CN115542158A - Unmanned aerial vehicle motor test system - Google Patents
Unmanned aerial vehicle motor test system Download PDFInfo
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- CN115542158A CN115542158A CN202211507920.3A CN202211507920A CN115542158A CN 115542158 A CN115542158 A CN 115542158A CN 202211507920 A CN202211507920 A CN 202211507920A CN 115542158 A CN115542158 A CN 115542158A
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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 a simulation test unit; the power supply is used for supplying electric energy to the motor control operation unit; the motor control operation unit comprises a tested motor, an accompanying motor, 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 controls the operation of the accompanying test 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; sending the motor simulation operation parameters to a second motor controller; and responding to the running of the tested motor and the accompanying tested motor, acquiring the running parameters of the tested motor, and carrying out 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 a motor test system of an unmanned aerial vehicle.
Background
In recent years, the development of unmanned aerial vehicle technology and application thereof is rapidly advanced, and the intelligent unmanned aerial vehicle becomes an important direction of intelligent technology development. The common motor is to dragging the test rack and can set up the torque value of accompanying the measuring motor and come to add the load for the measured motor to verify the performance of measured motor or the performance of machine controller, this in-process, the measured motor drags to accompany the measuring motor and rotates, accompany the measuring motor and apply reverse moment, as the load of measured motor, this process can accomplish the test demand to machine performance and machine controller performance, provide corresponding help for the development of the type selection of motor, machine controller algorithm and hardware circuit. However, when the performance test of the power system of the unmanned aerial vehicle 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 used together is more 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 used together 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 how to perform performance test on a motor or a motor controller under the condition that the motor, the motor controller and a propeller are used together.
In order to solve or improve the above technical problem to a certain extent, according to an aspect of the present invention, there is provided an unmanned aerial vehicle motor testing system, including:
the device comprises a power supply, a motor control operation unit and a simulation test unit;
the power supply is electrically connected with the motor control operation unit and is used for supplying electric energy to the motor control operation unit;
the motor control operation unit comprises a tested motor, an accompanying motor for providing load for the tested motor, a first motor controller for controlling the tested motor to operate, a second motor controller for controlling the accompanying motor to operate, and a motor connecting mechanism for driving the tested motor to drag the accompanying motor to rotate in unison; 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 a target propeller, and control the operation of the accompanying motor based on the motor simulation operation parameters, so that the accompanying motor serves as a 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; sending the motor simulation operation parameters to the second motor controller; responding to the operation of the tested motor and the accompanying tested motor, acquiring the operation parameters of the tested motor, and carrying out 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 operational parameter of the target propeller comprises:
establishing a first corresponding relation between propeller structure parameters and propeller operation parameters based on propeller entity power test data or historical unmanned aerial vehicle 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 corresponding relationship between the propeller structure parameters and the propeller operation parameters based on the propeller entity power test data or the historical operation data of the unmanned aerial vehicle includes:
acquiring and obtaining structural parameters of a propeller entity and propeller operation parameters corresponding to the structural parameters in a scene of performing a power test on the propeller entity of the unmanned aerial vehicle or a historical operation scene of the unmanned aerial vehicle;
and performing data fitting processing on the structural parameters of the propeller entity and the propeller operation parameters corresponding to the structural parameters of the propeller entity to obtain a function formula for representing the corresponding relation between the propeller structural parameters and the propeller operation parameters.
In some embodiments, said converting the operational parameters of the target propeller into the motor simulation operational parameters comprises:
establishing a second corresponding relation between propeller operation parameters and motor operation parameters based on propeller entity power test data or historical unmanned aerial vehicle 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 operating parameters and the motor operating parameters based on the propeller entity dynamic test data or the historical operating data of the unmanned aerial vehicle includes:
acquiring and obtaining operation parameters of a propeller entity and motor operation parameters corresponding to the operation parameters in a scene of performing a power test on the propeller entity of the unmanned aerial vehicle or 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 propeller operation parameters and the motor operation parameters.
In some embodiments, the motor connecting mechanism connects the motor to be tested and the motor to be tested through a flexible connection mode.
