CN210761368U - Unmanned aerial vehicle test platform - Google Patents
Unmanned aerial vehicle test platform Download PDFInfo
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- CN210761368U CN210761368U CN201921459588.1U CN201921459588U CN210761368U CN 210761368 U CN210761368 U CN 210761368U CN 201921459588 U CN201921459588 U CN 201921459588U CN 210761368 U CN210761368 U CN 210761368U
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Abstract
The utility model discloses an unmanned aerial vehicle test platform, wherein, unmanned aerial vehicle driving system includes power device, unmanned aerial vehicle test platform includes platform support, load simulation spare and determine module: the platform bracket is provided with a containing cavity, the platform bracket is provided with a detection port communicated with the containing cavity, and the power device is accommodated in the containing cavity and is arranged opposite to the detection port; the load simulation piece is arranged on the platform bracket, is arranged opposite to the detection port and is used for providing load for the power device; the detection assembly comprises a torque and speed sensor arranged at a detection port, one end of the torque and speed sensor is connected with the load simulation piece through a coupler, the other end of the torque and speed sensor is connected with the power device through the detection port, and the detection assembly is used for detecting power data of the power device. The utility model discloses technical scheme provides the test of type selection verification and stability for unmanned aerial vehicle driving system's electrical property and transmission structure.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, in particular to unmanned aerial vehicle test platform.
Background
With the progress of unmanned aerial vehicle technology and the outbreak of market, the single-rotor unmanned helicopter develops at a high speed. Because it generally only has a set of driving system, therefore the model selection and the stability of single rotor unmanned helicopter driving system become especially important, become the core part in whole unmanned aerial vehicle system. The whole power system generally comprises an energy source, a controller, a motor, a speed reducer and the like, wherein the matching performance of the energy source, the controller and the motor determines the endurance and the power stability of the single-rotor unmanned helicopter. The speed reducer generally performs speed reduction and torque increase by a gear, a belt, or the like, but the design of the speed reducer, heat generation of transmission, consumption of gear oil, wear of the gear and the belt, and the like all determine the transmission efficiency, the operating life, and the like of the speed reducer.
At present, the industry has no professional test platform, and the model selection verification and the stability test of the power can not be provided for the single-rotor unmanned helicopter product in the development stage.
The above is only for the purpose of assisting understanding of the technical solutions of the present application, and does not represent an admission that the above is prior art.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an unmanned aerial vehicle test platform aims at providing the test of lectotype verification and stability for unmanned aerial vehicle driving system's electrical property and transmission structure.
In order to achieve the above object, the utility model provides an unmanned aerial vehicle test platform for test unmanned aerial vehicle driving system, unmanned aerial vehicle driving system includes power device, unmanned aerial vehicle test platform includes:
the platform support is provided with a containing cavity, the platform support is provided with a detection port communicated with the containing cavity, and the power device is accommodated in the containing cavity and is arranged opposite to the detection port;
the load simulation piece is arranged on the platform bracket, is arranged right opposite to the detection port and is used for providing load for the power device;
the detection assembly comprises a torque and speed sensor arranged at the position of the detection port, one end of the torque and speed sensor is connected with the load simulation piece through a coupler, the other end of the torque and speed sensor is connected with the power device through the detection port, and the detection assembly is used for detecting the power data of the power device.
In one embodiment, the unmanned aerial vehicle test platform further comprises a power supply arranged on the platform support, the power supply and the load simulation piece are arranged at intervals, and the power supply is electrically connected with the power device and used for supplying power to the power device;
the detection assembly further comprises an electric power data instrument arranged on the platform support, and the electric power data instrument is electrically connected with the power supply and used for detecting the actual electric input power of the power supply.
In an embodiment, the unmanned aerial vehicle test platform is still including locating the torque speed power appearance of platform support, torque speed power appearance with load simulation piece interval sets up, torque speed sensor with torque speed power appearance electricity is connected, torque speed power appearance is used for reading torque speed sensor's actual mechanical power.
