WO2019061776A1

WO2019061776A1 - Unmanned aerial vehicle test method and apparatus

Info

Publication number: WO2019061776A1
Application number: PCT/CN2017/112690
Authority: WO
Inventors: 钟志勇; 李俊锋; 房玲江
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2017-09-29
Filing date: 2017-11-23
Publication date: 2019-04-04
Also published as: CN107719700B; CN107719700A

Abstract

An unmanned aerial vehicle test method and an unmanned aerial vehicle test apparatus, which relate to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle test method is used for implementing impact testing on an unmanned aerial vehicle, and the unmanned aerial vehicle comprises a power supply (10) and a center plate assembly (20). The unmanned aerial vehicle test method comprises: starting a power supply (10) of an unmanned aerial vehicle (S110); testing an operating state of the unmanned aerial vehicle (S120); detecting the running time of the unmanned aerial vehicle by means of a center plate assembly (20) (S130); and when the center plate assembly (20) determines that the running time is not less than a first preset time, controlling, by means of the center plate assembly (20) , the power supply (10) so same is turned off and restarts (S140).

Description

Unmanned aerial vehicle test method and device

Technical field

The present invention relates to the field of unmanned aerial vehicles, and in particular to an unmanned aerial vehicle test method and an unmanned aerial vehicle test device.

Background technique

At present, unmanned aerial vehicles have been widely used in aerial photography, environmental monitoring and military investigation. With the development of unmanned aerial vehicles, people are increasingly demanding unmanned aerial vehicles. Existing unmanned aerial vehicles typically include a power source, a center plate assembly, a flight control assembly, a power assembly, and the like. Among them, the power supply can be charged and discharged to provide power for the unmanned aerial vehicle, the central plate assembly can be used for power distribution and management, and the flight control component can control the flying height and position of the unmanned aerial vehicle.

Since the UAV is in use, it will undergo a large number of power-on and shutdown operations, causing the power to be turned off and on multiple times, and the power-on and power-off will have an impact on the UAV. Therefore, it is necessary to perform multiple impact tests on the unmanned aerial vehicle before leaving the factory to evaluate the reliability of the unmanned aerial vehicle. In the prior art, the manual operation mode is generally adopted, that is, a certain number of shutdowns and power-on operations are performed manually, and the power supply is continuously turned off and restarted. At the same time, when the power source is in the startup state, the operating state of the unmanned aerial vehicle can be tested. Determine whether the relevant components can still output normally under multiple impacts.

However, in the prior art, the unmanned aerial vehicle is turned on and off by manual operation, which results in low work efficiency. When the number of unmanned aerial vehicles is large, more test personnel are required, so that the labor cost is high; Due to the low stability of manual operation, deviations are easy to occur, which is not conducive to ensuring the consistency of test results.

It should be noted that the information disclosed in the Background section above is only for enhancement of understanding of the background of the invention, and thus may include information that does not constitute the prior art known to those of ordinary skill in the art.

Summary of the invention

It is an object of the present invention to provide an unmanned aerial vehicle test method and an unmanned aerial vehicle test apparatus that further overcomes at least to some extent one or more problems due to limitations and disadvantages of the related art.

According to an aspect of the present invention, there is provided an unmanned aerial vehicle test method for performing an impact test on an unmanned aerial vehicle, the unmanned aerial vehicle comprising a power supply and a center plate assembly, the unmanned aerial vehicle test method comprising:

Activating the power of the unmanned aerial vehicle;

Testing the operating state of the unmanned aerial vehicle;

Detecting an operating time of the UAV by the center panel assembly;

When the center board assembly determines that the running time is not less than the first preset time, the power supply is turned off and restarted by the center board assembly.

In an exemplary embodiment of the present invention, the UAV further includes a flight control component, and controlling the power to be turned off and restarting includes:

And sending, by the center board component, a restart request signal when the center board component determines that the running time is not less than the first preset time;

Responding to the restart request signal by the flight control component, determining whether to allow restart according to the operating state, and feeding back a restart enable signal by the flight control component when the restart is allowed;

A restart execution signal is issued to the power source by the center board assembly in response to the restart enable signal to control the power supply to be turned off and restarted.

