energy management system, the engine controller, the ISG controller and the CAN transceiver TLE6250GV33 of the battery management system are connected in series by a bus to form an internal main communication unit of the hybrid electric propulsion system of the unmanned aerial vehicle.
Preferably, the energy management system, the engine controller, the ISG controller and the battery management system are all further connected with an isolated RS-485 chip ADM2582E, and the energy management system, the engine controller, the ISG controller and the isolated RS-485 chip ADM2582E of the battery management system are connected in series by a bus to form an internal auxiliary communication unit of the hybrid electric propulsion system of the unmanned aerial vehicle.
The utility model has the advantages and positive effects that: in order to ensure the reliability of flight, the flight control system and the key signals of the hybrid electric propulsion system of the unmanned aerial vehicle are designed in a redundancy mode. When the main communication unit fails in communication, the hybrid electric propulsion system can still acquire important information such as the pitch and the target rotating speed through the auxiliary communication unit.
Besides adopting an internal main communication unit, the hybrid electric propulsion system of the unmanned aerial vehicle also carries out redundancy design on key signals. When inside main communication unit breaks down, start inside supplementary communication unit, avoid unmanned aerial vehicle damage out of control.
Drawings
Fig. 1 is a schematic structural diagram of the multi-protocol interactive communication system of the hybrid electric propulsion system of the unmanned aerial vehicle of the present invention;
fig. 2 is a schematic circuit diagram of a communication system between the flight control system and the hybrid electric propulsion system of the unmanned aerial vehicle according to the present invention;
fig. 3 is a schematic circuit diagram of a communication method of the energy management unit according to the present invention;
fig. 4 is a schematic circuit diagram of a communication mode of the engine controller according to the present invention;
fig. 5 is a schematic circuit diagram of the communication method of the IGS controller according to the present invention;
fig. 6 is a schematic circuit diagram of a communication method of the engine controller according to the present invention;
FIG. 7 is a method of communication between a flight control system and an unmanned hybrid electric propulsion system;
fig. 8 is a communication method inside the hybrid electric propulsion system of the unmanned aerial vehicle.
Detailed Description
For a better understanding of the present invention, the following further description is given in conjunction with the following embodiments and accompanying drawings.
As shown in fig. 1, the utility model provides an unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication system, this multiprotocol interaction communication system includes: an unmanned hybrid electric propulsion system; a flight control system; the unmanned aerial vehicle hybrid electric propulsion system is in communication connection with the flight control system through the communication system; the communication system includes a main communication unit and a standby communication unit.
In the prior art, an unmanned aerial vehicle hybrid electric propulsion system and a flight control system generally adopt CAN bus communication, and a single communication protocol cannot ensure the safety and reliability of key information transmission when the unmanned aerial vehicle hybrid electric propulsion system and the flight control system break down; the utility model is provided with a main communication unit and a standby communication unit; the reliability of the system operation is guaranteed through the main communication unit and the standby communication unit.
Further, in a specific embodiment of the present invention, the main communication unit adopts a CAN communication mode already existing in the system; the standby communication unit adopts a PWM communication mode.
In order to ensure the reliability of flight, the flight control system and the key signals of the hybrid electric propulsion system of the unmanned aerial vehicle are designed in a redundancy mode. This signal adopts the PWM wave form, and unmanned aerial vehicle flight control system is one-way to the two ripples signals of hybrid electric propulsion system conveying PWM, through the definition to the electric potential duration in advance, when CAN bus communication trouble, hybrid electric propulsion system still CAN obtain important information such as thick liquid distance, target rotational speed through the PWM wave.
Further, unmanned aerial vehicle hybrid electric propulsion system includes an inside communication system, and this inside communication system includes an inside main communication unit and an inside reserve communication unit. The internal backup communication unit is activated when the internal primary communication unit fails.
Furthermore, the internal main communication unit adopts a CAN communication mode; and the internal standby communication unit adopts an RS485 communication mode.
