An unmanned aerial vehicle inspires electricity integrated control system

Abstract

The application relates to the technical field of unmanned aerial vehicle control, and discloses an unmanned aerial vehicle starting and power generation integrated control system which comprises a communication interface, a control circuit, a driving circuit, a starting and power generation integrated motor and a power circuit; the control circuit is respectively connected with the communication interface, the driving circuit and the starting and power generation integrated motor in a signal mode; the communication interface comprises an ignition signal end, a CAN communication interface and an RS232 communication interface; the control circuit is used for receiving ignition signals and CAN and RS232 communication signals; the driving circuit is respectively connected with the control circuit and the starting and power generation integrated motor in an electrical mode, is used for receiving signals of the control circuit and is used for switching between a starting mode and a power generation mode; and the power circuit is respectively connected with the starting and power generation integrated motor, an unmanned aerial vehicle load and an ECU7 in an electrical mode. After the above structure is adopted, the application has the following advantages: the application integrates starting and power generation, simplifies the structure, reduces weight, improves efficiency, has multi-path communication and state detection, realizes stable mode switching and is reliable in power supply.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) control technology, and in particular to an integrated heuristic and electro-hydraulic control system for UAVs. Background Technology

[0002] In existing UAV power systems, the starter motor and generator are mostly independent, separate structures, resulting in low system integration, large overall size and weight, complex wiring, and high space occupancy. Furthermore, the separate structure easily leads to fragmented control logic and unsmooth switching between operating modes, making it difficult to meet the lightweight, integrated, and highly reliable requirements of UAVs. In addition, traditional control systems rely on limited communication methods and inadequate motor status monitoring, failing to provide a stable and reliable power supply to the UAV's load and ECU, thus hindering the overall operational stability of the UAV.

[0003] To address the shortcomings of existing technologies, this invention provides an integrated start-up and power generation control system for unmanned aerial vehicles (UAVs). This system integrates start-up and power generation functions, has a compact structure, operates stably, can reliably switch modes and detect motor status, and stably supplies power to the UAV load and ECU. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention provides an integrated start-up and power generation control system for unmanned aerial vehicles (UAVs). This system integrates start-up and power generation functions, has a compact structure, operates stably, can reliably switch modes and detect motor status, and stably supplies power to the UAV load and ECU.

[0005] To solve the above-mentioned technical problems, the technical solution provided by the present invention is: an integrated heuristic and motor control system for unmanned aerial vehicles, including a communication interface, a control circuit, a drive circuit, an integrated heuristic motor, and a power circuit;

[0006] The control circuit is connected to the communication interface, the drive circuit, and the integrated starter motor. The communication interface includes an ignition signal terminal, a CAN communication interface, and an RS232 communication interface. The control circuit is used to receive the ignition signal and the CAN and RS232 communication signals, and to detect the working status of the integrated starter motor to determine whether it is working properly.

[0007] The drive circuit is electrically connected to the control circuit and the integrated starter motor respectively. It is used to receive signals from the control circuit and switch between the start-up mode and the power generation mode. When the integrated starter motor control system is in normal state, it outputs the corresponding drive signal to the integrated starter motor according to the determined working mode.

[0008] The power circuit is electrically connected to the integrated starter motor, the drone load, and the ECU, respectively, and is used to convert the electrical energy generated by the integrated starter motor to power the drone load and the ECU.

[0009] As an improvement, the control circuit achieves data interaction with the UAV host computer or external control unit through the CAN communication interface and RS232 communication interface in the communication interface.

[0010] As an improvement, the drive circuit automatically switches between the start-up mode and the power generation mode based on the detection results of the integrated starter motor by the control circuit and external commands.

[0011] As an improvement, the power circuit includes a power conversion unit for converting the AC or frequency converter output from the integrated starter motor into regulated DC power adapted to the drone load and ECU.

[0012] As an improvement, after receiving the ignition signal, the control circuit first performs a status self-check on the integrated starter motor, and only allows the drive circuit to enter the start mode or power generation mode after the self-check passes.

[0013] As an improvement, the drive circuit outputs a start drive signal in start mode to control the starter motor to start the internal combustion engine, and outputs an excitation adjustment signal in generator mode to control the starter motor to enter the generator state.

[0014] As an improvement, the power circuit also has a built-in voltage protection unit, which cuts off the power supply when the output voltage exceeds a set threshold, in order to protect the drone load and ECU.

[0015] With the above structure, the present invention has the following advantages:

[0016] The system adopts an integrated starter motor, which integrates the starting and power generation functions into one unit, simplifying the system structure, reducing size and weight, and improving the space utilization and lightweight level of the drone.

[0017] The control circuit has the functions of ignition signal reception, multi-channel communication and motor status detection. The system has high reliability and faults can be identified in advance.

[0018] The drive circuit can achieve stable switching between startup and power generation modes, with clear control logic and rapid response;

[0019] The power circuit can directly power the drone's load and ECU. The power supply link is simple and highly stable, meeting the power supply requirements of the drone's onboard equipment. Attached Figure Description

[0020] Figure 1 This is an overall structural block diagram of an integrated heuristic and electro-hydraulic control system for unmanned aerial vehicles (UAVs) according to the present invention.

[0021] As shown in the figure: 1. Communication interface; 2. Control circuit; 3. Drive circuit; 4. Integrated starter motor; 5. Power circuit; 6. UAV load; 7. ECU. Detailed Implementation

[0022] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0023] As attached Figure 1 As shown, a drone-inspired motor integrated control system includes a communication interface 1, a control circuit 2, a drive circuit 3, an integrated motor 4, and a power circuit 5.

