CN213168607U - Special test platform of unmanned aerial vehicle - Google Patents
Special test platform of unmanned aerial vehicle Download PDFInfo
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- CN213168607U CN213168607U CN202022110931.0U CN202022110931U CN213168607U CN 213168607 U CN213168607 U CN 213168607U CN 202022110931 U CN202022110931 U CN 202022110931U CN 213168607 U CN213168607 U CN 213168607U
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Abstract
The utility model discloses a special test platform for unmanned aerial vehicle in the technical field of unmanned aerial vehicle test equipment, the upper surface of the base is fixedly connected with a motor base and a guard plate respectively, the upper surface of the base is provided with a shock pad, the shock pad is positioned inside the guard plate, the upper surface of the motor base is fixedly connected with a rotating motor, the surface of the output shaft of the rotating motor is fixedly connected with a crank, one end of the crank, which is far away from the output shaft of the rotating motor, is provided with a rocker, in the utility model, the basic wind direction and angle of the fan can be adjusted by arranging the rotating motor and the rocker, the specific wind direction angle and wind speed can be adjusted by arranging the fan adjusting motor, the wind speed probe and the fan, and the problem that the wind tunnel is difficult to flexibly adjust the single or combined wind direction for the unmanned aerial vehicle with smaller volume, such as, therefore, the problem of the actual working condition faced by the unmanned aerial vehicle is difficult to simulate.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle test equipment technical field specifically is a special test platform of unmanned aerial vehicle.
Background
Along with the continuous attack of unmanned aerial vehicle bottleneck technique, the unmanned aerial vehicle field demonstrates the development of explosive type in recent years, and unmanned aerial vehicle is easily received the disturbance of atmospheric motion at the flight in-process, and the existence of wind field will greatly influence its flight orbit precision and flight gesture, so the important index of anti-wind ability as the unmanned aerial vehicle performance receives user and tester's extensive attention.
At present, the wind-resistant performance test of unmanned aerial vehicle usually needs to go on through wind-tunnel simulation wind field in the laboratory, however the wind-tunnel is difficult to the nimble single or combination wind direction of adjustment of the unmanned aerial vehicle that the volume is less, like the combination of vertical wind and 45 degrees oblique upper side winds, therefore is difficult to simulate the operating condition that unmanned aerial vehicle faced. Therefore, the technical personnel in the field provide a special test platform for unmanned aerial vehicles to solve the problems in the background technology.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a special test platform of unmanned aerial vehicle to solve the problem that proposes in the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
a special test platform for an unmanned aerial vehicle comprises a base, wherein a motor base and a protective plate are fixedly connected to the upper surface of the base respectively, a shock pad is arranged on the upper surface of the base and located inside the protective plate, a rotating motor is fixedly connected to the upper surface of the motor base, a crank is fixedly connected to the surface of an output shaft of the rotating motor, a rocker is arranged at one end, away from the output shaft of the rotating motor, of the crank, the number of the cranks is four, the four cranks are in a circumferential array and are arranged on the surface of the output shaft of the rotating motor in a circumferential equidistant mode, a fan adjusting motor is fixedly connected to one end, away from the crank, of the rocker, fan fixing plates are fixedly connected to the output shaft of the fan adjusting motor, the number of the fan fixing plates is four, fans are fixedly connected to opposite faces of the fan fixing plates, and a rotating, and the other side of the base is fixedly connected with a fan adjusting controller.
As a further aspect of the present invention: the fan fixing plate is fixedly connected with the fan through the screw, and the fan is stable in structure when the angle is adjusted through the fan fixing plate and the fan which are fixedly connected through the screw.
As a further aspect of the present invention: the fan adjusting controller is electrically connected with the fan adjusting motor, the motor controller is electrically connected with the rotating motor, and the basic wind direction and the angle of the fan can be adjusted by setting the rotating motor controller to be electrically connected with the rotating motor.
As a further aspect of the present invention: the wind speed probe is fixedly connected to the inner top wall of the protection plate and the upper surface of the base, and the wind speed of the fan can be captured by the aid of the wind speed probe.
As a further aspect of the present invention: a plurality of air holes are formed in the surface of the protection plate and correspond to the fan, the fan is located inside the protection plate, and ventilation can be provided for the fan through the air holes.
As a further aspect of the present invention: the material of shock pad is rubber, and the material through setting up the shock pad is rubber, damages when can avoiding unmanned aerial vehicle to fall.
As a further aspect of the present invention: the surface silk of rocker connects has the internal thread, the rocker passes through internal thread fixed connection with the crank, can be according to unmanned aerial vehicle's the distance between the size adjustment fan opposite face through setting up the internal thread.
Compared with the prior art, the beneficial effects of the utility model are that:
1. the utility model discloses in, can adjust the basic wind direction and the angle of fan through setting up rotation motor and rocker, can adjust specific wind direction angle and wind speed through setting up fan adjusting motor, wind speed probe and fan, can solve through the setting that the wind-tunnel is difficult to adjust single or combination wind direction to the unmanned aerial vehicle flexibility that the volume is less, like the combination of vertical wind and 45 degrees upwind to one side, therefore be difficult to simulate the problem of the operating condition that unmanned aerial vehicle faced.