The system utilizes the CAN bus to carry out the transmission of key signal, and RS485 serial ports communication CAN transmit key signal between each equipment when the CAN bus trouble, prevents that the unmanned aerial vehicle that the CAN bus trouble arouses from out of control.
Besides adopting a CAN bus, the hybrid electric propulsion system of the unmanned aerial vehicle also carries out redundancy design on key signals. The redundancy design adopts RS485 communication, adopts a twisted pair cable as a bus, connects all nodes in the hybrid electric propulsion system of the unmanned aerial vehicle in series, and works in a master-slave communication mode. Each line of RS485 communication in the system is short, interference of each reflected signal is small, and signal transmission reliability is guaranteed.
Therefore, the multi-protocol information interaction can meet the requirements of real-time communication among subsystems and signal transmission safety between the subsystems and other controllers.
In a specific embodiment of the present invention, the hybrid electric propulsion system of the unmanned aerial vehicle is connected to the flight control system through a CAN bus isolation chip ISO1050 and a common mode choke coil DLW43SH510XK2, the CAN bus isolation chip ISO1050 and the common mode choke coil DLW43SH510XK2 constitute a main communication unit between the hybrid electric propulsion system of the unmanned aerial vehicle and the flight control system; meanwhile, the unmanned aerial vehicle hybrid electric propulsion system is in PWM communication connection with the flight control system through an optocoupler tlp281, and the PWM communication unit forms a standby communication unit between the unmanned aerial vehicle hybrid electric propulsion system and the flight control system; when the main communication unit fails, the optocoupler tlp281 is triggered, and the standby communication unit is started to communicate.
Further, in this embodiment, the unmanned hybrid electric propulsion system further comprises; the energy management system is used for controlling the engine; an ISG controller and a battery management system; the energy management system and the flight control system are in communication connection through the main communication unit and the standby communication unit; and the energy management system is respectively in communication connection with the engine controller, the ISG controller and the battery management system through the internal main communication unit and the standby communication unit.
Specifically, the energy management system, the engine controller, the ISG controller and the battery management system are all connected with a CAN transceiver TLE6250GV33, and the energy management system, the engine controller, the ISG controller and the CAN transceiver TLE6250GV33 of the battery management system are connected in series by adopting a bus to form an internal main communication unit of the hybrid electric propulsion system of the unmanned aerial vehicle; the energy management system, the engine controller, the ISG controller and the battery management system are all further connected with an isolated RS-485 chip ADM2582E, and the energy management system, the engine controller, the ISG controller and the isolated RS-485 chip ADM2582E of the battery management system are connected in series by a bus to form an internal auxiliary communication unit of the hybrid electric propulsion system of the unmanned aerial vehicle.
The utility model discloses a two independent CAN communication module are main communication unit and inside main communication unit promptly. The CAN bus data communication has no master-slave division, any node CAN initiate data communication to any other node(s), the communication order is determined according to the priority order of the information of each node, the information of the node with high priority is communicated in 134 mu s, and when a plurality of nodes of the CAN initiate communication at the same time, the node with low priority has high avoidance priority and CAN not cause congestion to a communication line; meanwhile, the CAN bus transmission medium CAN be a twisted-pair coaxial cable, the CAN bus is suitable for large-data-volume short-distance communication or long-distance small-data-volume communication, and the real-time performance of signal transmission CAN be guaranteed. Two CAN buses are respectively applied between the hybrid electric propulsion system of the unmanned aerial vehicle and the flight control system and inside the hybrid electric propulsion system of the unmanned aerial vehicle, so that the interference generated by information interaction among multiple devices is prevented.
The utility model discloses another aspect provides an unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication method, unmanned aerial vehicle hybrid electric propulsion system and flight control system set up and realize the communication connection through main communication unit and reserve communication unit; when the main communication unit works normally, the information transmission is realized through the main communication unit; when the main communication unit fails, the standby communication unit is started.
The main communication unit adopts a CAN communication mode, and the standby communication unit adopts a PWM communication mode; when the main communication unit works normally, the CAN communication mode of the main communication unit transmits all information; when the main communication unit breaks down, the PWM communication transmits key information, and non-key information adopts default values.
