CN106768565B - Testing arrangement of small-size unmanned vehicles motor - Google Patents
Testing arrangement of small-size unmanned vehicles motor Download PDFInfo
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- CN106768565B CN106768565B CN201710135598.9A CN201710135598A CN106768565B CN 106768565 B CN106768565 B CN 106768565B CN 201710135598 A CN201710135598 A CN 201710135598A CN 106768565 B CN106768565 B CN 106768565B
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- 238000012360 testing method Methods 0.000 title claims abstract description 73
- 238000002474 experimental method Methods 0.000 claims description 7
- 238000009864 tensile test Methods 0.000 claims description 6
- 238000001514 detection method Methods 0.000 claims description 5
- 239000004809 Teflon Substances 0.000 claims description 2
- 229920006362 Teflon® Polymers 0.000 claims description 2
- 238000012545 processing Methods 0.000 abstract description 5
- 238000013461 design Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- -1 polytetrafluoroethylene Polymers 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0061—Force sensors associated with industrial machines or actuators
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L3/00—Measuring torque, work, mechanical power, or mechanical efficiency, in general
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
- G01P3/36—Devices characterised by the use of optical means, e.g. using infrared, visible, or ultraviolet light
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/34—Testing dynamo-electric machines
- G01R31/343—Testing dynamo-electric machines in operation
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Analytical Chemistry (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a testing device of a small-sized unmanned aerial vehicle motor, which comprises a tension testing structure, a torque testing structure and a computer, wherein the tension testing structure, the torque testing structure and the computer are arranged on a laboratory bench; the measured data such as the tension, the torque and the like can be transmitted to the computer in real time, and data processing is facilitated.
Description
Technical Field
The invention relates to the field of structural design and test of a power testing device, in particular to a testing device for tension, current, rotating speed and torque of a motor of a small unmanned aerial vehicle.
Background
The small unmanned aerial vehicle has the advantages of being small in size, good in flight performance, capable of replacing people to execute dangerous tasks and the like, and is developed rapidly. The power system of the small unmanned aerial vehicle is mainly a brushless motor, the small unmanned aerial vehicle with single generator, double generator and multiple generators is very common, particularly the small unmanned aerial vehicle with multiple rotors has very high requirements on the rotating speed and the torque of the motor, but the motor products on the market are various at present, the quality of the motors produced by various manufacturers is different, and the detailed data of the motor obtained by testing is very necessary for the small unmanned aerial vehicle with relatively accurate performance requirements on the tension, the current, the rotating speed, the torque and the like of the motor. The data such as pulling force, the rotational speed of the nominal or rated state of this motor can be given in motor manufacturer's the description, but because different unmanned aerial vehicle's motor is different because of factors such as operational environment and mounted position, the user should test the actual data of motor by oneself to guarantee to satisfy actual demand.
Most of testing devices for motor tension, current, rotating speed and torque in the market are single and cannot effectively measure the attribute of a motor in detail, so that a device capable of rapidly and uniformly testing multiple parameters of different types of motors is urgently needed, certain precision requirements and safety indexes are met by the device, and the device is convenient and fast to use.
Disclosure of Invention
In view of this, the embodiment of the present invention provides a testing apparatus capable of measuring at least two working parameters of a motor of a small aircraft conveniently and quickly.
The technical scheme provided by the embodiment of the invention is as follows:
a testing device for a motor of a small unmanned aerial vehicle comprises a tension testing structure, a torque testing structure and a computer, wherein the tension testing structure, the torque testing structure and the computer are arranged on a laboratory bench;
the tensile test structure comprises a motor base, a rocker arm, a flange bearing assembly, a balance table and a plurality of first sensors which are fixedly connected from top to bottom in sequence; the flange bearing assembly comprises a cylinder fixed on the balance table and a flange bearing sleeved outside the cylinder; the motor base, the rocker arm and the flange bearing are fixedly connected, and a wire inlet hole is formed in the edge of the rocker arm; the first sensors are uniformly distributed at the bottom of the balance table;
the torque testing structure comprises a bracket and a pulley arranged on the bracket; one end of a stay wire is connected with a wire inlet hole on the rocker arm, and the other end of the stay wire is connected with a heavy object after passing around the pulley; the weight is arranged on the second sensor, wherein the center line of the pulley and the center of the wire inlet hole have the same height;
and the computer is electrically connected with the plurality of first sensors and the plurality of second sensors and displays the tension and the torque of the motor to be detected, which are obtained according to the detection results of the first sensors and the second sensors.
Optionally, the test apparatus for a motor of a small unmanned aerial vehicle further includes:
and the tachometer is used for measuring the rotating speed of the motor to be tested after rotating and is arranged on the balance table, and the distance between the tachometer and the central axis of the balance table is smaller than the rotating diameter of a propeller connected with the motor to be tested.