2. In the utility model, the fan can be more stable when adjusting the angle by arranging the fan fixing plate and fixedly connecting the fan with the screw; the basic wind direction and the angle of the fan can be adjusted by arranging the rotating motor controller to be electrically connected with the rotating motor; by arranging the wind speed probe, the wind speed of the fan can be captured.
3. In the utility model, the ventilation can be provided for the fan by arranging the air holes; the damping pad is made of rubber, so that the unmanned aerial vehicle can be prevented from being damaged when falling; can be according to the distance between unmanned aerial vehicle's the big or small adjustment fan opposite face through setting up the internal thread.
Drawings
Fig. 1 is a schematic isometric view of the present invention;
FIG. 2 is a schematic front view of the present invention;
FIG. 3 is a schematic side view of the present invention;
FIG. 4 is a schematic view of the internal structure of the guard plate of the present invention;
fig. 5 is an enlarged schematic view of a structure in fig. 4 according to the present invention.
In the figure: 1. a base; 2. a motor base; 3. a guard plate; 4. a shock pad; 5. rotating the motor; 6. a crank; 7. a rocker; 8. a fan adjustment motor; 9. a fan fixing plate; 10. a fan; 11. rotating the motor controller; 12. a fan adjustment controller; 13. a wind speed probe; 14. air holes are formed; 15. and (4) internal thread.
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 work belong to the protection scope of the present invention.
Referring to fig. 1 to 5, in the embodiment of the present invention, the fan assembly comprises a base 1, wherein a motor base 2 and a guard plate 3 are respectively fixedly connected to the upper surface of the base 1, a shock pad 4 is disposed on the upper surface of the base 1, the shock pad 4 is disposed inside the guard plate 3, a rotating motor 5 is fixedly connected to the upper surface of the motor base 2, a crank 6 is fixedly connected to the surface of an output shaft of the rotating motor 5, a rocker 7 is disposed at one end of the crank 6 away from the output shaft of the rotating motor 5, the number of the cranks 6 is four, the four cranks 6 are arranged in a circumferential array and are circumferentially equidistantly disposed on the surface of the output shaft of the rotating motor 5, a fan adjusting motor 8 is fixedly connected to one end of the rocker 7 away from the crank 6, a fan fixing plate 9 is fixedly connected to the output shaft of the fan adjusting motor 8, one side fixedly connected with of base 1 rotates machine controller 11, base 1's opposite side fixedly connected with fan adjustment controller 12, rotate motor 5 and rocker 7 through the setting and can adjust fan 10's basic wind direction and angle, can adjust specific wind direction angle through setting up fan adjustment motor 8 and fan 10, can solve the wind-tunnel through the aforesaid and be difficult to adjust single or combination wind direction in a flexible way to the less unmanned aerial vehicle of volume, like the combination of vertical wind and 45 degrees oblique upward crosswinds, therefore be difficult to simulate the problem of the operating condition that unmanned aerial vehicle faced.
The fan fixing plate 9 is fixedly connected with the fan 10 through a screw, and the fan 10 can be structurally stable when the angle is adjusted by fixedly connecting the fan fixing plate 9 with the fan 10 through the screw; the fan adjusting controller 12 is electrically connected with the fan adjusting motor 8, the rotating motor controller 11 is electrically connected with the rotating motor 5, and the basic wind direction and the angle of the fan 10 can be adjusted by arranging the rotating motor controller 11 to be electrically connected with the rotating motor 5; the wind speed probe 13 is fixedly connected to the inner top wall of the guard plate 3 and the upper surface of the base 1, and the wind speed of the air supplied by the fan 10 can be captured by the aid of the wind speed probe 13.
A plurality of air holes 14 are formed in the surface of the guard plate 3 corresponding to the fan 10, the fan 10 is located inside the guard plate 3, and ventilation can be provided for the fan 10 through the air holes 14; the damping pad 4 is made of rubber, and the damping pad 4 is made of rubber, so that the unmanned aerial vehicle can be prevented from being damaged when falling; the surperficial silk of rocker 7 connects has internal thread 15, and rocker 7 and crank 6 are through internal thread 15 fixed connection, can be according to the distance between unmanned aerial vehicle's the big or small adjustment fan 10 opposite face through setting up internal thread 15.
