CN115542158B - Unmanned aerial vehicle motor test system - Google Patents
Unmanned aerial vehicle motor test system Download PDFInfo
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- CN115542158B CN115542158B CN202211507920.3A CN202211507920A CN115542158B CN 115542158 B CN115542158 B CN 115542158B CN 202211507920 A CN202211507920 A CN 202211507920A CN 115542158 B CN115542158 B CN 115542158B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/34—Testing dynamo-electric machines
- G01R31/343—Testing dynamo-electric machines in operation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0208—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
- G05B23/0213—Modular or universal configuration of the monitoring system, e.g. monitoring system having modules that may be combined to build monitoring program; monitoring system that can be applied to legacy systems; adaptable monitoring system; using different communication protocols
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Abstract
The invention provides an unmanned aerial vehicle motor test system, which comprises: the device comprises a power supply, a motor control operation unit and an analog test unit; the power supply is used for providing electric energy for the motor control operation unit; the motor control operation unit comprises a motor to be tested, a first motor controller, a second motor controller and a motor connecting mechanism; the second motor controller is configured to receive motor simulation operation parameters which are sent by the simulation test unit and used for simulating the operation of the target propeller, and control the operation of the accompanying motor based on the motor simulation operation parameters; the simulation test unit is used for obtaining the operation parameters of the target propeller; converting the operation parameters of the target propeller into motor simulation operation parameters; transmitting the motor simulated operation parameters to a second motor controller; and responding to the running of the tested motor and the accompanying motor, acquiring and obtaining the running parameters of the tested motor, and performing performance test on the tested motor and/or the first motor controller based on the running parameters of the tested motor.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle motor test system.
Background
In recent years, unmanned aerial vehicle technology and application development thereof are in rapid progress, and intelligent unmanned aerial vehicles become an important direction of intelligent technological development. The common motor pair-dragging test bench can set a torque value of the motor to be tested to increase the load for the motor to be tested, so that the performance of the motor to be tested or the performance of a motor controller is verified, in the process, the motor to be tested drags the motor to be tested to rotate, the motor to be tested applies reverse torque to serve as the load of the motor to be tested, the process can complete the test requirements on the performance of the motor and the performance of the motor controller, and corresponding assistance is provided for the type selection of the motor, the development of a motor controller algorithm and a hardware circuit. However, when the performance test of the unmanned aerial vehicle power system is performed, the performance of the motor and the motor controller is concerned, and the performance of the motor or the motor controller under the condition that the motor, the motor controller and the propeller are matched together is concerned. Therefore, how to perform performance test on the motor or the motor controller under the condition that the motor, the motor controller and the propeller are matched together for use is a problem to be solved.
Disclosure of Invention
The invention provides an unmanned aerial vehicle motor test system which aims to solve the problem of performance test of a motor or a motor controller under the condition that the motor, the motor controller and a propeller are matched together.
To solve or improve the above technical problems to some extent, according to an aspect of the present invention, there is provided an unmanned aerial vehicle electrical test system, the system comprising:
the device comprises a power supply, a motor control operation unit and an analog test unit;
the power supply is electrically connected with the motor control operation unit and is used for providing electric energy for the motor control operation unit;
the motor control operation unit comprises a tested motor, a test accompanying motor for providing a load for the tested motor, a first motor controller for controlling the operation of the tested motor, a second motor controller for controlling the operation of the test accompanying motor, and a motor connecting mechanism for enabling the tested motor to drag the test accompanying motor to rotate together; the second motor controller is configured to receive motor simulation operation parameters for simulating the operation of the target propeller, which are sent by the simulation test unit, and control the operation of the accompanying motor based on the motor simulation operation parameters so as to enable the accompanying motor to serve as the load of the tested motor; the target propeller is a propeller used by a target unmanned aerial vehicle, and the tested motor is used for driving the target propeller;
the simulation test unit is used for obtaining the operation parameters of the target propeller; converting the operation parameters of the target propeller into the motor simulation operation parameters; transmitting the motor simulated operating parameters to the second motor controller; and responding to the operation of the tested motor and the accompanying motor, acquiring and obtaining the operation parameters of the tested motor, and performing performance test on the tested motor and/or the first motor controller based on the operation parameters of the tested motor.
