Aircraft power testing device and method

Abstract

The invention discloses an aircraft power testing device and method.The device comprises an upper computer, an adapter, a low-voltage power source, a low-voltage power source controller, a power source safety device and a debugging connecting line, and the debugging connecting line is connected to an aircraft bus interface of a tested electric aircraft; wherein the low-voltage power supply outputs power through the low-voltage power supply controller and provides low-voltage electric energy for the battery management module; the upper computer outputs an instruction through the adapter and sends a working instruction to the battery management module and the electronic debugger, so that the power battery pack provides high-voltage electric energy for the motor, and a test result is collected through the electronic debugger. According to the invention, an aircraft power test scheme with higher safety and operation convenience is realized, frequent switching of test equipment is avoided, the electric shock risk of personnel is reduced, and the test efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to an aircraft power testing device and method. Background Art

[0002] In the prior art, when the final assembly of an electric-drive aircraft is completed, a host computer will perform functional tests on the electronic debugger (also known as an electronic speed governor) and power battery pack installed inside the aircraft to read information data and send instructions, so as to confirm that the power unit is in normal working condition after final assembly.

[0003] The current tests are divided into two independent tests: First, the power battery pack is connected to the test computer via a connecting line and a CAN bus adapter, and powered by an adjustable DC power supply of 24V, and the information is read and tested by the host computer; Second, the electronic speed controller is connected to the test computer via a connecting line and a CAN adapter, and is powered by an adjustable DC power supply of 85V, and the information is read and tested by the host computer.

[0004] It can be seen that during the above test process, the equipment needs to be switched multiple times. On the one hand, the operation steps are relatively cumbersome, and on the other hand, the operator has a certain risk of electric shock. Summary of the invention

[0005] In order to overcome the deficiencies in the prior art, the purpose of the present invention is to provide an aircraft power testing device and method to solve the problem that during the current testing of the power system of an electric-driven aircraft, multiple equipment switching is required, the operating steps are relatively cumbersome, and the operator is at risk of electric shock.

[0006] The present invention proposes an aircraft power test device, which includes a host computer, a low-voltage power supply, a low-voltage power supply controller connected to the low-voltage power supply, a power supply fuse connected to the low-voltage power supply controller, and a debugging connection line connected to the power supply fuse, wherein the host computer is connected to the debugging connection line through a CAN adapter, and the debugging connection line is connected to an aircraft bus interface of an electric aircraft, wherein: The low-voltage power supply is used to output power through the low-voltage power supply controller, and provide low-voltage electric energy to the battery management module of the electric aircraft through the power supply fuse, the debugging connection line, and the aircraft bus interface; The host computer is used to output instructions through the CAN adapter, and send work instructions to the battery management module and the electronic debugger of the electric aircraft through the debugging connection line and the aircraft bus interface, so that the power battery pack of the electric aircraft can provide high-voltage electrical energy to the motor of the electric aircraft through the electronic debugger, and collect test results through the electronic debugger.

[0007] Optionally, the debugging connection line includes a first input interface of a power supply path and a second input interface of a communication connection path.

[0008] Optionally, the low-voltage power supply, the low-voltage power supply controller, and the power supply fuse are sequentially connected to the first input interface through the power supply path, wherein the power supply path is used to provide low-voltage power.

[0009] Optionally, the host computer and the CAN adapter are connected to the second input interface in sequence through the communication connection path.

[0010] Optionally, the debugging connection line includes a first output interface of a power supply path and a second output interface of a communication connection path.

[0011] Optionally, the first output interface is connected to the electric aircraft and provides the low-voltage electric energy required for operation to the battery management module via the aircraft bus interface.

[0012] Optionally, the second output interface is connected to the electric aircraft, and sends work instructions to the battery management module and the electronic debugger via the aircraft bus interface.

[0013] The present invention also proposes an aircraft power test method, which comprises: After the low-voltage power supply controller is turned on, the low-voltage power supply provides low-voltage electrical energy to the battery management module; Receiving a first startup instruction input by a user, wherein the first startup instruction is used to start a first host computer software corresponding to the battery management module, and the first host computer software is used to send a first working instruction to the battery management module, so that the power battery pack provides high-voltage electric energy to the motor via the electronic debugger; A second startup instruction input by a user is received, where the second startup instruction is used to start second host computer software corresponding to the electronic debugger, and the second host computer software is used to send a second working instruction to the electronic debugger so that the electronic debugger collects test results.

