CN210126647U - Unmanned aerial vehicle power performance testing arrangement - Google Patents
Unmanned aerial vehicle power performance testing arrangement Download PDFInfo
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- CN210126647U CN210126647U CN201920945581.4U CN201920945581U CN210126647U CN 210126647 U CN210126647 U CN 210126647U CN 201920945581 U CN201920945581 U CN 201920945581U CN 210126647 U CN210126647 U CN 210126647U
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Abstract
The utility model discloses an unmanned aerial vehicle dynamic behavior testing arrangement belongs to unmanned aerial vehicle test equipment technical field. The unmanned aerial vehicle power performance testing device is used for testing the power performance of a motor-propeller power set and comprises 1 base frame and 3 same pressure detection modules; the base frame is provided with a horizontally placed motor base used for installing a motor to be tested; the motor base is transversely connected with 3 force arms with the same included angle and the same length; the tail end of each force arm is respectively and fixedly connected with a supporting leg which faces vertically downwards; the base frame is placed on the pressure detection module through the supporting legs; the motor-propeller power set is arranged on the base frame and generates downward acting force after being started, and the acting force is detected by the pressure detection module.
Description
Technical Field
The utility model discloses an unmanned aerial vehicle dynamic behavior testing arrangement belongs to unmanned aerial vehicle test equipment technical field.
Background
Along with the technology is continuously mature, the electric unmanned aerial vehicle can be widely applied. The motor-propeller form a power system of the electric unmanned aerial vehicle, a power set formed by matching the motor-propeller forms a basic component of the unmanned aerial vehicle, and the performance of the power set directly influences the flight safety and the flight efficiency of the unmanned aerial vehicle.
At present, due to the lack of a convenient dynamic performance testing device, model selection and matching of a motor and a propeller often depend on experience of developers, quantitative measurement of a power system through a test platform is lacked, and feasibility of a model selection scheme is lacked of theoretical and experimental data support.
The existing unmanned aerial vehicle power performance testing device has multiple technical defects, and the wide application of the unmanned aerial vehicle power performance testing is limited, so that the practical performance of the unmanned aerial vehicle is improved.
In the prior art, a patent CN205919960U discloses an unmanned aerial vehicle power test system, and a patent CN203629733U discloses an electric unmanned aerial vehicle power test device, both of which adopt a horizontal configuration, and the power test has a vertical torsion to cause a measurement error; patent CN107664747A discloses a single-paddle motor power experimental device and a test method, which adopt vertical arrangement to reduce interference caused by gravity, but the multiple schemes all need to be fixed by a base, occupy space greatly and cannot be flexibly used anytime and anywhere; meanwhile, the safety protection of several devices needs to be enhanced. In addition, including the above scheme, the existing unmanned aerial vehicle power performance testing device mostly adopts a single load cell to measure the power strength, which may have large measurement errors, and even the load cell fails and is hard to perceive.
Therefore, in order to solve the above technical problems, a power performance testing device capable of accurately testing a motor-propeller power unit is needed, so as to facilitate selection and matching of the motor-propeller, better perform power analysis and research, and improve the flight efficiency of the electric unmanned aerial vehicle.
Disclosure of Invention
In order to overcome above technical problem, the utility model discloses an unmanned aerial vehicle dynamic property testing arrangement for the dynamic property of test motor-screw power group, the technical scheme who adopts is:
an unmanned aerial vehicle power performance testing device comprises 1 base frame and 3 same pressure detection modules; the base frame is provided with a horizontally placed motor base used for installing a motor to be tested; the motor base is transversely connected with 3 force arms with the same included angle and the same length; the tail end of each force arm is respectively and fixedly connected with a supporting leg which faces vertically downwards; the base frame is placed on the pressure detection module through the supporting legs; the motor-propeller power set is arranged on the base frame and generates downward acting force after being started, and the acting force is detected by the pressure detection module.
Furthermore, the force arm comprises an inner rod fixed on the motor base and a sleeve matched with the inner rod in size so as to form a telescopic structure; the sleeve is provided with a positioning bayonet at a fixed distance, and the inner rod is provided with a positioning bayonet which is matched with the positioning bayonet, so that the force arm can be extended or shortened according to a fixed size.