In some embodiments, the obtaining the operating parameters of the target propeller comprises:
establishing a first corresponding relation between the propeller structure parameter and the propeller operation parameter based on the propeller entity power test data or the unmanned aerial vehicle historical operation data;
obtaining structural parameters of the target propeller;
and obtaining the operation parameters of the target propeller based on the first corresponding relation and the structural parameters of the target propeller.
In some embodiments, the establishing a first correspondence between the propeller structural parameter and the propeller operating parameter based on the propeller entity power test data or the unmanned aerial vehicle historical operating data includes:
acquiring structural parameters of the propeller entity and corresponding propeller operation parameters in a scene of performing power test on the propeller entity of the unmanned aerial vehicle or in a historical operation scene of the unmanned aerial vehicle;
and carrying out data fitting processing on the structural parameters of the propeller entity and the propeller operation parameters corresponding to the structural parameters to obtain a function formula for representing the corresponding relation between the structural parameters of the propeller and the propeller operation parameters.
In some embodiments, the converting the operating parameter of the target propeller to the motor simulation operating parameter includes:
establishing a second corresponding relation between the propeller operation parameters and the motor operation parameters based on the propeller entity power test data or the unmanned aerial vehicle historical operation data;
and converting the operation parameters of the target propeller into the motor simulation operation parameters based on the second corresponding relation.
In some embodiments, the establishing a second correspondence between the propeller operation parameter and the motor operation parameter based on the propeller entity power test data or the unmanned aerial vehicle historical operation data includes:
acquiring and obtaining the operation parameters of the propeller entity and the motor operation parameters corresponding to the operation parameters in a scene of performing power test on the propeller entity of the unmanned aerial vehicle or in a historical operation scene of the unmanned aerial vehicle;
and performing data fitting processing on the operation parameters of the propeller entity and the motor operation parameters corresponding to the operation parameters to obtain a function formula for representing the corresponding relation between the operation parameters of the propeller and the motor operation parameters.
In some embodiments, the motor connecting mechanism connects the motor to be tested and the accompanying motor in a flexible connection manner.
In some embodiments, the motor connection mechanism comprises a driving wheel fixedly connected with the tail end of the output shaft of the motor to be tested, a driven wheel fixedly connected with the tail end of the output shaft of the motor to be tested, and a synchronous belt connecting the driving wheel and the driven wheel.
In some embodiments, the power supply is a bidirectional grid-connected power supply, and the bidirectional grid-connected power supply is electrically connected with the first motor controller and the second motor controller, and is used for providing electric energy for the tested motor and receiving electric energy generated by the accompanying motor.
In some embodiments, the analog test unit is further configured to: and obtaining the structural parameter of the target propeller based on the operation parameter of the target propeller and a first corresponding relation between the pre-established structural parameter of the propeller and the operation parameter of the propeller.
In some embodiments, the first motor controller and the second motor controller are the same specification, and the motor to be tested and the accompanying motor are the same specification.