In some embodiments, the motor connecting mechanism includes a driving wheel fixedly connected to the end of the output shaft of the motor under test, a driven wheel fixedly connected to the end of the output shaft of the motor under test, and a timing 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 to the first motor controller and the second motor controller respectively, and is configured to provide electric energy to the motor under test and receive electric energy generated by the motor under test.
In some embodiments, the simulation test unit is further configured to: and obtaining the structural parameters of the target propeller based on the operating parameters of the target propeller and a first corresponding relation between the pre-established propeller structural parameters and the propeller operating parameters.
In some embodiments, the first motor controller and the second motor controller are of the same specification, and the motor under test is of the same specification as the motor under test.
Compared with the prior art, the invention has the following advantages:
the invention provides an unmanned aerial vehicle motor test system, which comprises: the device comprises a power supply, a motor control operation unit and a simulation test unit; the power supply is electrically connected with the motor control operation unit and used for supplying electric energy to the motor control operation unit; the motor control operation unit comprises a tested motor, an accompanying motor for providing 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 accompanying motor, and a motor connecting mechanism for driving the tested 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 test-accompanying motor based on the motor simulation operation parameters, so that the test-accompanying motor is used as the load of the tested motor; the target propeller is a propeller used by the target unmanned aerial vehicle, and the detected 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; sending the motor simulation operation parameters to a second motor controller; and responding to the running of the tested motor and the accompanying tested motor, acquiring the running parameters of the tested motor, and carrying out performance test on the tested motor and/or the first motor controller based on the running parameters of the tested motor. Because the second motor controller is configured to receive the motor simulation operation parameters which are sent by the simulation test unit and used for simulating the operation of the target propeller, and controls 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 torque in a mode of simulating the operation of the target propeller to serve as the load required by the tested motor, therefore, by using the unmanned aerial vehicle motor test system, the performance test can be carried out on the motor or the motor controller under the condition of simulating the operation of the propeller, the test result matched with the actual use scene can be obtained, and the test result meets the scene requirement of the common cooperation use of the motor, the motor controller and the propeller.
The foregoing description is only an overview of the technical solutions of the present invention, and in order to make the technical means of the present invention more clearly understood, the present invention may be implemented in accordance with the content of the description, and in order to make the above and other objects, features, and advantages of the present invention more clearly understood, the following preferred embodiments are specifically described below with reference to the accompanying drawings.
Drawings
Fig. 1 is a schematic diagram of an unmanned aerial vehicle motor test system provided by an embodiment of the present application.
Detailed Description
To further illustrate the technical means and effects of the present invention adopted to achieve the predetermined objects, the following detailed description will be given to the specific embodiments and effects of the user identity authentication method according to the present invention with reference to the accompanying drawings.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application. This application is capable of implementation in many different ways than those herein set forth and of similar import by those skilled in the art without departing from the spirit of this application and is therefore not limited to the specific implementations 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 used together is more concerned. When a universal counter-trailing motor test rig is used to test the motor, motor controller and propeller in an unmanned aerial vehicle powered system, there are situations where only the respective performance of the motor and motor controller or the combined operating characteristics of the two components can be tested. The existing special stand for testing the power of the unmanned aerial vehicle (the propeller is arranged in the mesh enclosure for testing) has the following problems: the test bench has overlarge volume and higher requirement on the test environment, and the test process is more complicated and the energy consumption is high because a propeller entity needs to be arranged; there is a safety risk of the propeller breaking, shooting the propeller etc., e.g. by placing the propeller in a mesh, but there is also an extreme possibility that broken fragments of the propeller will drill out of the mesh.
To above-mentioned unmanned aerial vehicle driving system capability test scene, in order to carry out capability test to motor or motor controller under the condition that motor, motor controller and screw three cooperate the use jointly to obtain with real use scene assorted test result, and in order to reduce to test environment's requirement, so that the test procedure is comparatively simple, safety, this application provides an unmanned aerial vehicle motor test system. The following provides the embodiment and explains unmanned aerial vehicle motor test system in detail.
Fig. 1 is a schematic diagram of an unmanned aerial vehicle motor test system provided in a first embodiment of the present application, and the unmanned aerial vehicle motor test system provided in this embodiment is described in detail below with reference to fig. 1. The following description refers to embodiments for the purpose of illustrating the principles of the methods, and is not intended to be limiting in actual use.