Optionally, in the testing apparatus for a small-sized unmanned aerial vehicle motor, the tachometer is a digital infrared tachometer.
Optionally, the test apparatus for a motor of a small unmanned aerial vehicle further includes:
and the ammeter is clamped between two power lines of the motor to be measured and is used for measuring the working current of the rotated motor to be measured.
Optionally, in the test apparatus for a motor of a small unmanned aerial vehicle described above, the ammeter is a clamp ammeter.
Optionally, the test apparatus for a motor of a small unmanned aerial vehicle further includes:
and the electronic speed regulator is arranged on the experiment table, is electrically connected with the motor to be measured and regulates the rotating speed of the motor to be measured.
Optionally, in the testing apparatus for a motor of a small unmanned aerial vehicle, the tensile testing structure further includes:
and the gasket is arranged between the flange bearing and the balance table.
Optionally, in the test apparatus for a small unmanned aerial vehicle motor, the gasket is a teflon gasket.
Optionally, in the testing apparatus for a motor of a small unmanned aerial vehicle, in the tensile test structure, four first sensors are symmetrically arranged at the bottom of the balancing stand.
Optionally, in the test apparatus for a motor of a small unmanned aerial vehicle described above, the first sensor and the second sensor are fixedly connected to the bottom of the balancing stand by bolts.
The testing device for the motor of the small unmanned aerial vehicle provided by the embodiment of the invention comprises a tension testing structure, a torque testing structure and a computer which are arranged on a laboratory bench, and at least can conveniently and quickly measure the tension and the torque of the motor at the same time; the measured data such as pulling force, moment of torsion can be transmitted to the computer in real time, be convenient for carry out data processing.
Drawings
The objects and advantages of embodiments of the present invention will be understood and appreciated by reference to the following detailed description of embodiments of the invention, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic structural diagram of a testing device for a motor of a small unmanned aerial vehicle according to an embodiment of the invention;
FIG. 2 is a schematic structural diagram of another view of the testing device for the motor of the small-sized unmanned aerial vehicle shown in FIG. 1;
FIG. 3 is a front view of a test apparatus for a small unmanned aerial vehicle motor;
fig. 4 is an exploded view of the tensile test structure.
Wherein the reference numerals are:
01-propeller, 02-motor to be tested, 03-motor base, 04-rocker arm, 05-flange bearing, 06-tachometer, 07-balance table, 08-first sensor, 09-stay wire, 10-pulley, 11-pulley fixing part, 12-bracket, 13-weight, 14-second sensor, 15-experiment table, 16-cylinder, 17-gasket, 18-ammeter and 19-electronic speed regulator.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it is to be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Example 1
The embodiment provides a testing device for a motor of a small unmanned aerial vehicle, which comprises a tension testing structure, a torque testing structure and a computer, wherein the tension testing structure, the torque testing structure and the computer are arranged on a laboratory bench 15, as shown in fig. 1, 2 and 3. The tensile force testing structure comprises a motor base 03, a rocker arm 04, a flange bearing assembly, a balance table 07 and a plurality of first sensors 08 which are fixedly connected from top to bottom in sequence; the flange bearing assembly comprises a cylinder 16 fixed on the balance table 07 and a flange bearing 05 sleeved outside the cylinder; the motor base 03 and the rocker arm 04 are fixedly connected with the flange bearing 05, and a wire inlet hole is formed in the edge of the rocker arm 04; the plurality of first sensors 08 are uniformly distributed at the bottom of the balance table 07. The torque testing structure comprises a bracket 12 and a pulley 10 arranged on the bracket 12; one end of a pull wire 09 is connected with a wire inlet hole on the rocker arm 04, and the other end of the pull wire is connected with a heavy object 13 after passing around the pulley 10; the weight 13 is disposed on the second sensor 14. The computer is electrically connected with the plurality of first sensors 08 and the plurality of second sensors 14, and displays the tension and the torque of the motor 02 to be measured, which are obtained according to the detection results of the first sensors 08 and the second sensors 14.
The laboratory table 15 may be a proprietary laboratory table in a laboratory, or may be a ground table directly, or the above structure may be fixedly installed on the ground.