Compared with the prior art, the invention has the following advantages:
the unmanned aerial vehicle motor test system provided by the invention comprises: the device comprises a power supply, a motor control operation unit and an analog test unit; the power supply is electrically connected with the motor control operation unit and is used for providing electric energy for the motor control operation unit; the motor control operation unit comprises a tested motor, a test accompanying motor for providing a load for the tested motor, a first motor controller for controlling the operation of the tested motor, a second motor controller for controlling the operation of the test accompanying motor, and a motor connecting mechanism for enabling the tested motor to drag the test accompanying motor to rotate together; the second motor controller is configured to receive motor simulation operation parameters which are sent by the simulation test unit and used for simulating the operation of the target propeller, and control the operation of the accompanying motor based on the motor simulation operation parameters so as to enable the accompanying motor to serve as the load of the motor to be tested; the target propeller is a propeller used by the target unmanned aerial vehicle, and the tested motor is used for driving the target propeller; the simulation test unit is used for obtaining the operation parameters of the target propeller; converting the operation parameters of the target propeller into motor simulation operation parameters; transmitting the motor simulated operation parameters to a second motor controller; and responding to the running of the tested motor and the accompanying motor, acquiring and obtaining the running parameters of the tested motor, and performing performance test on the tested motor and/or the first motor controller based on the running parameters of the tested motor. The second motor controller is configured to receive the motor simulation operation parameters for simulating the operation of the target propeller, and control the operation of the accompanying motor based on the motor simulation operation parameters, namely, when the tested motor drags the accompanying motor to rotate, the accompanying motor applies reverse moment in a mode of simulating the operation of the target propeller, and the reverse moment is used as a load required by the tested motor, so that the performance test can be performed on the motor or the motor controller under the condition of simulating the operation of the propeller by using the unmanned aerial vehicle motor test system, a test result matched with a real use scene can be obtained, and the test result meets the scene requirement of the motor, the motor controller and the propeller for common cooperation.
The foregoing description is only an overview of the present invention, and is intended to be implemented in accordance with the teachings of the present invention, as well as the preferred embodiments thereof, together with the following detailed description of the invention, given by way of illustration only, together with the accompanying drawings.
Drawings
Fig. 1 is a schematic diagram of a test system for an unmanned aerial vehicle according to an embodiment of the present application.
Detailed Description
In order to further describe the technical means and effects adopted by the present invention to achieve the preset purpose, the following detailed description refers to the specific implementation and effects of the user identity authentication method according to the present invention with reference to the accompanying drawings and preferred embodiments.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application. This application is, however, susceptible of embodiment in many other ways than those herein described and similar generalizations can be made by those skilled in the art without departing from the spirit of the application and the application is therefore not limited to the specific embodiments disclosed below.
When the performance test of the unmanned aerial vehicle power system is carried out, the performance of the motor and the motor controller is concerned, and the performance of the motor or the motor controller under the condition that the motor, the motor controller and the propeller are matched together for use is concerned. When a universal test bench for a towed motor is used to test a motor, a motor controller and a propeller in an unmanned power system, there are only the respective performance of the motor and the motor controller or the combined operating characteristics of the two components. The following problems exist when the existing stand special for power test of the unmanned aerial vehicle is used (the propeller is arranged in the net cover for test): the test bench has overlarge volume and higher requirements on a test environment, and the test process is complex and the energy consumption is high because a propeller entity needs to be arranged; the propeller has safety risks such as breakage and ejection, for example, the propeller is arranged in the net cover, but broken propeller fragments are extremely likely to be drilled out from the net holes.
Aiming at the performance test scene of the unmanned aerial vehicle power system, the unmanned aerial vehicle power system test system is provided for performing performance test on the motor or the motor controller under the condition that the motor, the motor controller and the propeller are matched together for use, so as to obtain a test result matched with a real use scene, and for reducing the requirement on the test environment, so that the test process is simpler and safer. The following provides examples to describe the above-described unmanned aerial vehicle electrical test system in detail.
Fig. 1 is a schematic diagram of a testing system for an unmanned aerial vehicle according to a first embodiment of the present application, and the following describes the testing system for an unmanned aerial vehicle according to the present embodiment in detail with reference to fig. 1. The embodiments referred to in the following description are intended to illustrate the method principles and not to limit the practical use.
As shown in fig. 1, the unmanned aerial vehicle motor test system provided in the present embodiment includes a power supply 1, a motor control operation unit 2, and an analog test unit 3;
the power supply 1 is electrically connected with the motor control operation unit 2, and is used for providing electric energy for the motor control operation unit 2.