In an exemplary embodiment of the invention, the power off and restart intervals are separated by a second predetermined time.

In an exemplary embodiment of the present invention, the unmanned aerial vehicle testing method further includes:

And when the center board component determines that the running time is less than the first preset time, controlling the power to be turned off.

Detecting the amount of power of the power source;

Determining whether the power of the power source is greater than a preset value;

When the power is not greater than the preset value, the power is turned off.

In an exemplary embodiment of the invention, the operating state of the unmanned aerial vehicle is Line tests include:

It is judged whether the output of the power source is normal.

In an exemplary embodiment of the invention, testing the operational status of the UAV includes:

Determining whether the output of the center plate assembly is normal;

When the output of the center plate assembly is normal, the PTZ component of the UAV is controlled for self-test.

In an exemplary embodiment of the invention, the UAV further includes a power component, and testing the operating state of the UAV includes:

Determining whether the output of the power component is normal;

When the output of the power component is normal, the power component is controlled by the flight control component to output a preset power.

In an exemplary embodiment of the invention, the predetermined power is one-half of a rated power of the power component.

According to an aspect of the invention, there is provided an unmanned aerial vehicle test apparatus for performing an impact test on an unmanned aerial vehicle, the unmanned aerial vehicle comprising a power supply and a centerboard assembly, the unmanned aerial vehicle test apparatus comprising:

a startup module for starting power of the unmanned aerial vehicle;

a test module for testing an operating state of the unmanned aerial vehicle;

a time detecting module, disposed in the center board assembly, configured to detect an operating time of the UAV through the center board assembly;

The first control module is disposed on the center board assembly, and is configured to control, by the center board assembly, the power to be turned off and restarted when the center board assembly determines that the running time is not less than a first preset time.

In an exemplary embodiment of the present invention, the UAV further includes a flight control component, and the first control module includes:

a requesting unit, configured to send, by the center board component, a restart request signal when the center board component determines that the running time is not less than the first preset time;

a feedback unit, configured to respond to the restart request signal by the flight control component, determine whether to allow restart according to the running state, and when the restart is allowed, pass the flight control component Feed restart enable signal;

And an execution unit, configured to send a restart execution signal to the power source by the center board component in response to the restart permission signal to control the power supply to be turned off and restarted.

In an exemplary embodiment of the present invention, the first control module is further configured to control the power off when the center board component determines that the running time is less than the first preset time.

In an exemplary embodiment of the present invention, the UAV testing device further includes:

a power detecting module, configured to detect a power quantity of the power source;

a power determining module, configured to determine whether the power of the power source is greater than a preset value;

The second control module is configured to control the power to be turned off when the power is not greater than the preset value.

In an exemplary embodiment of the invention, the test module includes:

The power determining unit is configured to determine whether the output of the power source is normal.

In an exemplary embodiment of the invention, the test module includes:

a center board component determining unit, configured to determine whether the output of the center board component is normal;

The pan/tilt assembly control unit is configured to control the gimbal component self-test of the unmanned aerial vehicle when the output of the central plate assembly is normal.

In an exemplary embodiment of the present invention, the UAV further includes a power component, and the test module includes:

a power component determining unit, configured to determine whether the output of the power component is normal;

And a power component control unit, configured to control the power component to output a preset power through the flight control component when the output of the power component is normal.

The unmanned aerial vehicle test method and the unmanned aerial vehicle test device of the present invention can detect the running time of the unmanned aerial vehicle through the center plate assembly after the first power supply is started, and the running time of the center plate component is not less than the first preset. At the time, the power supply can be turned off and restarted through the center board assembly. Therefore, after the power is first turned on, the power supply can be automatically turned off and Restart, realize automatic shutdown and start-up of the unmanned aerial vehicle, avoid manual shutdown and restart of the power supply during multiple impact tests, so that work efficiency is improved, which is beneficial to reduce labor costs. At the same time, the deviation caused by manual operation is also avoided, which is beneficial to ensure the consistency of test results. In addition, the operating state of the UAV can be tested while the power is on to evaluate the reliability of the UAV.