As shown in fig. 4, when the motor 02 to be tested needs to be tested, the propeller 01 and the motor 02 to be tested are fastened, and the propeller 01 can be screwed on the motor 02 to be tested by using a matched nut gasket. The motor 02 to be tested is fixedly connected to the motor base 03, the area of the bottom of the motor can be increased through the motor base 03, and the motor can be fixed conveniently. The motor base 03 and the rocker arm 04 are fastened and connected with the outside of the linear flange bearing 05 through bolts, and the rocker arm 04 cannot independently displace. The linear flange bearing 05 is sleeved outside the cylinder 16 with a proper inner diameter, and the structures are matched to ensure that the rotation resistance of the rocker arm 04 is small. The column 16 is firmly connected with the balance platform 07, and the connection between the limiting column 16 and the balance platform 07 is firm, for example, the connecting parts can be welded together and can not be loosened. The contact area between the balance table 07 and the experiment table 15 is large enough, and the weight is also large as much as possible, so that the integral measuring device is prevented from being unstable and even turning over when the motor 02 to be measured rotates at a high speed; polytetrafluoroethylene gasket 17 can be added between linear flange bearing 05 and balance table 07 to minimize the frictional force between linear flange bearing 05 bottom surface and the balance table 07, and balance table 07 bottom surface and a plurality of first sensor 08 adopt bolted connection, and first sensor 08 can adopt pulling force/pressure sensor, and first sensor 08 will distribute evenly and prevent that the balance table from verting, and first sensor is together fixed with laboratory bench 15. Preferably, the number of the first sensors 08 is an even number, for example, four as shown in the figure, and four first sensors 08 are preferably symmetrically placed at four corners of the bottom of the balance block 07 to prevent the balance block 07 from tilting.
The pulley 10 is completely assembled, the pulley 10 is arranged on the bracket 12 through the pulley fixing part 11, the bracket 12 is fixed at a proper position of the experiment table 15, the pulley 10 is adjusted to a proper height and fixed, the center line of the pulley 10 corresponds to the center of the wire inlet hole on the rocker arm 04, and the height of the center line is consistent, so that the friction between the pulley 10 and the pull wire 09 when the pulley 10 slides is reduced. The pull wire 09 is wound around the pulley 10, one end of the pull wire is tied to the weight 13, the other end of the pull wire passes through the wire inlet hole of the rocker arm 04 and is tied to the rocker arm 04, then the weight 13 is placed on the second sensor 14, the second sensor 14 can also adopt a pressure/tension sensor, and the second sensor and the experiment table 15 can also adopt connecting pieces such as bolts and the like for fixed connection. The relationship between the rocker arm 04, the pulley 10 and the weight 13 is adjusted to make the stay 09 in a tightened state to wait for measurement.
It will be appreciated that in order to ensure that the test apparatus described above is operating properly, it must also be connected to a power supply for supplying power to the devices in the test apparatus. When the test device is assembled, the components requiring electrical power are connected to a power source via wires. After the motor 02 to be tested is fixed on the testing device according to the connection relation, the wiring terminals of the first sensor 08 and the second sensor 14 are connected, the wire of the motor 02 to be tested is connected to a proper electronic speed regulator 19, the computer is connected, a power supply is switched on, the motor 02 to be tested is controlled to rotate, the motor 02 to be tested can drive the rocker arm 04 to rotate when rotating, the rocker arm 04 drives the pull wire 09 to rotate around the pulley 10, and therefore pulling force is applied to the weight 13, the pulling force is torque when the motor to be tested rotates, and the torque can be directly measured through the second sensor 14. In addition, when the motor 02 to be measured rotates, the propeller 01 rotates to generate a pulling force, and the pulling force can be applied to the first sensor 08 after passing through the flange bearing 05 and the balance platform 07, so that the pulling force generated after the motor to be measured rotates can be directly measured through the first sensor 08.
According to the principle, the computer receives the detection results of the first sensor 08 and the second sensor 14, and after the detection results of the first sensor 08 and the second sensor 14 are in a stable state, the values of the tension and the torque measured when the motor 02 to be measured is matched with the propeller 01 can be obtained.
By adopting the testing device for the motor of the small unmanned aerial vehicle, the tensile force and the torque of the motor can be conveniently and rapidly measured simultaneously, and the testing device is simple in overall structural design, low in cost, high-efficiency and practical; the measured data such as pulling force, moment of torsion can be transmitted to the computer in real time, be convenient for carry out data processing.
Example 2
The testing device for the motor of the small unmanned aerial vehicle provided by the embodiment further comprises a tachometer 06 for measuring the rotating speed of the motor 02 to be tested after rotation, wherein the tachometer 06 is arranged on the balance block 07, and the distance between the tachometer 06 and the central axis of the balance block 07 is smaller than the rotating diameter of the propeller 01 connected with the motor 02 to be tested. Specifically, the tachometer 06 is a digital infrared tachometer. When the motor 02 to be tested rotates, the propeller 01 is driven to rotate, and the digital infrared tachometer is arranged in the rotating radius of the propeller 01, so that the rotating speed of the propeller 01 can be directly detected, namely the rotating speed of the motor 02 to be tested.
