Testing device for electrical system of unmanned aerial vehicle

Abstract

The utility model provides an unmanned aerial vehicle electrical system testing device, which relates to the technical field of unmanned aerial vehicle ground testing and comprises a cabinet body, and an alternating current power supply unit, a direct current power supply unit, an electronic load unit, a storage battery unit, a power supply conversion device, an electromechanical computer, a primary power distribution device and an industrial personal computer are arranged in the cabinet body. The AC power supply unit simulates the output of an onboard AC generator of the unmanned aerial vehicle; the DC power supply unit simulates the output of onboard low-voltage DC and high-voltage DC generators of the unmanned aerial vehicle. The primary power distribution device is used for energy distribution of the unmanned aerial vehicle electrical system testing device; the electronic load unit comprises an electronic load module and a load management device; the storage battery unit comprises a storage battery module and a storage battery management module; the industrial personal computer is connected with the direct-current power supply unit, the alternating-current power supply unit, the electronic load unit and the electromechanical computer; the problems of complex test accompanying system, low test equipment integration level and inconvenient parameter adjustment during ground test of the unmanned aerial vehicle in the prior art are solved.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicle (UAV) ground testing, and more specifically, relates to a testing device for the electrical system of a UAV. Background Art

[0002] At present, with the rapid development of UAV technology, the power supply and distribution system of UAVs is becoming more and more complex, and the reliability requirements are getting higher and higher. Therefore, it is necessary to conduct detailed ground tests on the electrical systems of UAVs, including the function and performance tests of single machines and systems. However, conventional ground tests require large-scale accompanying test equipment such as generator driving platforms and loads, and can only be manually adjusted, making it difficult to simulate the actual operating conditions on board.

[0003] Therefore, there is a need for an electrical system test platform with high integration, convenient software loading, and strong expandability, which does not require dragging generators, loads, etc., is convenient for loading software to complete real-time adjustment of parameters at the power supply end and load end, and can simulate the actual power supply and power consumption conditions on board, so as to complete the tests of the functions of the power supply and distribution single machines and systems of UAVs. Summary of the Utility Model

[0004] The purpose of the utility model is to provide a testing device for the electrical system of a UAV to solve the problems of complex accompanying test systems, low integration of test equipment, and inconvenient parameter adjustment in the prior art when conducting ground tests on UAVs.

[0005] To achieve the above purpose, the utility model provides a testing device for the electrical system of a UAV, including:

[0006] A cabinet body, in which an AC power supply unit, a DC power supply unit, an electronic load unit, a battery unit, a power conversion device, an electromechanical computer, a primary power distribution device, and an industrial control computer are arranged;

[0007] The AC power supply unit is provided with a first power input interface and is used to convert the alternating current input through the first power input interface into three-phase alternating current to simulate the output of the on-board AC generator of the UAV;

[0008] The power conversion device is connected between the AC power supply unit and the primary power distribution device. The AC power supply unit supplies power to the power conversion device, and the power conversion device is used to convert the three-phase alternating current output by the AC power supply unit into a DC power supply with a set voltage and supply power to the primary power distribution device;

[0009] The DC power supply unit is provided with a second power input interface and is used to convert the alternating current input through the second power input interface into direct current to simulate the output of the on-board low-voltage DC and high-voltage DC generators of the UAV;

[0010] The primary power distribution device is connected to the DC power supply unit, and the DC power supply unit supplies power to the primary power distribution device, which is used for the energy distribution of the UAV electrical system test device;

[0011] The electronic load unit includes an electronic load module and a load management device. The electronic load module is used to simulate the on-board electrical equipment of the UAV and convert the electrical energy passing through the primary power distribution device and the load management device into heat;

[0012] The battery unit includes a battery module and a battery management module. The battery module is used as the on-board emergency power supply of the UAV, and the battery management module is used to charge and control the temperature of the battery module;

[0013] The electromechanical computer is connected to the battery unit, the load management device, the power conversion device, and the primary power distribution device, and is used to transmit the data of the battery unit, the load management device, the power conversion device, and the primary power distribution device to the industrial control computer, and transmit the control instructions of the industrial control computer to the battery unit, the load management device, and the primary power distribution device;

[0014] The industrial control computer is connected to the DC power supply unit, the AC power supply unit, the electronic load unit, and the electromechanical computer. The industrial control computer includes a CAN bus board, and the CAN bus board is connected to the battery unit, the primary power distribution device, and the load management device.