The above general description and the following detailed description are intended to be illustrative and not restrictive.

DRAWINGS

The accompanying drawings, which are incorporated in the specification of FIG Obviously, the drawings in the following description are only some embodiments of the present invention, and those skilled in the art can obtain other drawings according to the drawings without any creative work.

1 is a block diagram of an unmanned aerial vehicle in an exemplary embodiment of the present invention.

2 is a flow chart of a method for testing an unmanned aerial vehicle in an exemplary embodiment of the present invention.

FIG. 3 is a flow chart of an exemplary embodiment of step S120 of FIG. 2.

4 is a flow chart of an exemplary embodiment of step S140 of FIG. 2.

FIG. 5 is a flowchart of steps S210 to S230 of the unmanned aerial vehicle testing method according to an exemplary embodiment of the present invention.

6 is a block diagram of an unmanned aerial vehicle test apparatus in an exemplary embodiment of the present invention.

FIG. 7 is a schematic diagram of an operation process of an unmanned aerial vehicle test apparatus according to an exemplary embodiment of the present invention.

Detailed ways

Example embodiments will now be described more fully with reference to the accompanying drawings. However, the example embodiments can be embodied in a variety of forms and should not be construed as being limited to the examples set forth herein; rather, these embodiments are provided to make the invention more comprehensive and complete, and the embodiments of the example embodiments are fully conveyed. To those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the description below, provided Numerous specific details are given to give a full understanding of the embodiments of the invention. However, one skilled in the art will appreciate that the technical solution of the present invention may be practiced and one or more of the specific details may be omitted, or other methods, components, devices, steps, etc. may be employed. In other instances, various aspects of the present invention are not obscured by the detailed description of the embodiments.

In addition, the drawings are merely schematic representations of the invention, and are not necessarily to scale. The same reference numerals in the drawings denote the same or similar parts, and the repeated description thereof will be omitted. Some of the block diagrams shown in the figures are functional entities and do not necessarily have to correspond to physically or logically separate entities. These functional entities may be implemented in software, or implemented in one or more hardware modules or integrated circuits, or implemented in different network and/or processor devices and/or microcontroller devices.

The terms "a", "an", "the" and "the" are used to mean the presence of one or more elements/components, etc.; the terms "including" and "having" are used to mean an inclusive. Meaning and means that there may be additional elements/components/etc. in addition to the listed elements/components/etc; the terms "first", "second", etc. are used only as marks, not the number of objects Restricted and can be combined arbitrarily.

An unmanned aerial vehicle test method for performing an impact test on an unmanned aerial vehicle is provided in the exemplary embodiment. As shown in FIG. 1 , the unmanned aerial vehicle includes a power supply 10 and a center plate assembly 20, but is not limited thereto. The power module 30, the flight control component 40, the pan/tilt assembly 50, and the like may also be included. For details, refer to the existing unmanned aerial vehicles, which will not be enumerated here.

As shown in FIG. 2, the unmanned aerial vehicle test method of the present exemplary embodiment may include:

Step S110, starting the power supply 101 of the UAV.

Step S120: Testing an operating state of the UAV.

Step S130, detecting the running time of the UAV by the center plate assembly 20.

Step S140: When the center board component 20 determines that the running time is not less than the first preset time, the power supply 10 is controlled to be turned off and restarted by the center board component 20.

The unmanned aerial vehicle test method of the example embodiment can perform the power on and off for the unmanned aerial vehicle multiple times, and test the running state after each power on, so as to test the impact caused by the start and shutdown of the unmanned aerial vehicle. In order to evaluate the power of the unmanned aerial vehicle Rely on sex.