[0024] The control circuit 2 is connected to the communication interface 1, the drive circuit 3, and the integrated starter motor 4 via signals. The communication interface 1 includes an ignition signal terminal, a CAN communication interface, and an RS232 communication interface. The control circuit 2 interacts with the UAV host computer or an external control unit through the CAN and RS232 communication interfaces in the communication interface 1. The control circuit 2 receives the ignition signal and the CAN and RS232 communication signals, and detects the working status of the integrated starter motor 4 to determine whether it is working properly. After receiving the ignition signal, the control circuit 2 first performs a status self-check on the integrated starter motor 4, and only allows the drive circuit 3 to enter the start-up mode or the power generation mode after the self-check passes.

[0025] The drive circuit 3 is electrically connected to both the control circuit 2 and the integrated starter-motor 4. It receives signals from the control circuit 2 and switches between start-up and power generation modes. The drive circuit 3 automatically switches between start-up and power generation modes based on the control circuit 2's detection results of the integrated starter-motor 4 and external commands. When the integrated starter-motor control system is in normal operation, it outputs a corresponding drive signal to the integrated starter-motor 4 according to the determined operating mode. In start-up mode, the drive circuit 3 outputs a start-up drive signal to control the integrated starter-motor 4 to start the internal combustion engine; in power generation mode, it outputs an excitation adjustment signal to control the integrated starter-motor 4 to enter the power generation state.

[0026] The power circuit 5 is electrically connected to the integrated starter motor 4, the drone load 6, and the ECU 7, respectively, and is used to convert the electrical energy generated by the integrated starter motor 4 to power the drone load 6 and the ECU 7. The power circuit 5 includes a power conversion unit, which converts the AC or frequency-converted power output from the integrated starter motor 4 into regulated DC power adapted to the drone load 6 and the ECU 7. The power circuit 5 also has a built-in voltage protection unit, which cuts off the power supply when the output voltage exceeds a set threshold to protect the drone load 6 and the ECU 7.

[0027] In actual operation, after receiving the ignition signal, the control circuit 2 first performs a status self-check on the integrated starter motor 4. Only after the self-check passes is the drive circuit 3 allowed to enter the start-up mode or power generation mode. Simultaneously, the control circuit 2 interacts with the UAV host computer or external control unit via CAN and RS232 communication signals. After determining the operating mode, the drive circuit 3 switches to the corresponding mode and outputs a drive signal. After the integrated starter motor 4 starts operating, the power circuit 5 converts electrical energy and supplies it to the UAV load 6 and ECU 7, achieving integrated start-up and power generation control.

[0028] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0029] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

[0030] The present invention and its embodiments have been described above. This description is not restrictive, and the accompanying drawings are only one embodiment of the present invention; the actual structure is not limited thereto. In conclusion, if those skilled in the art are inspired by this description and design similar structures and embodiments without departing from the spirit of the invention, such designs should fall within the protection scope of the present invention.

Claims

1. A heuristic-electric integrated control system for unmanned aerial vehicles (UAVs), characterized in that, It includes a communication interface (1), a control circuit (2), a drive circuit (3), an integrated starter motor (4), and a power circuit (5); The control circuit (2) is connected to the communication interface (1), the drive circuit (3) and the starter motor (4) respectively. The communication interface (1) includes an ignition signal terminal, a CAN communication interface and an RS232 communication interface. The control circuit (2) is used to receive the ignition signal and the CAN and RS232 communication signals, and to detect the working status of the starter motor (4) to determine whether it is working properly. The drive circuit (3) is electrically connected to the control circuit (2) and the integrated motor (4) respectively, and is used to receive the signal from the control circuit (2) and switch between the start-up mode and the power generation mode. When the integrated motor control system is in normal state, it outputs the corresponding drive signal to the integrated motor (4) according to the determined working mode. The power circuit (5) is electrically connected to the integrated starter motor (4), the drone load (6) and the ECU (7) respectively, and is used to convert the electrical energy generated by the integrated starter motor (4) to power the drone load (6) and the ECU (7).

2. The unmanned aerial vehicle (UAV) heuristic-electric integrated control system according to claim 1, characterized in that: The control circuit (2) achieves data interaction with the UAV host computer or external control unit through the CAN communication interface and RS232 communication interface in the communication interface (1).

3. The unmanned aerial vehicle (UAV) heuristic-electric integrated control system according to claim 1, characterized in that: The drive circuit (3) automatically switches between the start-up mode and the power generation mode based on the detection results of the integrated motor (4) by the control circuit (2) and external commands.

4. The unmanned aerial vehicle (UAV) heuristic-electric integrated control system according to claim 1, characterized in that: The power circuit (5) includes a power conversion unit, which is used to convert the AC or frequency conversion power output by the integrated starter motor (4) into regulated DC power adapted to the UAV load (6) and ECU (7).

5. The unmanned aerial vehicle (UAV) heuristic-electric integrated control system according to claim 1, characterized in that: After receiving the ignition signal, the control circuit (2) first performs a status self-check on the integrated starter motor (4), and only allows the drive circuit (3) to enter the start-up mode or power generation mode after the self-check is passed.

6. The unmanned aerial vehicle (UAV) heuristic-electric integrated control system according to claim 1, characterized in that: The drive circuit (3) outputs a start drive signal in the start mode to control the starter motor (4) to start the internal combustion engine, and outputs an excitation regulation signal in the power generation mode to control the starter motor (4) to enter the power generation state.

7. The unmanned aerial vehicle (UAV) heuristic-electric integrated control system according to claim 1, characterized in that: The power circuit (5) also has a built-in voltage protection unit, which is used to cut off the power supply when the output voltage exceeds the set threshold, so as to protect the drone load (6) and ECU (7).

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