The motor control operation unit 2 comprises a tested motor, a test accompanying motor for providing a load for the tested motor, a first motor controller for controlling the operation of the tested motor, a second motor controller for controlling the operation of the test accompanying motor, and a motor connecting mechanism for enabling the tested motor to drag the test accompanying motor to rotate together; the motor controller is also called an electric motor, is called an electronic speed regulator (Electronic Speed Control, ESC) and can be divided into a brush electric motor and a brushless electric motor according to different motors, can comprise various collectors such as a voltage sensor, a current sensor and a torque sensor, transmits collected data to the simulation test unit 3, can regulate the rotating speed of the motor according to a control signal of the simulation test unit 3, and can drive the motor to complete various instructions to simulate the actual working function of the motor so as to achieve the effect similar to the actual situation. The second motor controller is configured to receive a motor simulation operation parameter for simulating the operation of the target propeller, which is sent by the simulation test unit, and control the operation of the accompanying motor based on the motor simulation operation parameter, so that the accompanying motor is used as a load of the tested motor, namely, when the tested motor drags the accompanying motor to rotate, the accompanying motor applies a reverse moment in a mode of simulating the operation of the target propeller, and the reverse moment is used as the load of the tested motor; the target propeller is a propeller used by the target unmanned aerial vehicle, and the tested motor is used for driving the target propeller. In this embodiment, the first motor controller and the second motor controller have the same specification, and the motor to be tested and the accompanying motor have the same specification.
The simulation test unit 3 is used for obtaining the operation parameters of the target propeller; converting the operation parameters of the target propeller into the motor simulation operation parameters; transmitting the motor simulated operating parameters to the second motor controller; and responding to the operation of the tested motor and the accompanying motor, acquiring the operation parameters of the tested motor, for example, acquiring the parameters such as voltage, current, rotating speed, torque and the like of the tested motor through various sensors arranged on a first motor controller, and performing performance test on the tested motor, or performing performance test on the first motor controller, or performing performance test on the tested motor and the first motor controller respectively based on the operation parameters of the tested motor.
The operation parameter of the target propeller may be one or more of parameters such as a rotation speed, a torque, a tension, a wind speed, and a power of the target propeller, which may be a preset parameter (for example, a preset tension value of the target propeller), or may be an operation parameter that is obtained and matches with a structural parameter of the target propeller (for example, a diameter, a pitch, and a blade width of the target propeller), for example, in this embodiment, the obtaining, by the simulation test unit 3, the operation parameter of the target propeller may be: establishing a first corresponding relation between propeller structural parameters and propeller operation parameters based on existing propeller entity power test data or unmanned aerial vehicle historical operation data; obtaining structural parameters such as the diameter, the pitch, the blade width and the like of the target propeller, wherein the structural parameters are known for a given target propeller; and obtaining the operation parameters of the target propeller based on the first corresponding relation and the structural parameters of the target propeller.
In this embodiment, the establishing of the first correspondence between the propeller structural parameter and the propeller operation parameter based on the propeller entity power test data or the unmanned aerial vehicle historical operation data may be specifically implemented by the following manner: firstly, acquiring structural parameters of a propeller entity and corresponding propeller operation parameters in a scene of performing power test on the propeller entity of an unmanned aerial vehicle or in a historical operation scene of the unmanned aerial vehicle; secondly, carrying out data fitting processing on the structural parameters of the propeller entity and the propeller operation parameters corresponding to the structural parameters to obtain a function formula for representing the corresponding relation between the structural parameters of the propeller and the propeller operation parameters, wherein the function formula is a first corresponding relation between the structural parameters of the propeller and the propeller operation parameters, for example, a propeller tension calculation formula is obtained after the data fitting processing: diameter (D) (meter) ×pitch (Lj) (meter) ×propeller width (H) (meter) ×rotational speed (V) (revolutions/sec) ×1 atmospheric pressure (P) (1 normal atmospheric pressure) ×empirical coefficient (k) =pull force (L) (Kg). And obtaining the operation parameters of the target propeller based on the first corresponding relation and the structural parameters of the target propeller, namely substituting the structural parameters of the target propeller into the formula, and presetting a part of operation parameters to be known (for example, presetting the pull force L of the target propeller to be known), thereby obtaining the rotating speed V of the target propeller.