[0014] Optionally, after the low-voltage power supply controller is turned on and before the low-voltage power supply provides low-voltage power to the battery management module, the process includes: A low-voltage power supply path is created, which is composed of a low-voltage power supply, a low-voltage power supply controller, a power supply fuse, a debugging connection line, an aircraft bus interface, and a battery management module.

[0015] Optionally, after the low-voltage power supply controller is turned on and before the low-voltage power supply provides low-voltage power to the battery management module, the process includes: A communication connection path consisting of a host computer, a CAN adapter, the debugging connection line, the aircraft bus interface, the battery management module and an electronic debugger is created.

[0016] The aircraft power test device and method of the present invention have the beneficial effect that, by proposing an aircraft power test device, the device includes a host computer, a low-voltage power supply, a low-voltage power supply controller connected to the low-voltage power supply, a power supply fuse connected to the low-voltage power supply controller, and a debugging connection line connected to the power supply fuse device, wherein the host computer is connected to the debugging connection line through a CAN adapter, and the debugging connection line is connected to the aircraft bus interface of the electric aircraft, wherein: the low-voltage power supply is used to output power through the low-voltage power supply controller, and provide low-voltage electric energy to the battery management module of the electric aircraft through the power supply fuse device, the debugging connection line, and the aircraft bus interface; the host computer is used to output instructions through the CAN adapter, and send work instructions to the battery management module and the electronic debugger of the electric aircraft through the debugging connection line and the aircraft bus interface, so that the power battery pack of the electric aircraft provides high-voltage electric energy to the motor of the electric aircraft through the electronic debugger, and collects test results through the electronic debugger. A safer and more convenient aircraft power test solution has been implemented, which avoids frequent switching of test equipment, reduces the risk of electric shock to personnel, and improves test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The present invention will be further described below with reference to the accompanying drawings and embodiments, in which: Figure 1 It is a module block diagram of the aircraft power test device of the present invention; Figure 2 It is a flow chart of the aircraft power testing method of the present invention. DETAILED DESCRIPTION

[0018] It should be understood that the specific embodiments described herein are only used to explain the present invention, and are not used to limit the present invention.

[0019] In the subsequent description, the suffixes such as "module", "component" or "unit" used to represent elements are only used to facilitate the description of the present invention, and have no specific meanings. Therefore, "module", "component" or "unit" can be used in a mixed manner.

[0020] Figure 1 This is a block diagram of a module of an aircraft power test device of the present invention. This embodiment proposes an aircraft power test device, which includes a host computer 50, a low-voltage power supply 10, a low-voltage power supply controller 20 connected to the low-voltage power supply 10, a power supply fuse 30 connected to the low-voltage power supply controller 20, and a debugging connection line 40 connected to the power supply fuse 30. The host computer 50 is connected to the debugging connection line 40 through a CAN adapter 60, and the debugging connection line 40 is connected to the aircraft bus interface 70 of the electric aircraft, wherein: The low-voltage power supply 10 is used to output power through the low-voltage power supply controller 20, and provide low-voltage power to the battery management module 80 of the electric aircraft through the power supply fuse 30, the debugging connection line 40, and the aircraft bus interface 70; The host computer 50 is used to output instructions through the CAN adapter 60, and send work instructions to the battery management module 80 and the electronic debugger 100 of the electric aircraft through the debugging connection line 40 and the aircraft bus interface 70, so that the power battery pack 90 of the electric aircraft provides high-voltage electrical energy to the motor 110 of the electric aircraft through the electronic debugger 100, and collects test results through the electronic debugger 100.

[0021] In this embodiment, the debugging connection line 40 includes a first input interface of a power supply path and a second input interface of a communication connection path.

[0022] In this embodiment, the low-voltage power supply 10, the low-voltage power supply controller 20, and the power supply fuse 30 are sequentially connected to the first input interface through the power supply path, wherein the power supply path is used to provide low-voltage electricity.