[0015] Optionally, the load management device is connected between the primary power distribution device and the electronic load module, and the load management device includes a solid-state controllable switch with a protection function.

[0016] Optionally, the first power input interface and the second power input interface are connected to the 380V / 50Hz AC power supply from outside the cabinet.

[0017] Optionally, the three-phase alternating current is three-phase alternating current with adjustable output frequency, amplitude, and phase, and the rated power of the three-phase alternating current is 6kW.

[0018] Optionally, the voltage of the direct current is 0 - 400V, and the rated power of the direct current is 6kW.

[0019] Optionally, the battery module includes a lithium-ion battery and a temperature sensor and a heating component arranged inside the lithium-ion battery.

[0020] Optionally, the battery management module includes a charger adapted to the lithium-ion battery, a battery heating detection and control circuit, a battery health status monitoring component, a battery health status alarm component, and a battery circuit cut-off component.

[0021] Optionally, the set voltage is 28V. The power conversion device includes a rectification, transformation, and filtering component, an over-current, over-voltage, and over-temperature protection component, and is provided with a current equalization interface and can communicate through the CAN bus.

[0022] Optionally, the industrial control computer includes 3 functional boards, a 2-channel CAN bus board, an 8-channel RS422 / RS485 board, a 32-channel IO input / output board, and an extended function board. The extended function board communicates with the bottom board of the industrial control computer through a PCIe interface, and the display screen is interconnected with the industrial control computer through an HDMI interface.

[0023] Optionally, a plurality of mounting bottom boards are arranged inside the cabinet. The plurality of mounting bottom boards divide the internal space of the cabinet into a plurality of mounting spaces. The AC power supply unit, the DC power supply unit, the electronic load unit, the battery unit, the power conversion device, the electromechanical computer, the primary power distribution device, and the industrial control computer are distributed in the plurality of mounting spaces.

[0024] The present utility model provides a drone electrical system testing device, and its beneficial effects are as follows: The drone electrical system testing device integrates an AC power supply unit, a DC power supply unit, an electronic load unit, a battery unit, a power conversion device, an electromechanical computer, a primary power distribution device, and an industrial control computer inside the cabinet, with a high degree of integration. Through the settings of the AC power supply unit and the DC power supply unit, the device only needs to externally provide 380V alternating current as the power supply, effectively improving the convenience and working efficiency of the device testing. The setting of the industrial control computer makes it convenient for the device to carry human-computer interaction software and improves the convenience of parameter adjustment.

[0025] Other features and advantages of the present utility model will be described in detail in the subsequent specific implementation part. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] By describing the exemplary embodiments of the present utility model in more detail in conjunction with the drawings, the above-mentioned and other objects, features, and advantages of the present utility model will become more obvious. Among them, in the exemplary embodiments of the present utility model, the same reference numerals generally represent the same components.

[0027] Figure 1 FIG. shows a three-dimensional structural schematic diagram of a drone electrical system testing device according to an embodiment of the present utility model.

[0028] Figure 2The front view structural schematic diagram of a testing device for an unmanned aerial vehicle electrical system according to an embodiment of the present utility model is shown.

[0029] Figure 3 The connection relationship schematic diagram of a testing device for an unmanned aerial vehicle electrical system according to an embodiment of the present utility model is shown.

[0030] Description of the reference numerals:

[0031] 1. Cabinet; 2. AC power supply unit; 3. DC power supply unit; 4. Electronic load module; 5. Load management device; 6. Battery module; 7. Battery management module; 8. Power conversion device; 9. Electromechanical computer; 10. Primary power distribution device; 11. Industrial control computer; 12. Installation base plate; 13. Caster. Detailed implementation manners

[0032] The preferred implementation manners of the present utility model will be described in more detail below. Although the preferred implementation manners of the present utility model are described below, it should be understood that the present utility model can be implemented in various forms and should not be limited by the implementation manners described herein. On the contrary, these implementation manners are provided to make the present utility model more thorough and complete, and to be able to fully convey the scope of the present utility model to those skilled in the art.