As shown in fig. 1, the unmanned aerial vehicle motor test system provided by this embodiment includes a power supply 1, a motor control operation unit 2, and a simulation 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, an accompanying motor for providing 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 accompanying motor, and a motor connecting mechanism for driving the tested motor to drive the accompanying motor to rotate together; the motor controller is also called an Electronic governor (Electronic Speed controller, ESC), and can be divided into a brush Electronic governor and a brushless Electronic governor according to different motors, and the Electronic governor can include various collectors such as a voltage sensor, a current sensor and a torque sensor, and transmit collected data to the simulation test unit 3, and can adjust the rotating Speed of the motor according to a Control signal of the simulation test unit 3, and drive the motor to complete various instructions, so as to simulate the real working function of the motor, and achieve the effect similar to the real situation. 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 test motor based on the motor simulation operation parameters, so that the test motor is used as a load of the tested motor, namely, when the tested motor drags the test motor to rotate, the test motor applies a reverse torque in a mode of simulating the operation of the target propeller and is used as the load of the tested motor; wherein, the target screw is the screw that target unmanned aerial vehicle used, and the motor that is surveyed is used for driving this target screw. In this embodiment, the first motor controller and the second motor controller have the same specification, and the motor to be tested 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; sending the motor simulation operation parameters to the second motor controller; the method comprises the steps of responding to the running of a tested motor and an accompanying motor, acquiring running parameters of the tested motor, for example, acquiring parameters such as voltage, current, rotating speed and torque of the tested motor through various sensors arranged on a first motor controller, and carrying out performance test on the tested motor or the first motor controller or respectively carrying out performance test on the tested motor and the first motor controller based on the running parameters of the tested motor.
The operational parameter of the target propeller may be one or more of the parameters of the target propeller, such as the rotation speed, the torque, the tension, the wind speed, the power, etc., which may be a preset parameter (for example, a preset tension value of the target propeller), or an operational parameter matched with a structural parameter of the target propeller (for example, the diameter, the pitch, the blade width of the propeller), for example, in this embodiment, the obtaining of the operational parameter of the target propeller by the simulation test unit 3 may be: establishing a first corresponding relation between propeller structure parameters and propeller operation parameters based on existing propeller entity power test data or historical unmanned aerial vehicle operation data; obtaining structural parameters such as the diameter, the pitch, the blade width and the like of a target propeller, wherein the structural parameters of the given target propeller are known; 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 first corresponding relationship between the propeller structure parameters and the propeller operation parameters is established based on propeller entity power test data or historical unmanned aerial vehicle operation data, and the first corresponding relationship can be specifically realized in the following manner: firstly, acquiring and obtaining structural parameters of a propeller entity and propeller operation parameters corresponding to the structural parameters in a scene of performing a power test on the propeller entity of the unmanned aerial vehicle or in a historical operation scene of the unmanned aerial vehicle; secondly, performing 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 propeller structural parameters and the propeller operation parameters, wherein the function formula is the first corresponding relation between the propeller structural parameters and the propeller operation parameters, and for example, obtaining a propeller tension calculation formula after the data fitting processing: diameter (D) (meter) × pitch (Lj) (meter) × propeller width (H) (meter) × rotation speed (V) (revolutions/sec) × 1 atmospheric pressure (P) (1 standard atmospheric pressure) × empirical coefficient (k) = tensile force (L) (Kg). The obtaining of the operating parameter of the target propeller based on the first corresponding relationship and the structural parameter of the target propeller is to substitute the structural parameter of the target propeller into the formula, and preset a part of the operating parameters to be known (for example, preset the tension L of the target propeller to be known), so as to obtain the rotating speed V of the target propeller.
It should be noted that, in another implementation scenario, the simulation test unit 3 may further be configured to: the method comprises the steps of obtaining structural parameters of a target propeller based on the operation parameters of the target propeller and the pre-established first corresponding relation between the propeller structural parameters and the propeller operation parameters, and realizing selection of the structural parameters such as diameter, pitch, blade width and the like based on the given operation parameters of the target propeller in the propeller model selection process under the condition that the propeller structure is not given, for example, selecting the propeller based on the given tension value of the target propeller.