[0023] In this embodiment, the host computer 50 and the CAN adapter 60 are sequentially connected to the second input interface through the communication connection path.

[0024] In this embodiment, the debugging connection line 40 includes a first output interface of a power supply path and a second output interface of a communication connection path.

[0025] In this embodiment, the first output interface is connected to the electric aircraft and provides the battery management module 80 with low-voltage electric energy required for operation via the aircraft bus interface 70 .

[0026] In this embodiment, the second output interface is connected to the electric aircraft, and sends working instructions to the battery management module 80 and the electronic debugger 100 via the aircraft bus interface 70 .

[0027] In this embodiment, the low voltage power supply 10 is a 24V DC switching power supply.

[0028] In this embodiment, the host computer 50 is a configuration computer that runs the host computer 50 software related to the current test object and test requirements, wherein the host computer 50 software includes the configuration software of the battery management module 80 and the configuration software of the electronic debugger 100 .

[0029] In this embodiment, the low-voltage power supply 10 controls the power output through the low-voltage power supply controller 20, and is connected to the aircraft bus interface 70 through the power supply fuse device 30 and the debugging connection line 40 to provide low-voltage operating power for the battery management module 80.

[0030] In this embodiment, the power battery pack 90 is connected to the communication port of the battery management module 80 and to the power port of the electronic debugger 100. The three-phase port of the electronic debugger 100 is connected to the three-phase line of the motor 110 to provide high-voltage operating power to the motor 110.

[0031] In this embodiment, the host computer 50 is connected to the communication ports of the battery management module 80 and the electronic debugger 100 through the CAN adapter 60, the debugging connection line 40, and the aircraft bus interface 70, thereby sending relevant work instructions to the battery management module 80 and the electronic debugger 100 to collect test data.

[0032] In this embodiment, by turning on the power switch button on the software interface of the host computer 50 connected to the battery management module 80, the power battery pack 90 outputs 85V electric energy, which is the high-voltage electric energy required for the operation of the electronic debugger 100; further, the motor 110 control button on the software interface of the host computer 50 connected to the electronic debugger 100 is used to start the motor 110, and the relevant test data is viewed on the software interface of the host computer 50, for example, the electronic debugger temperature, the motor 110 temperature, etc., and the direction of the motor 110 is observed, for example, whether the motor 110 is rotating clockwise or counterclockwise at this time.

[0033] In this embodiment, the specific operation steps of the above-mentioned test device include: step 1, the low-voltage power supply 10 is connected to the low-voltage power supply controller 20 and the power supply fuse device 30; step 2, one end of the debugging connection line 40 is connected to the power supply fuse device 30, and the other end is connected to the aircraft bus interface 70; step 3, one end of the CAN adapter 60 is connected to the host computer 50 computer, and the other end is connected to the debugging connection line 40; step 4, turn on the switch of the low-voltage power supply controller 20; step 5, turn on the battery management module 80 host computer 50 software; step 6, click Click the power switch button on the upper computer 50 software interface to output the voltage of the power battery pack 90; step seven, start the upper computer 50 software of the electronic debugger 100; step eight, select the ID of the electronic debugger to be tested on the upper computer 50 software interface, and turn on the throttle button to rotate the motor 110, view the relevant test data on the upper computer 50 software interface, for example, the temperature of the electronic debugger, the temperature of the motor 110, etc., and observe the direction of the motor 110, for example, whether the motor 110 is rotating clockwise or counterclockwise at this time.

[0034] It can be seen that in this embodiment, the two traditional test devices are combined together, and a power controller is added, and the 24V DC switching power supply is used for power supply. At the same time, the host computer 50 controls the power battery pack 90 to output 85V to provide power for the electronic modem, thereby realizing the distributed power supply aircraft power system test. Further, in this embodiment, the test device is powered by a 24V DC switching power supply, which effectively solves the risk of electric shock in the existing solution due to the use of 85V power supply, and at the same time, greatly improves the production test efficiency and test operation convenience.