After the power source 10 is started for the first time, the running time of the UAV can be detected by the center board assembly 20, and when the center board assembly 20 determines that the running time is not less than the first preset time, the power can be controlled by the center board assembly 20. 10 close and restart. Therefore, after the power source 10 is started for the first time, the automatic shutdown and restart of the power supply 10 can be realized, and the automatic shutdown and startup of the unmanned aerial vehicle can be realized, thereby avoiding manually shutting down and restarting the power supply 10 when the impact test is performed multiple times, so that the work efficiency is achieved. The improvement is beneficial to reduce labor costs. At the same time, the deviation caused by manual operation is also avoided, which is beneficial to ensure the consistency of test results. In addition, when the power source 10 is in the activated state, the operating state of the unmanned aerial vehicle can be tested to evaluate the reliability of the unmanned aerial vehicle.

Hereinafter, each step of the unmanned aerial vehicle test method in the present exemplary embodiment will be further described.

In step S110, the power source 10 of the unmanned aerial vehicle is started.

Power source 10 can be coupled to center plate assembly 20 to provide power to center plate assembly 20. At the same time, the power source 10 may include a battery and a switch device. The battery may be a lithium battery, but not limited thereto. It may also be a fuel cell, a solar cell or other battery, which will not be enumerated here. In addition, the activation and shutdown of the power source 10 can be controlled by manually operating the switch device. For example, the switch button on the UAV can be manually operated to control the startup and shutdown of the power source 10 to enable the UAV to be turned on or off. Of course, the starting and closing of the power source 10 can also be controlled by other control devices, which will not be described in detail herein.

In step S120, the operating state of the unmanned aerial vehicle is tested.

As shown in FIG. 3, testing the operating state of the UAV may include step S1210, wherein:

In step S1210, it is judged whether or not the output of the power source 10 is normal.

When the power source 10 is in the startup state, whether the output of the power source 10 is normal can be judged by manual observation or by using a special detection instrument detection or the like. For example, the power indicator device such as the power supply 10 indicator of the UAV can be manually observed to determine whether the output of the power source 10 is normal; or the output voltage or current of the power source 10 can be detected by the voltage or current detecting device, by determining the output voltage or Whether the output current is in a preset range determines whether the output of the power source 10 is normal. Of course, it is also possible to determine whether the output of the power source 10 is normal by using other means such as detecting the output of the power source 10 by a detecting device preset in the unmanned aerial vehicle. No longer list them one by one.

As shown in FIG. 3, testing the operating state of the UAV may include step S1220 and step S1230, wherein:

In step S1220, it is judged whether or not the output of the center plate assembly 20 is normal.

When the power source 10 is in the startup state, whether the output of the center plate assembly 20 is normal can be judged by manual observation or by using a special detection instrument detection or the like. For details, refer to the implementation manner of determining whether the output of the power source 10 is normal in the above step S1210, and details are not described herein. Correct. Of course, it is also possible to judge whether the output of the center plate assembly 20 is normal by other means, for example, by a specific line detecting device or the like, which will not be enumerated here.

In step S1230, when the output of the center plate assembly 20 is normal, the pan/tilt assembly 50 is controlled to self-test.

In the event that the center panel assembly 20 output is normal, the pan/tilt assembly 50 can be powered up to initiate the pan/tilt assembly 50 for self-testing. The pan/tilt assembly 50 can include a bracket, a controller, a drive, and a position sensing device. The bracket is used to mount the photographic device, and the driving device is used to drive the bracket to drive the photographic device to change the shooting angle. The self-test of the pan-tilt assembly 50 may include a process in which the controller controls the driving device to adjust the posture of the bracket, and the position sensing device senses the posture of the bracket to calibrate the initial posture of the bracket and the photographing device, and may refer to the existing The self-test of the pan/tilt assembly 50 will not be described in detail herein.

As shown in FIG. 3, testing the operating state of the UAV may include step S1240 and step S1250, wherein:

In step S1240, it is judged whether or not the output of the power unit 30 is normal.