Further, the testing device further comprises an ammeter 18 which is clamped between two power lines of the motor 02 to be tested and measures the working current of the motor 02 to be tested after rotation. The ammeter 18 can be a clamp ammeter, after the power line of the motor 02 to be measured is connected, the power line is clamped between two power lines by the clamp ammeter, and when the motor 02 to be measured rotates to be stable in current, the reading is the current of the motor in stable operation.
The testing device for the motor of the small unmanned aerial vehicle provided by the embodiment of the invention comprises the tension testing structure, the torque testing structure and the computer which are arranged on the experiment table, at least the tension and the torque of the motor can be conveniently and rapidly measured simultaneously, and the testing device is simple in overall structural design, low in cost, high-efficiency and practical; the measured data such as the tension, the torque and the like can be transmitted to the computer in real time, and data processing is facilitated.
By adopting the testing device for the motor of the small unmanned aerial vehicle, provided by the embodiment, the tension, the torque, the rotating speed and the current of the motor can be conveniently and rapidly measured simultaneously, and the testing device is simple in overall structural design, low in cost, high-efficiency and practical; the measured data such as tension, torque, rotating speed, current and the like can be transmitted to a computer in real time, so that data processing is facilitated, and curves such as tension-rotating speed, rotating speed-torque and the like can be conveniently obtained for testers to use.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A testing device for a motor of a small unmanned aerial vehicle is characterized by comprising a tension testing structure, a torque testing structure and a computer, wherein the tension testing structure, the torque testing structure and the computer are arranged on a laboratory table;
the tensile test structure comprises a motor base, a rocker arm, a flange bearing assembly, a balance table and a plurality of first sensors which are fixedly connected from top to bottom in sequence; the flange bearing assembly comprises a cylinder fixed on the balance table and a flange bearing sleeved outside the cylinder; the motor base and the rocker arm are fixedly connected with the flange bearing, and a wire inlet hole is formed in the edge of the rocker arm; the first sensors are uniformly distributed at the bottom of the balance table;
the torque testing structure comprises a bracket and a pulley arranged on the bracket; one end of a stay wire is connected with a wire inlet hole on the rocker arm, and the other end of the stay wire is connected with a heavy object after passing around the pulley; the weight is arranged on the second sensor, wherein the center line of the pulley and the center of the wire inlet hole have the same height;
the computer is electrically connected with the first sensors and the second sensors and displays the tension and the torque of the motor to be detected according to the detection results of the first sensors and the second sensors;
the propeller is fixedly connected with a motor to be tested;
the motor to be tested is fixedly connected to the motor base.
2. The small unmanned aerial vehicle motor test apparatus as claimed in claim 1, further comprising:
and the tachometer is used for measuring the rotating speed of the motor to be tested after rotating and is arranged on the balance table, and the distance between the tachometer and the central axis of the balance table is smaller than the rotating diameter of a propeller connected with the motor to be tested.
3. The small-sized unmanned aerial vehicle motor test device according to claim 2, wherein: the revolution meter is a digital infrared revolution meter.
4. The small unmanned aerial vehicle motor test apparatus as claimed in claim 1, further comprising: and the ammeter is clamped between two power lines of the motor to be measured and is used for measuring the working current of the rotated motor to be measured.
5. The small unmanned aerial vehicle motor test device of claim 4, wherein: the ammeter is a clamp ammeter.
6. The small-sized unmanned aerial vehicle motor test device according to any one of claims 1 to 5, further comprising:
and the electronic speed regulator is arranged on the experiment table, is electrically connected with the motor to be measured and regulates the rotating speed of the motor to be measured.
7. The device for testing the motor of the small unmanned aerial vehicle as claimed in claim 6, wherein the tensile testing structure further comprises:
and the gasket is arranged between the flange bearing and the balance table.
8. The device for testing the motor of a small unmanned aerial vehicle as claimed in claim 7, wherein the gasket is a teflon gasket.
9. The device for testing the motor of the small unmanned aerial vehicle as claimed in claim 8, wherein the number of the first sensors in the tension test structure is four, and the four first sensors are symmetrically arranged at the bottom of the balancing stand.
10. The device for testing the motor of the small unmanned aerial vehicle as claimed in claim 9, wherein the first sensor is fixedly connected to the bottom of the balancing stand by a bolt.
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| CN202836835U (en) * | 2012-09-28 | 2013-03-27 | 佛山市安尔康姆航拍科技有限公司 | Unmanned aerial vehicle lift force and torsion force test device |
| CN103604608A (en) * | 2013-11-27 | 2014-02-26 | 沈阳航空航天大学 | Propeller tensile test bench for light sport aircraft |
| CN205971888U (en) * | 2016-07-07 | 2017-02-22 | 顺丰科技有限公司 | Aircraft driving system testing arrangement |
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