[0035] The beneficial effect of this embodiment is that, by implementing an aircraft power test device, the device includes a host computer 50, a low-voltage power supply 10, a low-voltage power supply controller 20 connected to the low-voltage power supply 10, a power supply fuse 30 connected to the low-voltage power supply controller 20, and a debugging connection line 40 connected to the power supply fuse 30, the host computer 50 is connected to the debugging connection line 40 through a CAN adapter 60, and the debugging connection line 40 is connected to the aircraft bus interface 70 of the electric aircraft, wherein: the low-voltage power supply 10 is used to output power through the low-voltage power supply controller 20, and through the The power supply insurance device 30, the debugging connection line 40, and the aircraft bus interface 70 provide power to the battery management module 80 of the electric aircraft; the host computer 50 is used to output instructions through the CAN adapter 60, and send work instructions to the battery management module 80 and the electronic debugger 100 of the electric aircraft through the debugging connection line 40 and the aircraft bus interface 70, so that the power battery pack 90 of the electric aircraft provides operating power to the motor 110 of the electric aircraft through the electronic debugger 100, and collects test results through the electronic debugger 100. A safer and more convenient aircraft power test solution is realized, which avoids frequent switching of test equipment, reduces the risk of electric shock to personnel, and improves test efficiency.

[0036] Figure 2 is a flow chart of the aircraft power test method of the present invention. Based on the above embodiment, the present invention also proposes an aircraft power test method, which includes: S1. After the low-voltage power supply controller is turned on, the low-voltage power supply provides low-voltage power to the battery management module; S2, receiving a first startup instruction input by a user, wherein the first startup instruction is used to start a first host computer software corresponding to the battery management module, and the first host computer software is used to send a first working instruction to the battery management module, so that the power battery pack provides high-voltage electric energy to the motor through the electronic debugger; S3. Receive a second startup instruction input by a user, where the second startup instruction is used to start a second host computer software corresponding to the electronic debugger, and the second host computer software is used to send a second working instruction to the electronic debugger to enable the electronic debugger to collect test results.

[0037] In this embodiment, after the low-voltage power supply controller is turned on and before the low-voltage power supply provides low-voltage electrical energy to the battery management module, it includes: creating a low-voltage power supply path consisting of a low-voltage power supply, a low-voltage power supply controller, a power supply fuse, a debugging connection line, an aircraft bus interface and a battery management module.

[0038] In this embodiment, after the low-voltage power supply controller is turned on and before the low-voltage power supply provides low-voltage power to the battery management module, it includes: creating a communication connection path consisting of a host computer, a CAN adapter, the debugging connection line, the aircraft bus interface, the battery management module and an electronic debugger.

[0039] In this embodiment, the above method is applied to an aircraft power test device, which includes a host computer, a low-voltage power supply, a low-voltage power supply controller connected to the low-voltage power supply, a power supply fuse device connected to the low-voltage power supply controller, and a debugging connection line connected to the power supply fuse device. The host computer is connected to the debugging connection line through a CAN adapter, and the debugging connection line is connected to the aircraft bus interface of the electric aircraft, wherein: the low-voltage power supply is used to output power through the low-voltage power supply controller, and provide low-voltage electric energy to the battery management module of the electric aircraft through the power supply fuse device, the debugging connection line, and the aircraft bus interface; the host computer is used to output instructions through the CAN adapter, and send work instructions to the battery management module and the electronic debugger of the electric aircraft through the debugging connection line and the aircraft bus interface, so that the power battery pack of the electric aircraft provides high-voltage electric energy to the motor of the electric aircraft through the electronic debugger, and collects test results through the electronic debugger.

[0040] In this embodiment, the debugging connection line includes a first input interface of a power supply path and a second input interface of a communication connection path.

[0041] In this embodiment, the low-voltage power supply, the low-voltage power supply controller, and the power supply fuse are sequentially connected to the first input interface through the power supply path, wherein the power supply path is used to provide low-voltage power.

[0042] In this embodiment, the host computer and the CAN adapter are sequentially connected to the second input interface through the communication connection path.

[0043] In this embodiment, the debugging connection line includes a first output interface of a power supply path and a second output interface of a communication connection path.