The power assembly 30 can include a drive motor and a power ESC, which can be used as a power source for the unmanned aerial vehicle to drive the rotor of the UAV, and the power ESC can be an electronic governor that can drive the speed of the motor. Make adjustments. When the power source 10 is in the starting state, it can be judged whether the power ESC and the driving motor are working normally by manually observing the rotation of the rotor to determine whether the output of the power component 30 is normal; or, the power can be adjusted by a special detecting instrument. The output voltage or the output current is detected to determine whether the output of the power unit 30 is normal. Of course, it is also possible to judge whether the output of the power unit 30 is normal, such as by a specific line detecting device or the like, which will not be enumerated here.

In step S1250, when the output of the power assembly 30 is normal, through the unmanned aerial vehicle The flight control assembly 40 controls the power assembly 30 to output at a preset power.

The flight control assembly 40 can communicate with the power ESC of the power assembly 30 in a wireless or wired manner, so that the power of the drive motor can be adjusted by the power ESC. For example, the power control can be utilized by the flight control assembly 40. The driving motor is outputted at a preset power, which may be half of the rated power of the power component 30, that is, 50%, and may of course be 30%, 40%, 60% of the rated power, and the like.

It should be noted that the above-mentioned UAV may further include other components, such as one or more of a flexible circuit board, a visual component, a graphic transmission component, a GPS component, and a steering gear deformation component, thereby operating the UAV. The state test may further include: determining whether the output of one or more of the flexible circuit board, the visual component, the image transmission component, the GPS component, and the steering gear deformation component is normal, and the specific determination manner refers to the power source 10 and the center plate component. The judgment mode of 20 or the existing judgment mode will not be described in detail herein.

In step S130, the running time of the UAV is detected by the center plate assembly 20.

The run time may be the time from the power up to the power down of the center panel assembly 20, and the center panel assembly 20 may detect the run time in real time if the output of the center panel assembly 20 is normal. Of course, the running time can also be the time when the power source 10 is turned on and off.

In step S140, when the center board assembly 20 determines that the running time is not less than the first preset time, the power supply 10 is controlled to be turned off and restarted by the center board assembly 20.

As shown in FIG. 4, the control power supply 10 is turned off and restarted, and may include steps S1410 to S1430, where:

In step S1410, when the center board assembly 20 determines that the running time is not less than the first preset time, the restart request signal is transmitted through the center board assembly 20.

The center board assembly 20 can compare the detected running time with the first preset time. When the running time is not less than the first preset time, that is, greater than or equal to the first preset time, the running time has reached the first time. At a predetermined time, the next impact test can be initiated, at which point a restart request signal can be sent to the flight control component 40 via the centerboard assembly 20. When it is determined that the running time is less than the first preset time, it indicates that the running time does not reach the first preset time, and the center board component 20 may be faulty. At this time, the restart request signal is not sent, and the power supply 10 is turned off for the purpose of performing Overhaul.

The first preset time may be 35 seconds, but not limited thereto, and may be longer or shorter. For example, 30 seconds, 40 seconds, and the like. At the same time, the first preset time can be determined according to experience or through multiple experiments, and can be adjusted.

In step S1420, the flight control component 40 responds to the restart request signal, determines whether the restart is permitted according to the operating state, and feeds back the restart enable signal through the flight control component 40 when the restart is permitted.

The operational status of the UAV may be detected by the flight control assembly 40 to obtain corresponding operational parameters, which may include attitude information of the UAV and/or status information of components such as the power assembly 30. It can be judged whether the unmanned aerial vehicle is in a state capable of turning off the power source 10 by judging whether the operating parameter meets the preset condition. If the preset condition is met, the restart enable signal can be fed back to the center board assembly 20, allowing the power supply 10 to be turned off, that is, shutting down. If the preset adjustment is not met, the restart enable signal is not fed back.

In step S1430, a restart execution signal is issued to the power source 10 by the center board assembly 20 in response to the restart permission signal to control the power source 10 to be turned off and restarted.