It should be noted that, in another implementation scenario, the analog test unit 3 may also be used to: based on the operation parameters of the target propeller and the first corresponding relation between the pre-established propeller structure parameters and the propeller operation parameters, the structure parameters of the target propeller are obtained, and in this way, in the process of selecting the propeller without a given propeller structure, the selection of the structure parameters such as the diameter, the pitch, the blade width and the like can be realized based on the operation parameters of the given target propeller, for example, the selection of the propeller is based on the pull value of the given target propeller.
In this embodiment, the above simulation test unit 3 converts the operation parameter of the target propeller into the motor simulation operation parameter, which may specifically be: firstly, establishing a second corresponding relation between propeller operation parameters and motor operation parameters based on propeller entity power test data or unmanned aerial vehicle historical operation data; for example, in a scene of performing power test on a propeller entity of the unmanned aerial vehicle or in a historical operation scene of the unmanned aerial vehicle, acquiring and obtaining operation parameters of the propeller entity and motor operation parameters (parameters such as voltage, current, rotating speed, torque and the like) corresponding to the operation parameters; and performing data fitting processing on the operation parameters of the propeller entity and the motor operation parameters corresponding to the operation parameters to obtain a function formula for representing the corresponding relation between the operation parameters of the propeller and the motor operation parameters. And secondly, converting the operation parameters of the target propeller into motor simulation operation parameters based on the second corresponding relation, for example, substituting the operation parameters of the target propeller into the formula to obtain the motor simulation operation parameters.
In this embodiment, the power supply is a bidirectional grid-connected power supply, and the bidirectional grid-connected power supply is electrically connected with the first motor controller and the second motor controller, and is configured to provide electric energy for the motor under test, and receive electric energy generated by the accompanying motor, where the motor under test works in an electric state, and the accompanying motor works in a power generation state. The first motor controller is electrically connected with the tested motor and the bidirectional grid-connected power supply, and can convert electric energy from the bidirectional grid-connected power supply (such as direct current to alternating current and output voltage control range) and provide the electric energy for the tested motor, and the second motor controller is electrically connected with the accompanying motor and the bidirectional grid-connected power supply, and can convert electric energy generated by the accompanying motor (such as alternating current to direct current) and provide the electric energy for the bidirectional grid-connected power supply.
In this embodiment, the motor connecting mechanism connects the tested motor and the accompanying motor in a flexible connection manner, specifically, the motor connecting mechanism includes a driving wheel fixedly connected with the end of the output shaft of the tested motor, a driven wheel fixedly connected with the end of the output shaft of the accompanying motor, and a synchronous belt connecting the driving wheel and the driven wheel, and the synchronous belt can be made of rubber or nylon. The existing motor is to dragging the process and adopts rigid connection modes such as shaft coupling, and the shaft coupling connection needs high-accuracy rack spare part, and its design cost is high, and the debugging centering degree of difficulty is big, comparatively consuming time (for example, because the bad damage that can lead to the motor that is surveyed in centering, therefore, when the motor is installed to rack fixing base, because motor machining precision problem, need adjust motor shaft and shaft coupling central point for two axial lead are on same straight line, this process consuming time is longer), this embodiment is through above-mentioned flexible connection mode connection motor and the motor of surveying of accompanying, it is lower to the centering requirement of connection, it is big clearance that allows when being connected with the hold-in range to follow driving wheel and drive wheel, it is simple high-efficient.