[0033] As Figures 1 to 3 shown, the present utility model provides a testing device for an unmanned aerial vehicle electrical system, including:

[0034] Cabinet 1, in which an AC power supply unit 2, a DC power supply unit 3, an electronic load unit, a battery unit, a power conversion device 8, an electromechanical computer 9, a primary power distribution device 10 and an industrial control computer 11 are arranged;

[0035] The AC power supply unit 2 is provided with a first power input interface and is used for converting the alternating current input through the first power input interface into three-phase alternating current to simulate the output of the on-board AC generator of the unmanned aerial vehicle;

[0036] The power conversion device 8 is connected between the AC power supply unit 2 and the primary power distribution device 10. The AC power supply unit 2 supplies power to the power conversion device 8. The power conversion device 8 is used for converting the three-phase alternating current output by the AC power supply unit 2 into a DC power supply with a set voltage and supplying power to the primary power distribution device 10;

[0037] The DC power supply unit 3 is provided with a second power input interface and is used for converting the alternating current input through the second power input interface into direct current to simulate the output of the on-board low-voltage DC and high-voltage DC generators of the unmanned aerial vehicle;

[0038] The primary power distribution device 10 is connected to the DC power supply unit 3, and the DC power supply unit 3 supplies power to the primary power distribution device 10. The primary power distribution device 10 is used for the energy distribution of the UAV electrical system test device;

[0039] The electronic load unit includes an electronic load module 4 and a load management device 5. The electronic load module 4 is used to simulate the on-board electrical equipment of the UAV and convert the electrical energy passing through the primary power distribution device 10 and the load management device 5 into heat;

[0040] The battery unit includes a battery module 6 and a battery management module 7. The battery module 6 is used as the on-board emergency power supply of the module UAV, and the battery management module 7 is used to charge and control the temperature of the battery module 6;

[0041] The electromechanical computer 9 is connected to the battery unit, the load management device 5, the power conversion device 8 and the primary power distribution device 10, and is used to transmit the data of the battery unit, the load management device 5, the power conversion device 8 and the primary power distribution device 10 to the industrial control computer 11, and transmit the control instructions of the industrial control computer 11 to the battery unit, the load management device 5 and the primary power distribution device 10;

[0042] The industrial control computer 11 is connected to the DC power supply unit 3, the AC power supply unit 2, the electronic load unit and the electromechanical computer 9. The industrial control computer 11 includes a CAN bus board, and the CAN bus board is connected to the battery unit, the primary power distribution device 10 and the load management device 5.

[0043] Specifically, to solve the problems of complex accompanying test systems, low integration of test equipment, and inconvenient parameter adjustment in the prior art when the UAV is tested on the ground; the UAV electrical system test device provided by the present invention integrates the AC power supply unit 2, the DC power supply unit 3, the electronic load unit, the battery unit, the power conversion device 8, the electromechanical computer 9, the primary power distribution device 10 and the industrial control computer 11 in the cabinet 1, with high integration. By setting the AC power supply unit 2 and the DC power supply unit 3, the device only needs to provide 380V AC power externally as the power source, effectively improving the convenience and working efficiency of the device test. The setting of the industrial control computer 11 makes it convenient for the device to carry human-computer interaction software and improves the convenience of parameter adjustment.

[0044] In this embodiment, the AC power supply unit 2 can complete the power output with an amplitude of 0-180Vac and a frequency of 300-800Hz, so as to meet the test of airborne products.

[0045] Optionally, the load management device 5 is connected between the primary power distribution device 10 and the electronic load module 4, and the load management device 5 includes a solid-state controllable switch with protection function.