The center board assembly 20 can issue a restart execution signal in response to the restart enable signal described above. After receiving the re-execution signal, the power supply 10 can be turned off and restarted, thereby ending the impact test and starting the next impact test, thereby avoiding manual shutdown and restart. At the same time, after the power supply 10 is turned off, the off state can be continued for the second predetermined time, and then restarted, that is, the second preset time is closed and restarted. The second preset time may be 5 seconds, but not limited thereto, and may be longer or shorter, for example, 1 second, 3 seconds, 7 seconds, and the like.

In addition, the number of times that the control power source 10 is turned off and restarted may be 1000 times, but not limited thereto, and may be less or more, for example, 500 times, 2000 times, and the like.

As shown in FIG. 5, the unmanned aerial vehicle testing method of the present exemplary embodiment may further include steps S210 to 230, wherein:

In step S210, the amount of power of the power source 10 is detected.

This amount of power is the remaining amount of power source 10. The power of the power source 10 can be detected by the center plate assembly 20 or other means.

In step S220, it is determined whether the power of the power source 10 is greater than a preset value.

The preset value may be the minimum amount of power that satisfies the operation of the UAV, which may be determined based on empirical data or experimental data. Of course, the preset value may also be a value greater than or less than the minimum power. The power of the power source 10 can be compared with a preset value to determine whether it is greater than the preset value. If it is greater than the preset value, it indicates that the power supply 10 can also supply power normally; if it is less than the preset value, it indicates that it is difficult to supply power again.

In step S230, when the power is not greater than the preset value, the control power source 10 is turned off.

When it is determined in step S220 that the power of the power source 10 is not greater than a preset value, that is, less than or equal to the preset value, the power of the power source 10 is reduced to or below the minimum power. At this time, the power source 10 can be controlled to be turned off to avoid no The human aircraft is shut down due to the exhaustion of the power source 10 to prevent damage to the unmanned aerial vehicle.

The unmanned aerial vehicle test method of the example embodiment may further include: determining whether the power is manually turned off after determining that the power of the power source 10 is greater than a preset value.

The following is an embodiment of the apparatus of the present invention, which can be used to carry out the method embodiments of the present invention. For details not disclosed in the embodiment of the device of the present invention, please refer to the method embodiment of the present invention.

The present exemplary embodiment further provides an unmanned aerial vehicle testing device for performing an impact test on an unmanned aerial vehicle, which may be an unmanned aerial vehicle in an exemplary embodiment of the above-described unmanned aerial vehicle testing method, which is not The composition will be described in detail.

As shown in FIG. 6, the UAV test apparatus of the present exemplary embodiment may include a startup module 1, a test module 2, a time detection module 3, and a first control module 4.

In the present exemplary embodiment, the activation module 1 can be used to activate the power source 10 of the unmanned aerial vehicle.

In the present exemplary embodiment, the test module 2 can be used to test the operational status of the unmanned aerial vehicle.

The test module 2 may include a power supply determining unit that can be used to determine whether the output of the power source 10 is normal.

The test module 2 may include a center board component judging unit and a pan/tilt head unit control unit, wherein:

The center plate assembly determining unit can be used to determine whether the output of the center plate assembly 20 is normal.

The pan/tilt assembly control unit can be used to control the gimbal assembly 50 self-test of the unmanned aerial vehicle when the output of the center plate assembly 20 is normal.

The test module 2 may include a power component determination unit and a power component control unit, wherein:

The power component determination unit can be used to determine whether the output of the power component 30 is normal.

The power component control unit can be used to control the power component 30 through the flight control component 40 to preset power output when the output of the power component 30 is normal. The preset power is the amount of the power component 30 Half of the fixed power.

In the present exemplary embodiment, the time detection module 3 can be provided to the center panel assembly 20 for detecting the runtime of the UAV through the center panel assembly 20.

In the present exemplary embodiment, the first control module 4 may be disposed on the center board assembly 20, and may control the power source through the center board assembly 20 when the center board assembly 20 determines that the running time is not less than the first preset time. 10 close and restart. The first control module 4 is further configured to control the power supply 10 to be turned off when the center board assembly 20 determines that the running time is less than the first preset time.