The unmanned aerial vehicle motor test system that this embodiment provided includes: the device comprises a power supply, a motor control operation unit and an analog test unit; the power supply is electrically connected with the motor control operation unit and is used for providing electric energy for the motor control operation unit; the motor control operation unit comprises a tested motor, a test accompanying motor for providing a load for the tested motor, a first motor controller for controlling the operation of the tested motor, a second motor controller for controlling the operation of the test accompanying motor, and a motor connecting mechanism for enabling the tested motor to drag the test accompanying motor to rotate together; the second motor controller is configured to receive motor simulation operation parameters which are sent by the simulation test unit and used for simulating the operation of the target propeller, and control the operation of the accompanying motor based on the motor simulation operation parameters so as to enable the accompanying motor to serve as the load of the motor to be tested; the target propeller is a propeller used by the target unmanned aerial vehicle, and the tested motor is used for driving the target propeller; the simulation test unit is used for obtaining the operation parameters of the target propeller; converting the operation parameters of the target propeller into motor simulation operation parameters; transmitting the motor simulated operation parameters to a second motor controller; and responding to the running of the tested motor and the accompanying motor, acquiring and obtaining the running parameters of the tested motor, and performing performance test on the tested motor and/or the first motor controller based on the running parameters of the tested motor. The second motor controller is configured to receive the motor simulation operation parameters for simulating the operation of the target propeller, and control the operation of the accompanying motor based on the motor simulation operation parameters, namely, when the tested motor drags the accompanying motor to rotate, the accompanying motor applies reverse moment in a mode of simulating the operation of the target propeller, and the reverse moment is used as a load required by the tested motor, so that the performance test can be performed on the motor or the motor controller under the condition of simulating the operation of the propeller by using the unmanned aerial vehicle motor test system, a test result matched with a real use scene can be obtained, and the test result meets the scene requirement of the motor, the motor controller and the propeller for common cooperation. And, for current unmanned aerial vehicle power test special stand (through locating the screw in the screen panel and carrying out motor performance test), unmanned aerial vehicle motor test system that this embodiment provided need not to carry out motor performance test based on screw entity to can reduce the requirement to test the environment, so that the test process is simpler, safe.
In one typical configuration, a computing device includes one or more processors (CPUs), input/output interfaces, network interfaces, and memory.
The memory may include volatile memory in a computer-readable medium, random Access Memory (RAM) and/or nonvolatile memory, such as Read Only Memory (ROM) or flash memory (flash RAM). Memory is an example of computer-readable media.
1. Computer readable media, including both non-transitory and non-transitory, removable and non-removable media, may implement information storage by any method or technology. The information may be computer readable instructions, data structures, modules of a program, or other data. Examples of storage media for a computer include, but are not limited to, phase change memory (PRAM), static Random Access Memory (SRAM), dynamic Random Access Memory (DRAM), other types of Random Access Memory (RAM), read Only Memory (ROM), electrically Erasable Programmable Read Only Memory (EEPROM), flash memory or other memory technology, compact disc read only memory (CD-ROM), digital Versatile Discs (DVD) or other optical storage, magnetic cassettes, magnetic tape magnetic disk storage or other magnetic storage devices, or any other non-transmission medium, which can be used to store information that can be accessed by a computing device. Computer readable media, as defined herein, does not include non-transitory computer readable media (transmission media), such as modulated data signals and carrier waves.
2. It will be appreciated by those skilled in the art that embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present invention is not limited to the above-mentioned embodiments, but is intended to be limited to the following embodiments, and any modifications, equivalents and modifications can be made to the above-mentioned embodiments without departing from the scope of the invention.