In one embodiment, the detection assembly further comprises a temperature sensor arranged on the power device and used for detecting the real-time temperature of the power device.
In an embodiment, unmanned aerial vehicle test platform is still including locating the temperature display appearance of platform support, the temperature display appearance with load simulation piece interval sets up, the temperature display appearance with the temperature sensor electricity is connected, the temperature display appearance is used for reading temperature sensor's temperature data.
In one embodiment, the load simulator is a brake;
unmanned aerial vehicle test platform is still including locating the load control ware of platform support, load control ware with the stopper interval sets up, just load control ware with the stopper electricity is connected.
In an embodiment, the unmanned aerial vehicle test platform further comprises a cooling water tank arranged on the platform bracket, and the load simulation piece and the cooling water tank are arranged at intervals; the cooling water tank comprises a water tank body and a circulating pipe connected with the water tank body, and at least part of the circulating pipe is arranged around the periphery of the load simulation part.
In one embodiment, the platform support comprises:
the first bracket is provided with the containing cavity and the detection port; and
the second support is arranged on the first support and is opposite to the detection port, the second support is provided with an installation cavity communicated with the detection port, and the load simulation piece is arranged in the installation cavity;
the power system further comprises a power rack arranged in the containing cavity, the power device is arranged in the power rack, the power device is provided with an output shaft penetrating through the power rack, and the output shaft penetrates through the detection port to be connected with the torque and rotation speed sensor.
In an embodiment, the unmanned aerial vehicle test platform further comprises an installation support arranged in the cavity, the installation support comprises two installation pipes and a plurality of connecting pieces connected to the installation pipes in a sliding mode, two ends of each installation pipe are connected to the wall of the cavity in a sliding mode, installation spaces are formed in the installation pipes at intervals, the power rack is located in the installation spaces, and one end, far away from the installation pipes, of each connecting piece is detachably connected with the power rack.
In an embodiment, the cavity is provided with two slide rails respectively opposite to the two cavity walls, two ends of each mounting tube are provided with a slide block respectively, and each mounting tube is connected with the cavity wall of the cavity in a sliding manner through the sliding fit of the slide blocks and the slide rails.
According to the technical scheme of the utility model, the detection assembly and the load simulation piece are arranged on the platform support, when the power device of the unmanned aerial vehicle power system is arranged in the containing cavity of the platform support, the power device is just arranged on the detection port, the load simulation piece is also just arranged on the detection port, the power device is connected with one end of the torque and speed sensor of the detection assembly, and the end of the torque and speed sensor, which is back to the power device, is connected with the load simulation piece; when the unmanned aerial vehicle test platform needs to be detected, the power device is electrified to drive the torque and speed sensor to rotate, the load simulation piece connected with the torque and speed sensor correspondingly rotates, the load simulation piece gives certain resistance to the torque and speed sensor while rotating to simulate the real load scene of the power device, the power device can detect the actual mechanical power of the power device running with load through the torque and speed sensor, and therefore the unmanned aerial vehicle test platform can provide type selection verification and stability test for the electrical performance and transmission of the unmanned aerial vehicle power system.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
Fig. 1 is a schematic structural view of a viewing angle of an embodiment of the unmanned aerial vehicle test platform of the present invention;
fig. 2 is the utility model discloses the structural schematic diagram at another visual angle of unmanned aerial vehicle test platform embodiment.
The reference numbers illustrate:
| reference numerals | Name (R) | Reference numerals | Name (R) | |
| 1 | |
50 | |
|
| 2 | Power frame | 60 | |
|
| 10 | |
70 | |
|
| 10a | Containing chamber | 11 | |
|
| | Detection port | 12 | |
|
| 20 | Load simulator/ |
| Mounting cavity | |
| 30 | |
80 | |
|
| 31 | Torque and |
81 | |
|
| 32 | Electric |
82 | Connecting |
|
| 40 | Torque, rotating speed and power meter |
The objects, features and advantages of the present invention will be further described with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
It should be noted that all the directional indicators (such as upper, lower, left, right, front and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the motion situation, etc. in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit ly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions in the embodiments may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
The utility model provides an unmanned aerial vehicle test platform.