The first control module 4 may include a request unit, a feedback unit, and an execution unit, where:

The requesting unit may be configured to send a restart request signal through the center board component 20 when the center board component 20 determines that the running time is not less than the first preset time.

The feedback unit can be configured to determine whether the restart is allowed according to the running state by the flight control component 40 in response to the restart request signal, and feed back the restart enable signal through the flight control component 40 when the restart is allowed.

The execution unit can be configured to issue a restart execution signal to the power source 10 via the center board assembly 20 in response to the restart enable signal to control the power supply 10 to shut down and restart. And the power supply 10 is turned off and restarted for a second preset time.

The UAV test apparatus of the example embodiment may further include a power detecting module, a power amount determining module, and a second control module, wherein:

The power detection module can be used to detect the amount of power of the power source 10.

The power determining module is configured to determine whether the power of the power source 10 is greater than a preset value.

The second control module can be configured to control the power source 10 to be turned off when the power is not greater than a preset value.

The specific details of each module and unit in the above-described UAV test device have been described in detail in the corresponding UAV test method, and therefore will not be described herein.

Based on the unmanned aerial vehicle test method of the above exemplary embodiment, the unmanned aerial vehicle may be tested, and the unmanned aerial vehicle may be an unmanned aerial vehicle in the exemplary embodiment of the above-described unmanned aerial vehicle test method, and the configuration will not be described in detail herein. The testing process of the unmanned aerial vehicle can be as shown in FIG. 7 . For details, refer to the above exemplary embodiment, and the description is not repeated here.

It should be noted that although several modules or units of equipment for action execution are mentioned in the detailed description above, such division is not mandatory. In fact, according to embodiments of the present invention, the features and functions of two or more modules or units described above may be in one Concreteized in modules or units. Conversely, the features and functions of one of the modules or units described above may be further divided into multiple modules or units.

Furthermore, although the various steps of the method of the invention are described in a particular order in the figures, this does not require or imply that the steps must be performed in that particular order, or that all the steps shown must be performed to achieve the desired. result. Additionally or alternatively, certain steps may be omitted, multiple steps being combined into one step execution, and/or one step being decomposed into multiple step executions and the like.

Through the description of the above embodiments, those skilled in the art will readily understand that the example embodiments described herein may be implemented by software or by software in combination with necessary hardware. Therefore, the technical solution according to the embodiment of the present invention may be embodied in the form of a software product, which may be stored in a non-volatile storage medium (which may be a CD-ROM, a USB flash drive, a mobile hard disk, etc.) or on a network. A number of instructions are included to cause a computing device (which may be a personal computer, server, mobile terminal, or network device, etc.) to perform a method in accordance with an embodiment of the present invention.

Other embodiments of the invention will be apparent to those skilled in the <RTIgt; The present application is intended to cover any variations, uses, or adaptations of the present invention, which are in accordance with the general principles of the present invention and include common general knowledge or conventional technical means in the art that are not disclosed in the present invention. . The specification and examples are to be considered as illustrative only,

Claims

An unmanned aerial vehicle test method for impact testing an unmanned aerial vehicle, the unmanned aerial vehicle comprising a power supply and a center plate assembly, wherein the unmanned aerial vehicle test method comprises:

Activating the power of the unmanned aerial vehicle;

Testing the operating state of the unmanned aerial vehicle;

Detecting an operating time of the UAV by the center panel assembly;

When the center board assembly determines that the running time is not less than the first preset time, the power supply is turned off and restarted by the center board assembly.
The unmanned aerial vehicle test method according to claim 1, wherein the unmanned aerial vehicle further comprises a flight control component, and controlling the power supply to be turned off and restarting comprises:

And sending, by the center board component, a restart request signal when the center board component determines that the running time is not less than the first preset time;

Responding to the restart request signal by the flight control component, determining whether to allow restart according to the operating state, and feeding back a restart enable signal by the flight control component when the restart is allowed;