Claims (9)
1. An unmanned aerial vehicle electrical testing system, comprising:
the device comprises a power supply, a motor control operation unit and an analog test unit;
the power supply is electrically connected with the motor control operation unit and is used for providing electric energy for the motor control operation unit;
the motor control operation unit comprises a tested motor, a test accompanying motor for providing a load for the tested motor, a first motor controller for controlling the operation of the tested motor, a second motor controller for controlling the operation of the test accompanying motor, and a motor connecting mechanism for enabling the tested motor to drag the test accompanying motor to rotate together; the second motor controller is configured to receive motor simulation operation parameters for simulating the operation of the target propeller, which are sent by the simulation test unit, and control the operation of the accompanying motor based on the motor simulation operation parameters so as to enable the accompanying motor to serve as the load of the tested motor; the target propeller is a propeller used by a target unmanned aerial vehicle, and the tested motor is used for driving the target propeller;
the simulation test unit is used for obtaining the operation parameters of the target propeller, wherein the operation parameters of the target propeller are preset parameters or are obtained operation parameters matched with the structural parameters of the target propeller; converting the operating parameters of the target propeller into the motor simulation operating parameters, including: establishing a second corresponding relation between the propeller operation parameters and the motor operation parameters based on the propeller entity power test data or the unmanned aerial vehicle historical operation data; converting the operation parameters of the target propeller into the motor simulation operation parameters based on the second corresponding relation; transmitting the motor simulated operating parameters to the second motor controller; and responding to the operation of the tested motor and the accompanying motor, acquiring and obtaining the operation parameters of the tested motor, and performing performance test on the tested motor and/or the first motor controller based on the operation parameters of the tested motor.
2. The unmanned aerial vehicle electrical test system of claim 1, wherein the obtaining the operating parameters of the target propeller comprises:
establishing a first corresponding relation between the propeller structure parameter and the propeller operation parameter based on the propeller entity power test data or the unmanned aerial vehicle historical operation data;
obtaining structural parameters of the target propeller;
and obtaining the operation parameters of the target propeller based on the first corresponding relation and the structural parameters of the target propeller.
3. The unmanned aerial vehicle electrical test system of claim 2, wherein the establishing a first correspondence between propeller structural parameters and propeller operating parameters based on propeller entity power test data or unmanned aerial vehicle historical operating data comprises:
acquiring structural parameters of the propeller entity and corresponding propeller operation parameters in a scene of performing power test on the propeller entity of the unmanned aerial vehicle or in a historical operation scene of the unmanned aerial vehicle;
and carrying out data fitting processing on the structural parameters of the propeller entity and the propeller operation parameters corresponding to the structural parameters to obtain a function formula for representing the corresponding relation between the structural parameters of the propeller and the propeller operation parameters.
4. The unmanned aerial vehicle electrical test system of claim 1, wherein the establishing a second correspondence between propeller operating parameters and motor operating parameters based on propeller entity power test data or unmanned aerial vehicle historical operating data comprises:
acquiring and obtaining the operation parameters of the propeller entity and the motor operation parameters corresponding to the operation parameters in a scene of performing power test on the propeller entity of the unmanned aerial vehicle or in a historical operation scene of the unmanned aerial vehicle;
and performing data fitting processing on the operation parameters of the propeller entity and the motor operation parameters corresponding to the operation parameters to obtain a function formula for representing the corresponding relation between the operation parameters of the propeller and the motor operation parameters.
5. The unmanned aerial vehicle motor test system of claim 1, wherein the motor connection mechanism connects the motor under test and the accompanying motor by way of a flexible connection.
6. The unmanned aerial vehicle motor test system of claim 5, wherein the motor connection mechanism comprises a drive wheel fixedly connected to an output shaft end of the motor under test, a driven wheel fixedly connected to an output shaft end of the accompanying motor, and a timing belt connecting the drive wheel and the driven wheel.
7. The unmanned aerial vehicle electrical test system of claim 1, wherein the power supply is a bi-directional grid-connected power supply electrically connected to the first and second motor controllers, respectively, for providing electrical power to the motor under test and receiving electrical power generated by the accompanying motor.
8. The unmanned aerial vehicle electrical test system of claim 1, wherein the analog test unit is further configured to: and obtaining the structural parameter of the target propeller based on the operation parameter of the target propeller and a first corresponding relation between the pre-established structural parameter of the propeller and the operation parameter of the propeller.
9. The unmanned aerial vehicle motor test system of claim 1, wherein the first motor controller is the same specification as the second motor controller, and the motor under test is the same specification as the accompanying motor.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211507920.3A CN115542158B (en) | 2022-11-29 | 2022-11-29 | Unmanned aerial vehicle motor test system |
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