In the embodiment of the utility model, referring to fig. 1 and 2, man-machine test platform is used for testing unmanned aerial vehicle driving system, unmanned aerial vehicle driving system includes power device 1, unmanned aerial vehicle test platform includes platform support 10, load simulation piece 20 and determine module 30. The platform support 10 is provided with a cavity 10a, the platform support 10 is provided with a detection port 10b communicated with the cavity 10a, and the power device 1 is accommodated in the cavity 10a and is arranged opposite to the detection port 10 b; the load simulation part 20 is arranged on the platform support 10, is arranged opposite to the detection port 10b, and is used for providing a load for the power device 1; the detection assembly 30 comprises a torque and rotation speed sensor 31 arranged at the detection port 10b, one end of the torque and rotation speed sensor 31 is connected with the load simulator 20 through a coupler, and the other end of the torque and rotation speed sensor 31 is connected with the power device 1 through the detection port 10 b; the detection component 30 is used for detecting the power data of the power device 1.
In the present embodiment, the power system includes a power device 1, and the power device 1 specifically includes a speed reducer, a transmission belt, and a driving motor, and the speed reducer is in transmission connection with an output shaft of the driving motor through the transmission belt.
When a test is started, the power device 1 is arranged in the cavity 10a, and an output shaft of the power device 1 penetrates through the detection port 10b to be connected with a torque and rotation speed sensor 31 arranged at the detection port 10 b; subsequently, the power device 1 is powered on, the output shaft of the power device 1 drives the torque and rotation speed sensor 31 to rotate, the torque and rotation speed sensor 31 drives the load simulation piece 20 to rotate, at the moment, the load simulation piece 20 can endow certain resistance and gravity to the torque and rotation speed sensor 31 while rotating, namely, the load simulation piece 20 is utilized to simulate the real load condition of the power device, the power device 1 is enabled to run in a load mode, further, the actual mechanical power of the power device 1 running in a load mode can be detected through the torque and rotation speed sensor 31, and therefore the unmanned aerial vehicle testing platform can provide type selection verification and stability testing for the electrical performance and the transmission structure of the unmanned aerial vehicle power system.
According to the technical scheme of the utility model, the detection assembly 30 and the load simulation piece 20 are arranged on the platform support 10, when the power device 1 of the unmanned aerial vehicle power system is arranged in the containing cavity 10a of the platform support 10, the power device 1 is just arranged at the detection port 10b, the load simulation piece 20 is also just arranged at the detection port 10b, the power device 1 is connected with one end of the torque and rotation speed sensor 31 of the detection assembly 30, and one end of the torque and rotation speed sensor 31, which is opposite to the power device 1, is connected with the load simulation piece 20; so set up, when needs detect, power device 1 circular telegram drives torque speed sensor 31 and rotates, and the load simulation piece 20 that is connected with torque speed sensor 31 also corresponding rotation, certain resistance and gravity to torque speed sensor 31 are given in load simulation piece 20 when the pivoted, with the true load scene of simulation power device 1, make power device 1 accessible torque speed sensor 31 detect the actual mechanical power who obtains power device 1 of on-load operation, thereby unmanned aerial vehicle test platform just can realize providing life-span and the test of dynamic stability for unmanned aerial vehicle's driving system.
Optionally, referring to fig. 1 and fig. 2, the test platform of the unmanned aerial vehicle further includes a power supply disposed on the platform support 10, the power supply is disposed at an interval with the load simulator 20, and the power supply is electrically connected to the power device 1 and is configured to supply power to the power device 1; the detection assembly 30 further comprises an electric power data meter 32 disposed on the platform support 10, wherein the electric power data meter 32 is electrically connected to the power supply for detecting the actual electric input power of the power supply.