Furthermore, an internal communication system of the hybrid electric propulsion system of the unmanned aerial vehicle comprises an internal main communication unit and an internal standby communication unit, and all nodes of the hybrid electric propulsion system of the unmanned aerial vehicle are in communication connection through the internal main communication unit and the internal standby communication unit; when the internal main communication unit works normally, the information transmission is realized through the internal main communication unit; when the internal main communication unit fails, the internal standby communication unit is started.
The internal main communication unit adopts a CAN communication mode, and the internal standby communication unit adopts an RS485 communication mode; when the internal main communication unit works normally, the CAN communication mode of the internal main communication unit transmits all information; when the internal main communication unit breaks down, the RS485 communication mode transmits key information, and non-key information adopts default values.
The embodiments of the present invention have been described in detail, but the description is only for the preferred embodiments of the present invention and should not be construed as limiting the scope of the present invention. All equivalent changes and modifications made within the scope of the present invention should be covered by the present patent.
Claims (9)
1. The utility model provides an unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication system which characterized in that: the multi-protocol interactive communication system comprises:
an unmanned hybrid electric propulsion system;
a flight control system; and
the unmanned aerial vehicle hybrid electric propulsion system is in communication connection with the flight control system through the communication system;
the communication system includes a main communication unit and a standby communication unit.
2. The unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication system of claim 1, characterized in that: the main communication unit adopts a CAN communication mode; the standby communication unit adopts a PWM communication mode.
3. The unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication system of claim 1 or 2, characterized in that: the hybrid electric propulsion system of the unmanned aerial vehicle is connected with the flight control system through a CAN bus isolation chip ISO1050 and a common mode choke coil DLW43SH510XK2, and the CAN bus isolation chip ISO1050 and the common mode choke coil DLW43SH510XK2 form a main communication unit between the hybrid electric propulsion system of the unmanned aerial vehicle and the flight control system.
4. The unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication system of claim 1 or 2, characterized in that: the unmanned aerial vehicle hybrid electric propulsion system is connected with the flight control system through PWM communication between an optocoupler tlp281, and the PWM communication unit forms a standby communication unit between the unmanned aerial vehicle hybrid electric propulsion system and the flight control system.
5. The unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication system of claim 3, characterized in that: unmanned aerial vehicle hybrid electric propulsion system includes an internal communication system, and this internal communication system includes an inside main communication unit and an inside reserve communication unit.
6. The unmanned aerial vehicle hybrid electric propulsion system multi-protocol interactive communication system of claim 5, characterized in that: the internal main communication unit adopts a CAN communication mode; and the internal standby communication unit adopts an RS485 communication mode.
7. An unmanned aerial vehicle hybrid electric propulsion system multiprotocol interaction communication system according to claim 5 or 6, characterized in that: the hybrid electric propulsion system of the unmanned aerial vehicle also comprises; an energy management system, an engine controller; an ISG controller; and a battery management system.
8. The unmanned aerial vehicle hybrid electric propulsion system multi-protocol interactive communication system of claim 7, wherein: the energy management system, the engine controller, the ISG controller and the battery management system are all connected with a CAN transceiver TLE6250GV33, and the energy management system, the engine controller, the ISG controller and the CAN transceiver TLE6250GV33 of the battery management system are connected in series by adopting a bus to form an internal main communication unit of the hybrid electric propulsion system of the unmanned aerial vehicle.
9. The unmanned aerial vehicle hybrid electric propulsion system multi-protocol interactive communication system of claim 7, wherein: the energy management system, the engine controller, the ISG controller and the battery management system are all further connected with an isolated RS-485 chip ADM2582E, and the energy management system, the engine controller, the ISG controller and the isolated RS-485 chip ADM2582E of the battery management system are connected in series by a bus to form an internal auxiliary communication unit of the hybrid electric propulsion system of the unmanned aerial vehicle.
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