[0044] In this embodiment, the first output interface is connected to the electric aircraft and provides the low-voltage electric energy required for operation to the battery management module via the aircraft bus interface.

[0045] In this embodiment, the second output interface is connected to the electric aircraft, and sends working instructions to the battery management module and the electronic debugger via the aircraft bus interface.

[0046] In this embodiment, the low voltage power supply is a 24V DC switching power supply.

[0047] In this embodiment, the host computer is a configuration computer, which runs host computer software related to the current test object and test requirements, wherein the host computer software includes configuration software of the battery management module and configuration software of the electronic debugger.

[0048] In this embodiment, the low-voltage power supply controls the power output through a low-voltage power supply controller, and is connected to the aircraft bus interface through a power supply fuse and a debugging connection line to provide low-voltage operating power for the battery management module.

[0049] In this embodiment, the power battery pack is connected to the communication port of the battery management module and to the power port of the electronic debugger. The three-phase port of the electronic debugger is connected to the three-phase line of the motor to provide high-voltage operating power to the motor.

[0050] In this embodiment, the host computer is connected to the communication port of the battery management module and the electronic debugger through a CAN adapter, a debugging connection line, and an aircraft bus interface, thereby sending relevant work instructions to the battery management module and the electronic debugger to collect test data.

[0051] In this embodiment, by turning on the power switch button on the host computer software interface connected to the battery management module, the power battery pack outputs 85V electric energy, which is the high-voltage electric energy required for the operation of the electronic debugger; further, the motor control button on the host computer software interface connected to the electronic debugger is used to start the motor, and relevant test data is viewed on the host computer software interface, such as the electronic debugger temperature, motor temperature, etc., and the motor direction is observed, for example, whether the motor is rotating clockwise or counterclockwise at this time.

[0052] In this embodiment, the above-mentioned test method includes: step one, the low-voltage power supply is connected to the low-voltage power supply controller and the power supply fuse device; step two, one end of the debugging connection line is connected to the power supply fuse device, and the other end is connected to the aircraft bus interface; step three, one end of the CAN adapter is connected to the host computer, and the other end is connected to the debugging connection line; step four, turn on the switch of the low-voltage power supply controller; step five, start the battery management module host software; step six, click the power switch button on the host software interface to output the voltage of the power battery pack; step seven, start the electronic debugger host software; step eight, select the ID of the electronic debugger to be tested in the host software interface, and turn on the throttle button to make the motor rotate, view relevant test data in the host software interface, for example, the electronic debugger temperature, motor temperature, etc., and observe the direction of the motor, for example, whether the motor is rotating clockwise or counterclockwise at this time.

[0053] It can be seen that in this embodiment, the two traditional test devices are combined together, and a power controller is added, combined with a 24V DC switching power supply for power supply. At the same time, the host computer controls the power battery pack to output 85V to provide power for the electronic regulator, thereby realizing the distributed power supply aircraft power system test. Further, in this embodiment, the test device is powered by a 24V DC switching power supply, which effectively solves the risk of electric shock in the existing solution due to the use of 85V power supply, and at the same time, greatly improves the production test efficiency and test operation convenience.

[0054] The beneficial effects of this embodiment are that a low-voltage power supply path is formed by sequentially connecting a low-voltage power supply, a low-voltage power supply controller, a power supply fuse, a debugging connection line, an aircraft bus interface, and a battery management module, and a communication connection path is formed by sequentially connecting a host computer, a CAN adapter, the debugging connection line, the aircraft bus interface, the battery management module, and an electronic debugger; operating power is provided to the battery management module through the power supply path, and work instructions are sent to the battery management module and the electronic debugger through the communication connection path; the power battery pack of the electric aircraft is controlled to provide operating power to the motor of the electric aircraft through the electronic debugger, and the test results are collected through the electronic debugger. A safer and more convenient aircraft power test solution is realized, which avoids frequent switching of test equipment, reduces the risk of electric shock to personnel, and improves test efficiency.