Furthermore, the lower part of the supporting foot is in an inverted cone shape.
Further, the pressure detection module include the base, the base is equipped with pressure sensor, pressure sensor's top is equipped with the atress part, the upper surface of atress part is concave structure and concave bottom is the arc surface.
Further, the base of the pressure detection module is in a circular truncated cone shape, and a rubber pad is adhered to the lower side of the base; the bottom of the rubber pad is provided with anti-skid lines.
The test method using the unmanned aerial vehicle power performance test device comprises the following steps:
installing a motor-propeller power set on a base frame of the device, and resetting the value of the pressure detection module before starting a motor; the motor-propeller power pack generates a downward force upon starting the motor, which is detected by the pressure detection module and calculated as: and calculating the average value of the data obtained by the 3 pressure detection modules, comparing the difference value of the data obtained by each pressure detection module with the average value, and if the difference value is not more than 6% of the average value, determining that the data is valid, wherein the acting force of the motor-propeller power set is the sum of the data measured by the 3 pressure detection modules.
Further, the method is used for detecting the acting force direction of the motor-propeller power set and self-checking the device, and comprises the following steps:
calculating the average value of the data obtained by the 3 pressure detection modules, comparing the difference value of the data obtained by each pressure detection module with the average value, if the difference value exceeds 6 percent of the average value, lifting the base frame after stopping the motor, rotating the base frame clockwise or anticlockwise by one foot position and continuing testing; observing that the data obtained by the pressure detection module changes along with the rotation of the base frame or follows the pressure detection module without generating rotation change, wherein if the obtained data changes along with the rotation of the base frame, the acting force generated by the motor-propeller power set does not move along the vertical direction; if the pressure detection module is followed without generating rotation change, the pressure detection module corresponding to the data with larger difference value is in failure.
The utility model discloses following beneficial effect has:
(1) the device does not need to be fixed, occupies small space, is convenient to carry and can be used for an external field;
(2) the device is simple to operate, and high precision is guaranteed by using a plurality of sensors;
(3) the self-checking function can be realized, and the device fault which is not easy to detect is avoided;
(4) in addition to measuring total thrust, the power balance of the motor-propeller power pack can also be detected;
(5) the propeller is enclosed in the base frame and acts downwards, so that the safety performance is good.
Drawings
Fig. 1 is a schematic structural diagram of the device for testing the power performance of the unmanned aerial vehicle of the present invention;
fig. 2 is a schematic structural diagram of the pressure detection module according to the present invention.
Detailed Description
The present invention will be further explained with reference to the accompanying drawings:
as shown in fig. 1, the unmanned aerial vehicle dynamic performance testing device comprises 1 pedestal and 3 identical pressure detection modules (6); the base frame is provided with a motor base (1) which is horizontally placed and used for installing a motor (5) to be tested, and the motor (5) to be tested is provided with a propeller (4) to form a power unit.
The motor base (1) is transversely connected with 3 force arms (2) with the same included angle and the same length; the force arm (2) comprises an inner rod fixed on the motor base (1) and a sleeve matched with the inner rod to form a telescopic structure; the sleeve is provided with a positioning bayonet at a fixed distance, and the inner rod is provided with a positioning bayonet projection matched with the positioning bayonet, so that the force arm can be extended or shortened according to a fixed size; the section of the force arm (2) can be circular, and relative rotation cannot be found due to the arrangement of the bayonet.
The tail end of each force arm (2) is respectively and fixedly connected with a supporting leg (3) which vertically faces downwards, the lower part of each supporting leg (3) is in an inverted cone shape, and the base frame is placed on the pressure detection module (6) through the supporting legs (3).
As shown in the attached figure 2, the pressure detection module (6) comprises a truncated cone-shaped base (6-a), a pressure sensor (6-c) is arranged in the base (6-a), a stress component (6-b) is arranged above the pressure sensor (6-c), the upper surface of the stress component (6-b) is of a concave structure, and the concave bottom is a circular arc surface; a rubber pad (6-d) is adhered to the lower side of the base (6-a), and anti-skid grains are arranged at the bottom of the rubber pad (6-d).