The utility model discloses a theory of operation is: the utility model discloses, the user opens rotating machine controller 11 at first when using, make rotating machine controller 11 and rotating motor 5 electricity be connected, control and adjust the angle of rocker 7 through rotating machine controller 11, open fan adjustment controller 12 again, can make fan adjustment controller 12 and fan adjustment motor 8 electricity be connected, control and adjust the basic wind direction and the angle of fan 10 through fan adjustment controller 12, start fan 10 at this moment, make fan 10 begin work, can know the wind speed that fan 10 sent in fan adjustment controller 12 through wind speed probe 13 simultaneously, according to the wind speed numerical value and utilize fan adjustment motor 8 to carry out the wind speed adjustment, after reaching ideal state, the user remote control unmanned aerial vehicle enters the test area and carries out unmanned aerial vehicle's anti-wind performance test, can solve the wind tunnel and be difficult to adjust single or make up the wind direction to the unmanned aerial vehicle flexibility that the volume is less through above-mentioned setting and use, such as the combination of vertical wind and 45 degrees oblique upwind, thus it is difficult to simulate the problem of the real operating condition that unmanned aerial vehicle faced.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (7)
1. The utility model provides a special test platform of unmanned aerial vehicle, includes base (1), its characterized in that: the upper surface of the base (1) is fixedly connected with a motor base (2) and a guard plate (3) respectively, the upper surface of the base (1) is provided with a shock pad (4), the shock pad (4) is positioned inside the guard plate (3), the upper surface of the motor base (2) is fixedly connected with a rotating motor (5), the surface of an output shaft of the rotating motor (5) is fixedly connected with a crank (6), one end, away from the output shaft of the rotating motor (5), of the crank (6) is provided with a rocker (7), the number of the cranks (6) is four, the four cranks (6) are in a circumferential array and are arranged on the surface of the output shaft of the rotating motor (5) in a circumferential equidistance mode, one end, away from the crank (6), of the rocker (7) is fixedly connected with a fan adjusting motor (8), and the output shaft of the fan adjusting motor (8) is fixedly connected with, the fan fixing plate (9) is four in number, four opposite face fixedly connected with fan (10) of fan fixing plate (9), one side fixedly connected with of base (1) rotates machine controller (11), the opposite side fixedly connected with fan adjustment controller (12) of base (1).
2. The test platform special for unmanned aerial vehicles of claim 1, wherein: the fan fixing plate (9) is fixedly connected with the fan (10) through a screw.
3. The test platform special for unmanned aerial vehicles of claim 1, wherein: the fan adjusting controller (12) is electrically connected with the fan adjusting motor (8), and the rotating motor controller (11) is electrically connected with the rotating motor (5).
4. The test platform special for unmanned aerial vehicles of claim 1, wherein: the wind speed probe (13) is fixedly connected to the inner top wall of the guard plate (3) and the upper surface of the base (1).
5. The test platform special for unmanned aerial vehicles of claim 1, wherein: a plurality of air holes (14) are formed in the surface of the protection plate (3) and correspond to the fan (10), and the fan (10) is located inside the protection plate (3).
6. The test platform special for unmanned aerial vehicles of claim 1, wherein: the shock pad (4) is made of rubber.
7. The test platform special for unmanned aerial vehicles of claim 1, wherein: the surface of the rocker (7) is connected with an inner wire (15), and the rocker (7) is fixedly connected with the crank (6) through the inner wire (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022110931.0U CN213168607U (en) | 2020-09-23 | 2020-09-23 | Special test platform of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022110931.0U CN213168607U (en) | 2020-09-23 | 2020-09-23 | Special test platform of unmanned aerial vehicle |
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| CN213168607U true CN213168607U (en) | 2021-05-11 |
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| CN202022110931.0U Active CN213168607U (en) | 2020-09-23 | 2020-09-23 | Special test platform of unmanned aerial vehicle |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113335558A (en) * | 2021-05-28 | 2021-09-03 | 合肥飞豪通信科技有限公司 | Remote measurement type small unmanned aerial vehicle wind pressure test system |
| CN114486149A (en) * | 2022-01-19 | 2022-05-13 | 山东交通学院 | Wind field simulation generation device and method based on unmanned aerial vehicle test |
| CN115959303A (en) * | 2023-03-16 | 2023-04-14 | 四川省天域航通科技有限公司 | Intelligent flight test method and application of large-scale fixed-wing freight unmanned aerial vehicle |
-
2020
- 2020-09-23 CN CN202022110931.0U patent/CN213168607U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113335558A (en) * | 2021-05-28 | 2021-09-03 | 合肥飞豪通信科技有限公司 | Remote measurement type small unmanned aerial vehicle wind pressure test system |
| CN113335558B (en) * | 2021-05-28 | 2024-03-19 | 西安宇翼星智能科技有限公司 | Remote-measuring type small unmanned aerial vehicle wind pressure test system |
| CN114486149A (en) * | 2022-01-19 | 2022-05-13 | 山东交通学院 | Wind field simulation generation device and method based on unmanned aerial vehicle test |
| CN114486149B (en) * | 2022-01-19 | 2023-11-24 | 山东交通学院 | Wind field simulation generation device and method based on unmanned aerial vehicle test |
| CN115959303A (en) * | 2023-03-16 | 2023-04-14 | 四川省天域航通科技有限公司 | Intelligent flight test method and application of large-scale fixed-wing freight unmanned aerial vehicle |
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