A restart execution signal is issued to the power source by the center board assembly in response to the restart enable signal to control the power supply to be turned off and restarted.
The unmanned aerial vehicle test method according to claim 1, wherein the power source is turned off and restarted by a second preset time.
The unmanned aerial vehicle testing method according to claim 1, wherein the unmanned aerial vehicle testing method further comprises:

And when the center board component determines that the running time is less than the first preset time, controlling the power to be turned off.
The unmanned aerial vehicle testing method according to claim 1, wherein the unmanned aerial vehicle testing method further comprises:

Detecting the amount of power of the power source;

Determining whether the power of the power source is greater than a preset value;

When the power is not greater than the preset value, the power is turned off.
The unmanned aerial vehicle test method according to any one of claims 1 to 5, characterized in that The test of the operating state of the UAV includes:

It is judged whether the output of the power source is normal.
The unmanned aerial vehicle testing method according to any one of claims 1 to 5, characterized in that the testing of the operating state of the unmanned aerial vehicle comprises:

Determining whether the output of the center plate assembly is normal;

When the output of the center plate assembly is normal, the PTZ component of the UAV is controlled for self-test.
The unmanned aerial vehicle test method according to claim 2, wherein the unmanned aerial vehicle further comprises a power component, and testing the operating state of the unmanned aerial vehicle comprises:

Determining whether the output of the power component is normal;

When the output of the power component is normal, the power component is controlled by the flight control component to output a preset power.
The unmanned aerial vehicle test method according to claim 8, wherein the preset power is half of a rated power of the power component.
An unmanned aerial vehicle testing device for impact testing an unmanned aerial vehicle, the unmanned aerial vehicle comprising a power supply and a center plate assembly, wherein the UAV testing device comprises:

a startup module for starting power of the unmanned aerial vehicle;

a test module for testing an operating state of the unmanned aerial vehicle;

a time detecting module, disposed in the center board assembly, configured to detect an operating time of the UAV through the center board assembly;

The first control module is disposed on the center board assembly, and is configured to control, by the center board assembly, the power to be turned off and restarted when the center board assembly determines that the running time is not less than a first preset time.
The unmanned aerial vehicle test apparatus according to claim 10, wherein the unmanned aerial vehicle further comprises a flight control component, and the first control module comprises:

a requesting unit, configured to send, by the center board component, a restart request signal when the center board component determines that the running time is not less than the first preset time;

a feedback unit, configured to respond to the restart request signal by the flight control component, according to the Determining whether the restart is allowed, and when the restart is allowed, the restart permission signal is fed back through the flight control component;

And an execution unit, configured to send a restart execution signal to the power source by the center board component in response to the restart permission signal to control the power supply to be turned off and restarted.
The UAV test apparatus according to claim 10, wherein the power off and restart intervals are separated by a second predetermined time.
The UAV testing device according to claim 10, wherein the first control module is further configured to: when the center panel component determines that the running time is less than the first preset time, control the The power is off.
The UAV testing device according to claim 10, wherein the UAV testing device further comprises:

a power detecting module, configured to detect a power quantity of the power source;

a power determining module, configured to determine whether the power of the power source is greater than a preset value;

The second control module is configured to control the power to be turned off when the power is not greater than the preset value.
The unmanned aerial vehicle testing device according to any one of claims 10 to 14, wherein the test module comprises:

The power determining unit is configured to determine whether the output of the power source is normal.
The unmanned aerial vehicle testing device according to any one of claims 10 to 14, wherein the test module comprises:

a center board component determining unit, configured to determine whether the output of the center board component is normal;

The pan/tilt assembly control unit is configured to control the gimbal component self-test of the unmanned aerial vehicle when the output of the central plate assembly is normal.
The UAV test apparatus according to claim 11, wherein the UAV further comprises a power component, and the test module comprises:

a power component determining unit, configured to determine whether the output of the power component is normal;

And a power component control unit, configured to control the power component to output a preset power through the flight control component when the output of the power component is normal.
The UAV test apparatus according to claim 17, wherein said preset power is one-half of a rated power of said power pack.