In this embodiment, a power source is disposed outside the cavity 10a of the platform support 10, and the power source is electrically connected to the power device 1 to provide electric energy for the power device 1 during testing. And an electric power data instrument 32 is arranged between the platform support 10 and the power supply, and the electric power data instrument 32 is electrically connected with the power supply to detect data such as voltage and current of the power supply for supplying power to the power device 1, calculate actual electric input power of the power device 1 and supply data for calculating working power of the power device 1.
Further, referring to fig. 1 and fig. 2, in an embodiment, the unmanned aerial vehicle testing platform further includes a torque and rotation speed power meter 40 disposed on the platform support 10, the torque and rotation speed power meter 40 is disposed at an interval with the load simulator 20, the torque and rotation speed sensor 31 is electrically connected to the torque and rotation speed power meter 40, and the torque and rotation speed power meter 40 is configured to read an actual mechanical power of the torque and rotation speed sensor 31.
In the embodiment, two voltage signals of the torque and rotation speed sensor 31 are input to the torque and rotation speed power meter 40, and the voltage signals are amplified, shaped, phase-detected, converted into counting pulses through the torque and rotation speed power meter 40, and then counted and displayed, so that the measurement results of the torque and the rotation speed can be directly read out. Because the torque and rotating speed measuring method based on magnetoelectric conversion, phase difference principle and digital display is adopted, stable, reliable, quick and sensitive high-precision measurement can be carried out. That is, the actual load power of the torque rotation speed sensor 31 is read and displayed by the torque rotation speed power meter 40, so that the user can directly view and record the actual load power detected by the torque rotation speed sensor 31. The torque rotating speed power instrument 40 and the electric power data instrument 32 are sequentially connected in a stacked manner, one side, opposite to the torque rotating speed power instrument 40, of the electric power data instrument 32 is arranged on the first support 11 and is located outside the accommodating cavity 10a, namely the temperature display instrument 50, the load controller 60, the torque rotating speed power instrument 40 and the electric power data instrument 32 are sequentially connected to the outer top wall of the first support 11 in a stacked manner, and meanwhile the temperature display instrument 50, the load controller 60, the torque rotating speed power instrument 40 and the electric power data instrument 32 are arranged at intervals with the load simulator 20.
Further, referring to fig. 1 and 2, in an embodiment, the detecting assembly 30 further includes a temperature sensor disposed on the power device 1, and configured to detect a real-time temperature of the power frame 1.
In this embodiment, temperature sensor can paste the optional position at power device 1, and temperature sensor is through contacting with power device 1, and then obtains power device 1 and carry the real-time temperature of process in area, provides the reference for the long-time load operation condition that the user aassessment power device 1, and then promotes unmanned aerial vehicle test platform's detection precision.
Further, referring to fig. 1 and 2, in an embodiment, the unmanned aerial vehicle test platform further includes a temperature display instrument 50 disposed on the platform support 10, the temperature display instrument 50 is disposed at an interval with the load simulator 20, the temperature display instrument 50 is electrically connected to the temperature sensor, and the temperature display instrument 50 is configured to read temperature data of the temperature sensor. In this embodiment, the temperature display instrument 50 is electrically connected to the temperature sensor, so as to read and display the temperature data of the temperature sensor, thereby facilitating the user to check and record the temperature of the temperature sensor. The temperature display instrument 50, the load controller 60, the torque and speed power instrument 40 and the electric power data instrument 32 are sequentially stacked and connected on the outer top wall of the first bracket 11, and meanwhile, the temperature display instrument 50, the load controller 60, the torque and speed power instrument 40 and the electric power data instrument 32 are arranged at intervals with the load simulator 20.
Further, referring to fig. 1 and 2, in one embodiment, the load simulator 20 is a brake;
unmanned aerial vehicle test platform is still including locating platform support 10's load controller 60, load controller 60 with stopper 20 interval sets up, load controller 60 with stopper 20 electricity is connected.