The unmanned aerial vehicle power performance testing device is mainly used for testing the power performance of a motor-propeller power set, and the testing method comprises the following steps:
and (3) installing a motor-propeller power set on the base frame, and resetting the numerical value of the pressure detection module (6) before starting the motor.
When the motor is started, the base frame should be lightly supported or the speed should be slowly increased, so that the torsion overturning device generated when the power set is vigorously started is avoided. When the rotating speed is stable, the base frame sinks into a concave structure of the stress component (6-b) of the pressure sensor (6-c) and cannot fall off; and because the pressure detection module (6) is acted downwards, the friction with the ground is extremely large, and the deviation of the device cannot occur.
After the motor is started, the power set generates downward acting force, and the acting force is detected by the pressure detection module (6). The force generated by the power pack is calculated as: and calculating the average value of the data obtained by the 3 pressure detection modules, and comparing the difference value between the data obtained by each pressure detection module and the average value, wherein if the difference value is not more than 6 percent of the average value, the data is considered to be effective, and the acting force of the power group is the sum of the data measured by the 3 pressure detection modules.
The device can also be used for detecting the acting force direction of the motor-propeller power set and self-checking the device, and the method comprises the following steps:
calculating the average value of the data obtained by the 3 pressure detection modules, comparing the difference value of the data obtained by each pressure detection module with the average value, if the difference value exceeds 6 percent of the average value, lifting the base frame after stopping the motor, rotating the base frame clockwise or anticlockwise by one foot position and continuing testing; the data obtained by observing the pressure detection module is changed along with the rotation of the base frame, or is changed along with the pressure detection module without rotation.
If the obtained data changes along with the rotation of the base frame, the acting force generated by the motor-propeller power set is not along the vertical direction; if the pressure detection module is followed without rotation change, the pressure detection module corresponding to the data with larger difference value is in failure.
The above description is only for the specific embodiments of the present invention, and the examples do not limit the essential contents of the present invention, and those skilled in the art will modify or modify the foregoing specific embodiments without departing from the essential spirit of the present invention.
Claims (5)
1. An unmanned aerial vehicle power performance testing device is used for testing the power performance of a motor-propeller power set and is characterized by comprising 1 base frame and 3 same pressure detection modules;
the base frame is provided with a horizontally placed motor base used for installing a motor to be tested; the motor base is transversely connected with 3 force arms with the same included angle and the same length; the tail end of each force arm is respectively and fixedly connected with a supporting leg which faces vertically downwards;
the base frame is placed on the pressure detection module through the supporting legs;
the motor-propeller power set is arranged on the base frame and generates downward acting force after being started, and the acting force is detected by the pressure detection module.
2. The unmanned aerial vehicle dynamic performance testing device of claim 1, wherein the force arm comprises an inner rod fixed to the motor base and a sleeve matched with the inner rod in size to form a telescopic structure; the sleeve is provided with a positioning bayonet at a fixed distance, and the inner rod is provided with a positioning bayonet which is matched with the positioning bayonet, so that the force arm can be extended or shortened according to a fixed size.
3. The testing device for the dynamic performance of the unmanned aerial vehicle as claimed in claim 1, wherein the lower portion of the supporting foot is in an inverted cone shape.
4. The unmanned aerial vehicle dynamic behavior testing arrangement of claim 3, characterized in that, the pressure detection module include the base, the base is equipped with pressure sensor, pressure sensor's top is equipped with the atress part, the upper surface of atress part is concave structure and concave bottom is the arc surface.
5. The unmanned aerial vehicle dynamic performance testing device of claim 4, wherein the base of the pressure detection module is truncated cone-shaped, and a rubber pad is adhered to the lower side of the base; the bottom of the rubber pad is provided with anti-skid lines.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110127084A (en) * | 2019-06-22 | 2019-08-16 | 广西翼界科技有限公司 | A kind of unmanned plane power performance detector and test method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110127084A (en) * | 2019-06-22 | 2019-08-16 | 广西翼界科技有限公司 | A kind of unmanned plane power performance detector and test method |
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Denomination of utility model: A power performance test device for UAV Effective date of registration: 20220107 Granted publication date: 20200306 Pledgee: Guilin Bank Co.,Ltd. Beihai Branch Pledgor: GUANGXI YIJIE TECHNOLOGY CO.,LTD. Registration number: Y2022450000005 |