In this embodiment, the simulation testing unit 3 converts the operation parameters of the target propeller into motor simulation operation parameters, 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 historical unmanned aerial vehicle operation data; for example, in a scene of performing a power test on a propeller entity of an unmanned aerial vehicle or in a historical operating scene of the unmanned aerial vehicle, acquiring and obtaining operating parameters of the propeller entity and motor operating parameters (such as voltage, current, rotating speed and torque) corresponding to the operating 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 propeller operation parameters and the motor operation parameters. Secondly, based on the second corresponding relation, the operation parameters of the target propeller are converted into motor simulation operation parameters, for example, the motor simulation operation parameters can be obtained by substituting the operation parameters of the target propeller into the formula.
In this embodiment, the power is two-way power that is incorporated into the power networks, this two-way power that is incorporated into the power networks respectively with first motor controller and second motor controller electric connection for provide the electric energy to the motor under test, and receive the electric energy of accompanying the survey motor and generating, the motor under test work is at the electric state, accompanies the survey motor work at the power generation state. The first motor controller is electrically connected with the tested motor and the bidirectional grid-connected power supply, can convert electric energy from the bidirectional grid-connected power supply (such as converting direct current into alternating current and outputting voltage control range) and then supply the electric energy to the tested motor, the second motor controller is electrically connected with the accompanying and testing motor and the bidirectional grid-connected power supply, and can convert electric energy generated by the accompanying and testing motor (such as converting alternating current into direct current) and then supply the electric energy to the bidirectional grid-connected power supply.
In this embodiment, above-mentioned motor coupling mechanism is connected the measured motor and is accompanied the measuring motor through flexonics's mode, and is specific, motor coupling mechanism include with the drive wheel of being measured the output shaft end fixed connection of motor, with accompany measuring the output shaft end fixed connection of motor from the driving wheel and connect the drive wheel and follow the hold-in range of driving wheel, this hold-in range can adopt rubber or nylon preparation. The current motor adopts rigid connection methods such as shaft coupling to drag the process, the shaft coupling connection needs rack spare part of high accuracy, its design cost is high, and debugging centering degree of difficulty is big, it is consuming time (for example, because the centering harmfully can lead to the damage of being surveyed the motor, therefore, the motor is when installing on the rack fixing base, because the motor machining precision problem, need adjustment motor shaft and shaft coupling central point, make two axial leads on same straight line, this process is consuming time longer, this embodiment is connected by above-mentioned flexible connection mode and is surveyed the motor and accompany and survey the motor, it is lower to the centering nature requirement of connecting, from driving wheel and drive wheel allow bigger clearance when being connected with the hold-in range, 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 a simulation test unit; the power supply is electrically connected with the motor control operation unit and used for supplying electric energy to the motor control operation unit; the motor control operation unit comprises a tested motor, an accompanying motor for providing 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 accompanying motor, and a motor connecting mechanism for driving the tested 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 test-accompanying motor based on the motor simulation operation parameters, so that the test-accompanying motor is used as the load of the tested motor; the target propeller is a propeller used by the target unmanned aerial vehicle, and the detected 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; sending the motor simulation operation parameters to a second motor controller; and responding to the running of the tested motor and the accompanying tested motor, acquiring the running parameters of the tested motor, and carrying out performance test on the tested motor and/or the first motor controller based on the running parameters of the tested motor. Because the second motor controller is configured to receive the motor simulation operation parameters which are sent by the simulation test unit and used for simulating the operation of the target propeller, and controls 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 torque in a mode of simulating the operation of the target propeller to serve as the load required by the tested motor, therefore, by using the unmanned aerial vehicle motor test system, the performance test can be carried out on the motor or the motor controller under the condition of simulating the operation of the propeller, the test result matched with the actual use scene can be obtained, and the test result meets the scene requirement of the common cooperation use of the motor, the motor controller and the propeller. And, for the special rack of current unmanned aerial vehicle power test (through locating the screw and carrying out motor performance test in the screen panel), the unmanned aerial vehicle motor test system that this embodiment provided need not to carry out motor performance test based on the screw entity to can reduce the requirement to testing environment, so that the test procedure is simpler, safety.
In a typical configuration, a computing device includes one or more processors (CPUs), input/output interfaces, network interfaces, and memory.