In the present embodiment, the load controller 60 is specifically disposed between the torque, rotation speed and power meter 40 and the temperature display instrument 50 of the platform support 10, and is located outside the cavity 10 a.
The optimum matching can only be guaranteed under the design conditions due to the functional relationship between the rotational speed and the pitch. Therefore, it is difficult to ensure an optimum match when the operating state of the power unit 1 changes, such as when the load increases or because the pitch increases, it is possible to overload the power unit 1. Without the use of the load controller 60, it would be necessary for the host operator to constantly monitor the power plant 1 load. Therefore, in order to avoid overloading the power device 1 and reduce the labor intensity of the operator, the load controller 60 is electrically connected with the load simulator 20, so that the test stability of the unmanned aerial vehicle test platform is improved. The temperature display instrument 50, the load controller 60, the torque and speed power instrument 40 and the electric power data instrument 32 are sequentially stacked and connected on the outer top wall of the first bracket 11, and meanwhile, the temperature display instrument 50, the load controller 60, the torque and speed power instrument 40 and the electric power data instrument 32 are arranged at intervals with the load simulator 20.
Further, referring to fig. 1 and fig. 2, in an embodiment, the test platform of the unmanned aerial vehicle further includes a cooling water tank 70 disposed on the platform support 10, and the load simulator 20 is disposed at an interval from the cooling water tank 70; the cooling water tank 70 includes a tank body and a circulation pipe (not shown) connected to the tank body, and at least a portion of the circulation pipe is disposed around the periphery of the load simulator 20.
In this embodiment, when the load simulation piece 20 is driven by the torque and rotation speed sensor 31 to rotate at a high speed, the load simulation piece 20 easily gathers heat in the life test process of the unmanned aerial vehicle power system, in order to avoid the heat to influence the normal rotation of the load simulation piece 20, therefore, the cooling water tank 70 is arranged, the circulating pipe utilizing the cooling water tank 70 is arranged around the periphery of the load simulation piece 20, so, when refrigerant in the water tank body circulates in the circulating pipe, the circulating pipe with lower temperature can exchange heat with the load simulation piece 20 with higher temperature, thereby reducing the temperature of the load simulation piece 20, and further improving the stability of the unmanned aerial vehicle test platform. Specifically, a cooling water tank installation cavity communicated with the accommodating cavity 10a is further formed in the first support 11 and located on one side of the accommodating cavity 10a, which is opposite to the detection port 10b, and the cooling water tank 70 is installed in the cooling water tank installation cavity.
In an embodiment, referring to fig. 1 and 2, the platform support 10 includes a first support 11 and a second support 12 disposed on the first support 11, and the first support 11 is provided with the cavity 10a and the detection port 10 b; the second support 12 is arranged opposite to the detection port 10b, the second support 12 is provided with an installation cavity 12a communicated with the detection port 10b, and the load simulation piece 20 is arranged in the installation cavity 12 a; the power system further comprises a power frame 2 arranged in the accommodating cavity 10a, the power device 1 is arranged in the power frame 2, the power device 1 is provided with an output shaft penetrating through the power frame 2, and the output shaft penetrates through the detection port 10b to be connected with the torque and rotation speed sensor 31.
In the present embodiment, the first bracket 11 and the second bracket 12 may be formed by welding through the provision of profile pipes, and in other embodiments may be formed by assembling plates. In this embodiment, the first support 11 and the second support 12 are rectangular frames, the first support 11 and the second support 12 are arranged from top to bottom, the first support 11 is provided with a containing cavity 10a, the second support 12 is provided with an installation cavity 12a, the detection port 10b is arranged between the containing cavity 10a and the installation cavity 12a, that is, the containing cavity 10a is communicated with the installation cavity 12a through the detection port 10 b.