[0046] Specifically, the electronic load module 4 simulates the electrical equipment on the aircraft, converting the electrical energy passing through the primary power distribution device 10 and the load management device 5 into heat for consumption, thereby verifying the functions and performance of the power supply and power distribution system; the load management device 5 is a protection device for the power distribution system, isolating the power supply end from the electrical equipment end of the unmanned aircraft through the load management device 5. The load management device 5 has a solid-state controllable switch with protection functions, and can set the protection curve according to the characteristics of the subsequent electrical equipment. When an electrical equipment fails, the faulty equipment is removed from the bus, thus ensuring the safety of the power grid.

[0047] In this embodiment, the electronic load module 4 can complete the regulation of modes such as isolated constant power, constant current, and constant resistance, simulating different types of loads on the aircraft, such as resistive loads, inductive loads, capacitive loads, etc., making the ground test process more in line with the actual working conditions.

[0048] Optionally, the first power input interface and the second power input interface are connected to a 380V / 50Hz AC power supply from outside the cabinet 1.

[0049] Specifically, the 380V / 50Hz AC power supply can be input into the unmanned aircraft electrical system test device through the first power input interface and the second power input interface, serving as the only electrical energy input, which is very convenient to use.

[0050] Optionally, the three-phase alternating current is three-phase alternating current with adjustable output frequency, amplitude, and phase, and the rated power of the three-phase alternating current is 6kW.

[0051] Specifically, the AC power supply unit 2 can complete the power output with an amplitude of 0 - 180Vac and a frequency of 300 - 800Hz, thus meeting the test requirements of airborne products.

[0052] Optionally, the voltage of the direct current is 0 - 400V, and the rated power of the direct current is 6kW.

[0053] Specifically, the DC power supply unit 3 has an adjustable output voltage of 0 - 400V and a power of 6 kilowatts, meeting the test requirements of various DC devices and loads.

[0054] Optionally, the battery module 6 includes a lithium-ion battery and a temperature sensor and a heating component arranged inside the lithium-ion battery.

[0055] Specifically, the lithium-ion battery, as the core component of the battery module 6, is used to store electrical energy. The temperature sensor is used to detect the temperature of the lithium-ion battery, and based on the temperature detection result, it can conveniently control the operation of the heating component to ensure the performance of the battery in a low-temperature environment.

[0056] In this embodiment, the battery module 6 is equipped with a 7S lithium-ion battery, which is a 18650-type battery, with an output voltage of 21 - 29.4V, a capacity of 60Ah, and serves as the emergency power supply on the simulator. When the main generator or main power supply of the UAV fails, the emergency power supply continues to supply power to the on-board equipment to ensure the smooth return of the UAV. At the same time, in order to ensure the performance of the battery at low temperatures, the battery is internally equipped with 3 groups of Pt1000 temperature sensors and 2 groups of heating belt devices, which cooperate with the charger to complete the temperature detection and temperature control of the battery module 6.

[0057] Optionally, the battery management module 7 includes a charger adapted to the lithium-ion battery, a battery heating detection and control circuit, a battery health status monitoring component, a battery health status alarm component, and a battery circuit cut-off component.

[0058] Specifically, the battery management module 7 charges the battery module 6, and the charging mode is constant current - constant voltage charging, which completes the acquisition and feedback of the charging, discharging parameters, and single-cell parameters of the battery module 6. At the same time, the battery management module 7 is equipped with a battery heating detection and control circuit to ensure that the low-temperature characteristics of the battery meet the usage requirements.

[0059] Optionally, the set voltage is 28V. The power conversion device 8 includes a rectifier, transformer, and filter component, an over-current, over-voltage, and over-temperature protection component, and is provided with a current equalization interface and can communicate through the CAN bus.

[0060] Specifically, the power conversion device 8 converts the alternating current output by the AC power supply into a 28V DC power supply through rectification, filtering, and voltage stabilization, and provides power for the primary distribution device, the load management device 5, and other remaining equipment to ensure the normal operation of the system.