[0055] Through the description of the above implementation methods, those skilled in the art can clearly understand that the above-mentioned embodiment methods can be implemented by means of software plus a necessary general hardware platform, and of course can also be implemented by hardware, but in many cases the former is a better implementation method. Based on such an understanding, the technical solution of the present invention, or the part that contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium (such as ROM / RAM, a magnetic disk, or an optical disk), and includes a number of instructions for enabling a terminal (which can be a mobile phone, a computer, a server, an air conditioner, or a network device, etc.) to execute the methods described in each embodiment of the present invention.

[0056] It should be noted that, in this article, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the existence of other identical elements in the process, method, article or device including the element.

[0057] The embodiments of the present invention are described above in conjunction with the accompanying drawings, but the present invention is not limited to the above-mentioned specific implementation modes, which are merely illustrative rather than restrictive. Under the guidance of the present invention, ordinary technicians in this field can also make many forms without departing from the scope of protection of the present invention and the claims, all of which are within the protection of the present invention.

Claims

1. An aircraft power test device, characterized in that: The device comprises a host computer, a low-voltage power supply, a low-voltage power supply controller connected to the low-voltage power supply, a power supply fuse connected to the low-voltage power supply controller, and a debugging connection line connected to the power supply fuse, wherein the host computer is connected to the debugging connection line through a CAN adapter, and the debugging connection line is connected to an aircraft bus interface of an electric aircraft, wherein: The low-voltage power supply is used to output power through the low-voltage power supply controller, and provide low-voltage electric energy to the battery management module of the electric aircraft through the power supply fuse, the debugging connection line, and the aircraft bus interface; The host computer is used to output instructions through the CAN adapter, and send work instructions to the battery management module and the electronic debugger of the electric aircraft through the debugging connection line and the aircraft bus interface, so that the power battery pack of the electric aircraft can provide high-voltage electrical energy to the motor of the electric aircraft through the electronic debugger, and collect test results through the electronic debugger.

2. The aircraft power test device according to claim 1, characterized in that: The debugging connection line includes a first input interface of a power supply path and a second input interface of a communication connection path.

3. The aircraft power test device according to claim 2, characterized in that: The low-voltage power supply, the low-voltage power supply controller, and the power supply fuse are sequentially connected to the first input interface through the power supply path, wherein the power supply path is used to provide low-voltage electrical energy.

4. The aircraft power test device according to claim 2, characterized in that: The host computer and the CAN adapter are connected to the second input interface in sequence through the communication connection path.

5. The aircraft power test device according to claim 1, characterized in that: The debugging connection line includes a first output interface of a power supply path and a second output interface of a communication connection path.

6. The aircraft power test device according to claim 5, characterized in that: The first output interface is connected to the electric aircraft and provides the battery management module with low-voltage electric energy required for operation via the aircraft bus interface.

7. The aircraft power test device according to claim 5, characterized in that: The second output interface is connected to the electric aircraft and sends working instructions to the battery management module and the electronic debugger via the aircraft bus interface.

8. An aircraft power test method, applied to the aircraft power test device according to claims 1 to 7, characterized in that: The method comprises: After the low-voltage power supply controller is turned on, the low-voltage power supply provides low-voltage electrical energy to the battery management module; receiving a first startup instruction input by a user, wherein the first startup instruction is used to start a first host computer software corresponding to the battery management module, and the first host computer software is used to send a first working instruction to the battery management module, so that the power battery pack provides high-voltage electric energy to the motor via the electronic debugger; A second startup instruction input by a user is received, where the second startup instruction is used to start second host computer software corresponding to the electronic debugger, and the second host computer software is used to send a second working instruction to the electronic debugger so that the electronic debugger collects test results.

9. The aircraft power testing method according to claim 8, characterized in that: After the low-voltage power supply controller is turned on and before the low-voltage power supply provides low-voltage power to the battery management module, the method includes: A low-voltage power supply path is created, which is composed of a low-voltage power supply, a low-voltage power supply controller, a power supply fuse, a debugging connection line, an aircraft bus interface, and a battery management module.

10. The aircraft power testing method according to claim 8, characterized in that: After the low-voltage power supply controller is turned on and before the low-voltage power supply provides low-voltage power to the battery management module, the method includes: A communication connection path consisting of a host computer, a CAN adapter, the debugging connection line, the aircraft bus interface, the battery management module and an electronic debugger is created.

Images