Specifically, a first mounting seat is arranged on the wall of the mounting cavity 12a, the periphery of the load simulator 20 is fixed on the first mounting seat, an output shaft of the load simulator 20 is connected with a torque and rotation speed sensor 31 located at the detection port 10b through a coupler, a second mounting seat is arranged on the wall of the detection port 10b, and the periphery of the torque and rotation speed sensor 31 is fixed on the second mounting seat; the power frame 2 is arranged on the cavity wall of the containing cavity 10a, and the output shaft of the power device 1 penetrates out of the power frame 2 and is connected with one end of the torque and rotation speed sensor 31, which is opposite to the load simulator 20, through the detection port 10 b. The second support 12 is arranged on the top wall of the first support 11, the volume of the second support 12 is smaller than that of the first support 11, the temperature display instrument 50, the load controller 60, the torque rotating speed power instrument 40 and the electric power data instrument 32 are sequentially connected in a stacking mode, one side, back to the torque rotating speed power instrument 40, of the electric power data instrument 32 is arranged on the first support 11 and located outside the accommodating cavity 10a, namely the temperature display instrument 50, the load controller 60, the torque rotating speed power instrument 40 and the electric power data instrument 32 are sequentially connected on the outer top wall of the first support 11 in a stacking mode, and meanwhile the temperature display instrument 50, the load controller 60, the torque rotating speed power instrument 40 and the electric power data instrument 32 are arranged at intervals with the load simulation piece 20.
Further, referring to fig. 1 and 2, in an embodiment, the unmanned aerial vehicle test platform further includes an installation support 80 disposed in the accommodating cavity 10a, where the installation support 80 includes two installation pipes 81 and a plurality of connecting members 82 slidably connected to each of the installation pipes 81, two ends of each of the installation pipes 81 are slidably connected to a cavity wall of the accommodating cavity 10a, the two installation pipes 81 are disposed at an interval and form an installation space, the power frame 2 is located in the installation space, and one end of each of the connecting members 82, which is far away from the installation pipe 81, is detachably connected to the power frame 1.
In this embodiment, sliding connection is on the chamber wall that holds chamber 10a respectively through the both ends of two installation pipes 81, make the interval of two installation pipes 81 can adjust according to the size of the unmanned aerial vehicle driving system's that needs test at present power frame 2, and the interval of a plurality of connecting pieces 82 of each installation pipe 81 of rethread adjustment, make the connecting piece of each installation pipe 81 can be connected with the both sides of power frame 2 uniformly, and the connecting piece is connected with power frame 2 dismantlement, be convenient for power frame 2's dismouting, thereby realize improving unmanned aerial vehicle test platform's test range.
Further, referring to fig. 1 and fig. 2, in an embodiment, the accommodating cavity 10a is provided with a slide rail (not shown) respectively opposite to two cavity walls, two ends of each of the mounting tubes 81 are provided with a slide block respectively, and each of the mounting tubes 81 is slidably connected to the cavity wall of the accommodating cavity 10a through sliding fit between the slide block and the slide rail. This is provided to enable adjustment of the spacing between the two mounting tubes 81.
The above only is the preferred embodiment of the present invention, not limiting the scope of the present invention, all the equivalent structure changes made by the contents of the specification and the drawings under the inventive concept of the present invention, or the direct/indirect application in other related technical fields are included in the patent protection scope of the present invention.
Claims (10)
1. The utility model provides an unmanned aerial vehicle test platform for test unmanned aerial vehicle driving system, unmanned aerial vehicle driving system includes power device, its characterized in that, unmanned aerial vehicle test platform includes:
the platform support is provided with a containing cavity, the platform support is provided with a detection port communicated with the containing cavity, and the power device is accommodated in the containing cavity and is arranged opposite to the detection port;
the load simulation piece is arranged on the platform bracket, is arranged right opposite to the detection port and is used for providing load for the power device;
the detection assembly comprises a torque and speed sensor arranged at the position of the detection port, one end of the torque and speed sensor is connected with the load simulation piece through a coupler, the other end of the torque and speed sensor is connected with the power device through the detection port, and the detection assembly is used for detecting the power data of the power device.