[0061] In this embodiment, the electromechanical computer 9 is used to implement functions such as communication control, data transmission, parameter acquisition, and system protection of the system under test equipment. The electromechanical computer 9 is connected to on-board analog devices such as the battery unit, the load management device 5, and the primary power distribution device 10 through the CAN bus. At the same time, the electromechanical computer 9 collects parameters such as system voltage, current, and temperature through the analog acquisition interface. The electromechanical computer 9 serves as the communication and control relay of the system. After collecting and packing the data of the on-board analog devices, it sends the data to the industrial control computer 11 through the RS422 interface for status display. At the same time, it receives the instructions sent by the industrial control computer 11, parses the instructions, and sends them to each execution device through the CAN bus.

[0062] In this embodiment, the primary power distribution device 10 is the energy distribution center of the UAV electrical system test device, responsible for the input, output, busbar switching and protection of various power supplies, and the acquisition of power supply parameters.

[0063] Optionally, the industrial control computer 11 includes three functional boards, a 2-channel CAN bus board, an 8-channel RS422 / RS485 board, a 32-channel IO input / output board, and an expansion function board. The expansion function board communicates with the baseboard of the industrial control computer 11 through a PCIe interface, and the display screen is interconnected with the industrial control computer 11 through an HDMI interface.

[0064] Specifically, the industrial control computer 11 is responsible for the communication and control of the on-board co-testing equipment. The on-board co-testing equipment includes a DC power supply unit 3, an AC power supply unit 2, and an electronic load unit, etc. The industrial control computer 11 is equipped with an RS422 / RS485 board, and completes the control and parameter acquisition of the AC power supply unit 2, the DC power supply unit 3, and the electronic load unit through the MODBUS protocol; communicates with the electromechanical computer 9 through an RS422 interface; at the same time, it is convenient to provide a human-machine interaction interface, which is responsible for the status display and control of the unmanned aerial vehicle electrical system test device, and is convenient to display the instrument information collected through the RS485 bus and the product status feedback by the electromechanical computer 9 through RS422, and sends system instructions to the electromechanical computer 9 through the RS422 interface; at the same time, the industrial control computer 11 is equipped with a CAN bus board, which is convenient to access the on-board test product network, stores bus data in real time, can be used for data playback and fault troubleshooting, and is convenient to set software. Through the software settings, a single unit or module or the device under test can be simulated, and then semi-physical testing can be completed, effectively improving the test convenience and test efficiency.

[0065] Optionally, a plurality of mounting baseboards 12 are arranged in the cabinet 1. The plurality of mounting baseboards 12 divide the internal space of the cabinet 1 into a plurality of mounting spaces. The AC power supply unit 2, the DC power supply unit 3, the electronic load unit, the battery unit, the power conversion device 8, the electromechanical computer 9, the primary power distribution device 10, and the industrial control computer 11 are distributed in the plurality of mounting spaces.

[0066] Specifically, the cabinet 1 is divided into a plurality of mounting spaces, which is convenient for classifying and setting the above-mentioned plurality of units and devices integrated in the cabinet 1, and is convenient for inspection and maintenance.

[0067] In this embodiment, casters 13 are arranged at the bottom of the cabinet 1, which is convenient for the movement of the unmanned aerial vehicle electrical system test device, and thus convenient for ground testing of the unmanned aerial vehicle.

[0068] In summary, when the drone electrical system testing device provided by the present utility model is in use, taking this embodiment as an example: after power-on, set the power parameters through the display and control software, select whether to use AC power or DC power, set parameters such as the power output voltage and frequency, and set the power protection mode and protection threshold. Subsequently, set the load parameters through the display and control software, select the load working mode, such as constant current, constant voltage, or constant resistance mode, and set the corresponding power value. Then set the power output to be conducted with the load, and confirm whether the working status of the instrument and airborne equipment is normal through the feedback parameters of the display and control software. When the system is working properly, start the normal testing process. If the system is abnormal, immediately cut off the power, and retest after troubleshooting.