The memory may include forms of volatile memory in a computer readable medium, random Access Memory (RAM) and/or non-volatile memory, such as Read Only Memory (ROM) or flash memory (flash RAM). Memory is an example of a computer-readable medium.
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 computer storage media 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 Disks (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. As defined herein, computer readable media does not include non-transitory computer readable media (transient media), such as modulated data signals and carrier waves.
2. As will be appreciated by one skilled in the art, 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.
Although the present invention has been described with reference to a preferred embodiment, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. An unmanned aerial vehicle motor test system, its characterized in that includes:
the device comprises a power supply, a motor control operation unit and a simulation test unit;
the power supply is electrically connected with the motor control operation unit and is used for supplying electric energy to the motor control operation unit;
the motor control operation unit comprises a tested motor, an accompanying motor for providing load for the tested motor, a first motor controller for controlling the tested motor to operate, a second motor controller for controlling the accompanying motor to operate, and a motor connecting mechanism for driving the accompanying motor to rotate together by the tested motor; 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 a target propeller, and control the operation of the accompanying motor based on the motor simulation operation parameters, so that the accompanying motor serves as a 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 operating parameters of the target propeller into the motor simulation operating parameters; sending the motor simulation operation parameters to the second motor controller; responding to the operation of the tested motor and the accompanying tested motor, acquiring the operation parameters of the tested motor, and carrying out performance test on the tested motor and/or the first motor controller based on the operation parameters of the tested motor.
2. The drone motor test system of claim 1, wherein the obtaining operational parameters of the target propeller comprises:
establishing a first corresponding relation between propeller structure parameters and propeller operation parameters based on propeller entity power test data or historical unmanned aerial vehicle 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 motor test system of claim 2, wherein establishing a first correspondence between propeller configuration parameters and propeller operating parameters based on propeller physical power test data or historical unmanned aerial vehicle operating data comprises:
acquiring and obtaining structural parameters of a propeller entity and propeller operation parameters corresponding to the structural parameters in a scene of performing a power test on the propeller entity of the unmanned aerial vehicle or a historical operation scene of the unmanned aerial vehicle;
and performing data fitting processing on the structural parameters of the propeller entity and the propeller operation parameters corresponding to the structural parameters of the propeller entity to obtain a function formula for representing the corresponding relation between the propeller structural parameters and the propeller operation parameters.
4. The drone motor test system of claim 1, wherein the converting the operating parameters of the target propeller into the motor simulation operating parameters comprises:
establishing a second corresponding relation between propeller operation parameters and motor operation parameters based on propeller entity power test data or historical unmanned aerial vehicle operation data;
and converting the operation parameters of the target propeller into the motor simulation operation parameters based on the second corresponding relation.
5. The unmanned aerial vehicle motor test system of claim 4, wherein establishing a second correspondence between propeller operating parameters and motor operating parameters based on propeller entity power test data or historical unmanned aerial vehicle operating data comprises:
acquiring and obtaining operation parameters of a propeller entity and motor operation parameters corresponding to the operation parameters in a scene of performing a power test on the propeller entity of the unmanned aerial vehicle or 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 propeller operation parameters and the motor operation parameters.
6. An unmanned aerial vehicle motor test system as claimed in claim 1, wherein the motor connection mechanism connects the motor under test and the motor under test in a flexible connection manner.
7. The unmanned aerial vehicle motor test system of claim 6, wherein 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.
8. The unmanned aerial vehicle motor test system of claim 1, wherein the power supply is a bidirectional grid-connected power supply, and the bidirectional grid-connected power supply is electrically connected to the first motor controller and the second motor controller respectively, and is configured to provide electric energy to the motor under test and receive electric energy generated by the motor under test.
9. The unmanned aerial vehicle motor test system of claim 1, wherein the simulation test unit is further configured to: and obtaining the structural parameters of the target propeller based on the operating parameters of the target propeller and a first corresponding relation between the pre-established propeller structural parameters and propeller operating parameters.
10. An unmanned aerial vehicle motor test system as claimed in claim 1, wherein the first motor controller is the same as the second motor controller in specification, and the motor under test is the same as the accompanying motor in specification.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211507920.3A CN115542158B (en) | 2022-11-29 | 2022-11-29 | Unmanned aerial vehicle motor test system |
Applications Claiming Priority (1)
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