2. The unmanned aerial vehicle test platform of claim 1, further comprising a power source disposed on the platform support, the power source being spaced apart from the load simulator and electrically connected to the power device for powering the power device;
the detection assembly further comprises an electric power data instrument arranged on the platform support, and the electric power data instrument is electrically connected with the power supply and used for detecting the actual electric input power of the power supply.
3. The unmanned aerial vehicle test platform of claim 1, further comprising a torque and speed dynamometer disposed on the platform support, the torque and speed dynamometer being spaced apart from the load simulator, the torque and speed sensor being electrically connected to the torque and speed dynamometer, the torque and speed dynamometer being configured to read an actual mechanical power of the torque and speed sensor.
4. An unmanned aerial vehicle test platform as claimed in claim 1, wherein the detection assembly further comprises a temperature sensor provided to the power plant for detecting a real-time temperature of the power plant.
5. The unmanned aerial vehicle test platform of claim 4, further comprising a temperature display instrument disposed on the platform support, the temperature display instrument being spaced apart from the load simulator, the temperature display instrument being electrically connected to the temperature sensor, the temperature display instrument being configured to read temperature data of the temperature sensor.
6. An unmanned aerial vehicle test platform as claimed in any one of claims 1 to 5, wherein the load simulator is a brake;
unmanned aerial vehicle test platform is still including locating the load control ware of platform support, load control ware with the stopper interval sets up, just load control ware with the stopper electricity is connected.
7. An unmanned aerial vehicle test platform as claimed in any one of claims 1 to 5, wherein the unmanned aerial vehicle test platform further comprises a cooling water tank provided to the platform support, the load simulator being spaced from the cooling water tank; the cooling water tank comprises a water tank body and a circulating pipe connected with the water tank body, and at least part of the circulating pipe is arranged around the periphery of the load simulation part.
8. A drone testing platform according to any one of claims 3 to 5, wherein the platform support includes:
the first bracket is provided with the containing cavity and the detection port; and
the second support is arranged on the first support and is opposite to the detection port, the second support is provided with an installation cavity communicated with the detection port, and the load simulation piece is arranged in the installation cavity;
the power system further comprises a power rack arranged in the containing cavity, the power device is arranged in the power rack, the power device is provided with an output shaft penetrating through the power rack, and the output shaft penetrates through the detection port to be connected with the torque and rotation speed sensor.
9. The unmanned aerial vehicle test platform of claim 8, further comprising a mounting bracket disposed in the cavity, wherein the mounting bracket includes two mounting tubes and a plurality of connecting members slidably connected to each of the mounting tubes, two ends of each of the mounting tubes are slidably connected to the cavity wall of the cavity, the two mounting tubes are spaced apart from each other and form a mounting space, the power frame is located in the mounting space, and one end of each of the connecting members, which is far away from the mounting tubes, is detachably connected to the power frame.
10. An unmanned aerial vehicle test platform as claimed in claim 9, wherein the chamber has a slide rail for each of two opposite chamber walls, each of the two ends of the mounting tube has a slide block, and each of the mounting tubes is slidably connected to the chamber wall of the chamber by a sliding fit between the slide block and the slide rail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921459588.1U CN210761368U (en) | 2019-09-03 | 2019-09-03 | Unmanned aerial vehicle test platform |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921459588.1U CN210761368U (en) | 2019-09-03 | 2019-09-03 | Unmanned aerial vehicle test platform |
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| CN210761368U true CN210761368U (en) | 2020-06-16 |
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| CN201921459588.1U Active CN210761368U (en) | 2019-09-03 | 2019-09-03 | Unmanned aerial vehicle test platform |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
-
2019
- 2019-09-03 CN CN201921459588.1U patent/CN210761368U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
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