[0069] The embodiments of the present utility model have been described above. The above description is exemplary and not exhaustive, and is not limited to the disclosed embodiments. Many modifications and variations are obvious to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A test device for an unmanned aerial vehicle electrical system, characterized in that, Including: A cabinet body, inside which are provided with an AC power supply unit, a DC power supply unit, an electronic load unit, a battery unit, a power conversion device, an electromechanical computer, a primary power distribution device, and an industrial control computer; The AC power supply unit is provided with a first power input interface and is used to convert the alternating current input through the first power input interface into three-phase alternating current to simulate the output of the on-board AC generator of the UAV; The power conversion device is connected between the AC power supply unit and the primary power distribution device. The AC power supply unit supplies power to the power conversion device, and the power conversion device is used to convert the three-phase alternating current output by the AC power supply unit into a DC power supply with a set voltage and supply power to the primary power distribution device; The DC power supply unit is provided with a second power input interface and is used to convert the alternating current input through the second power input interface into direct current to simulate the output of the on-board low-voltage DC and high-voltage DC generators of the UAV; The primary power distribution device is connected to the DC power supply unit. The DC power supply unit supplies power to the primary power distribution device, and the primary power distribution device is used for the energy distribution of the UAV electrical system test device; The electronic load unit includes an electronic load module and a load management device. The electronic load module is used to simulate the on-board electrical equipment of the UAV and is used to convert the electrical energy passing through the primary power distribution device and the load management device into heat; The battery unit includes a battery module and a battery management module. The battery module is used as the on-board emergency power supply of the UAV module, and the battery management module is used to charge and control the temperature of the battery module; The electromechanical computer is connected to the battery unit, the load management device, the power conversion device, and the primary power distribution device, and is used to transmit the data of the battery unit, the load management device, the power conversion device, and the primary power distribution device to the industrial control computer, and transmit the control instructions of the industrial control computer to the battery unit, the load management device, and the primary power distribution device; The industrial control computer is connected to the DC power supply unit, the AC power supply unit, the electronic load unit, and the electromechanical computer. The industrial control computer includes a CAN bus board, and the CAN bus board is connected to the battery unit, the primary power distribution device, and the load management device.

2. The drone electrical system testing device according to claim 1, wherein The load management device is connected between the primary power distribution device and the electronic load module, and the load management device includes a solid-state controllable switch with a protection function.

3. The drone electrical system testing device according to claim 1, characterized in that The first power input interface and the second power input interface are connected to the 380V / 50Hz AC power supply from outside the cabinet body.

4. The drone electrical system testing device according to claim 1, characterized in that, The three-phase alternating current is three-phase alternating current with adjustable output frequency, amplitude, and phase, and the rated power of the three-phase alternating current is 6kW.

5. The drone electrical system testing device according to claim 1, wherein, The voltage of the direct current is 0 - 400V, and the rated power of the direct current is 6kW.

6. The drone electrical system testing device according to claim 1, wherein, The battery module includes a lithium-ion battery and a temperature sensor and a heating component arranged inside the lithium-ion battery.

7. The drone electrical system testing device according to claim 6, wherein, The battery management module includes a charger adapted to the lithium-ion battery, a battery heating detection and control circuit, a battery health status monitoring component, a battery health status alarm component, and a battery circuit cut-off component.

8. The drone electrical system testing device according to claim 1, characterized in that The set voltage is 28V. The power conversion device includes a rectifier, transformer, and filter component, an over-current, over-voltage, and over-temperature protection component, and is provided with a current sharing interface and can communicate via the CAN bus.

9. The drone electrical system testing device according to claim 1, wherein The industrial computer includes 3 functional boards, a 2-channel CAN bus board, an 8-channel RS422 / RS485 board, a 32-channel IO input / output board, and an expansion function board. The expansion function board communicates with the bottom board of the industrial computer through a PCIe interface, and the display screen is interconnected with the industrial computer through an HDMI interface.

10. The drone electrical system testing device according to claim 1, characterized in that, A plurality of mounting bases are arranged inside the cabinet, and the plurality of mounting bases divide the internal space of the cabinet into a plurality of mounting spaces. The AC power supply unit, the DC power supply unit, the electronic load unit, the battery unit, the power conversion device, the electromechanical computer, the primary power distribution device, and the industrial computer are distributed in the plurality of mounting spaces.

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