CN106768565A - A kind of test device of small-sized unmanned aircraft motor - Google Patents

Abstract

The invention provides a test device for a small unmanned aerial vehicle motor, which includes a tension test structure, a torque test structure and a computer placed on a test bench. The test device can at least measure the motor pull and torque conveniently and quickly at the same time, and the overall structure The design is simple, the cost is low, efficient and practical; the measurement data such as tension and torque can be transmitted to the computer in real time, which is convenient for data processing.

Description

A test device for a small unmanned aerial vehicle motor

technical field

The invention relates to the field of structural design and testing of a power testing device, in particular to a testing device for a small unmanned aerial vehicle motor pulling force, current, rotational speed and torque.

Background technique

Due to its small size, good flight performance, and the ability to perform dangerous tasks instead of humans, small unmanned aerial vehicles are developing rapidly. The power system of small unmanned aerial vehicles is mainly brushless motors. Single-engine, double-engine and multi-generator small unmanned aerial vehicles are very common, especially multi-rotor aircraft, which have very high requirements for motor speed and torque, but currently on the market There are many types of motor products, and the quality of the motors produced by each manufacturer is different. For small unmanned aerial vehicles with more precise performance requirements such as motor pull, current, speed and torque, it is very necessary to test and obtain detailed data of the motor. The motor manufacturer’s manual will give the motor’s nominal or rated state pulling force, speed and other data, but because the motors of different drones are different due to factors such as working environment and installation location, users should test the actual data of the motor by themselves. To ensure that actual needs are met.

At present, most of the test devices for motor pull, current, speed and torque on the market are single-test, and cannot measure the properties of the motor in detail and effectively. Therefore, there is an urgent need for a device that can quickly and uniformly test multiple parameters of different types of motors. device, and the device must meet certain accuracy requirements and safety indicators, and it must be convenient and quick to use.

Contents of the invention

In view of this, an embodiment of the present invention provides a test device that can conveniently and quickly measure at least two working parameters of a small aircraft motor at the same time.

The technical scheme that the embodiment of the present invention provides is as follows:

A test device for a small unmanned aerial vehicle motor, including a tension test structure, a torque test structure and a computer placed on the test bench;

The tensile test structure includes a motor base, a rocker arm, a flange bearing assembly, a balance platform and a plurality of first sensors fixedly connected in sequence from top to bottom; wherein, the flange bearing assembly includes The cylinder on the top and the flange bearing sleeved on the outside of the cylinder; the motor seat, the rocker arm and the flange bearing are fixedly connected, and the edge of the rocker arm is formed with a wire hole; a plurality of the The first sensors are evenly distributed on the bottom of the balance platform;

The torque testing structure includes a bracket and a pulley arranged on the bracket; one end of the pull wire is connected to the wire inlet hole on the rocker arm, and the other end is connected to the weight after bypassing the pulley; the weight is set on the second sensor, wherein the centerline of the pulley has the same height as the center of the inlet hole;

The computer is electrically connected to a plurality of the first sensors and the second sensors, and displays the pulling force and torque of the motor to be tested obtained according to the detection results of the first sensors and the second sensors.

Optionally, in the test device of the above-mentioned small unmanned aerial vehicle motor, also include:

The tachometer measures the rotating speed of the motor to be tested, and is arranged on the balance platform, and the distance between it and the central axis of the balance platform is smaller than the rotation diameter of the propeller connected to the motor to be tested.

Optionally, in the above-mentioned small unmanned aerial vehicle motor testing device, the tachometer is a digital infrared tachometer.

Optionally, in the test device of the above-mentioned small unmanned aerial vehicle motor, also include:

The ammeter is clamped between the two power lines of the motor to be tested, and measures the working current of the motor to be tested after it rotates.

Optionally, in the above-mentioned small unmanned aerial vehicle motor testing device, the ammeter is a clamp-on ammeter.

Optionally, in the test device of the above-mentioned small unmanned aerial vehicle motor, also include:

The electronic governor is placed on the test bench, electrically connected with the motor to be tested, and adjusts the speed of the motor to be tested.

Optionally, in the test device of the above-mentioned small unmanned aerial vehicle motor, the tensile test structure also includes:

The gasket is arranged between the flange bearing and the balance platform.

Optionally, in the above-mentioned small unmanned aerial vehicle motor testing device, the gasket is a polytetrafluoroethylene gasket.

Optionally, in the above test device for small unmanned aerial vehicle motors, in the tensile test structure, there are four first sensors, which are symmetrically arranged at the bottom of the balance platform.

Optionally, in the above-mentioned small UAV motor testing device, the first sensor and the second sensor are fixedly connected to the bottom of the balance platform by bolts.

The test device for the small unmanned aerial vehicle motor provided by the embodiment of the present invention includes a tension test structure, a torque test structure and a computer placed on the test bench, which can at least measure the motor tension and torque conveniently and quickly at the same time, and the overall structure design is simple. , low cost, efficient and practical; measurement data such as tension and torque can be transmitted to the computer in real time, which is convenient for data processing.

Description of drawings

The following will describe the embodiment of the present invention in detail through the accompanying drawings, which will help to understand the purpose and advantages of the embodiment of the present invention, wherein:

Fig. 1 is the structural representation of the testing device of small unmanned aerial vehicle motor described in the embodiment of the present invention;

Fig. 2 is the structure schematic diagram of another angle of view of the testing device of small unmanned aerial vehicle motor shown in Fig. 1;

Fig. 3 is the front view of the testing device of small unmanned aerial vehicle motor;

Fig. 4 is an exploded schematic view of the tensile test structure.

The reference signs therein are:

01-propeller, 02-motor to be tested, 03-motor seat, 04-rocker arm, 05-flange bearing, 06-speed counter, 07-balance table, 08-first sensor, 09-guy wire, 10-pulley, 11-pulley fixture, 12-support, 13-weight, 14-second sensor, 15-test bench, 16-column, 17-pad, 18-ammeter, 19-electronic governor.

detailed description

The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to 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. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, or in a specific orientation. construction and operation, therefore, should not be construed as limiting the invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and should not be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that unless otherwise specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. Connected, or integrally connected; it can be mechanically connected or electrically connected; it can be directly connected or indirectly connected through an intermediary, and it can be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.

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 there is no conflict with each other.

Example 1

The present embodiment provides a test device for a small unmanned aerial vehicle motor, as shown in Fig. 1 , Fig. 2 and Fig. 3 , including a tension test structure, a torque test structure and a computer placed on the test bench 15. The tensile test structure includes a motor base 03, a rocker arm 04, a flange bearing assembly, a balance table 07 and a plurality of first sensors 08 fixedly connected in sequence from top to bottom; wherein, the flange bearing assembly includes a The cylinder 16 on the balance platform 07 and the flange bearing 05 sleeved on the outside of the cylinder; the motor base 03, the rocker arm 04 are fixedly connected to the flange bearing 05, and the edge of the rocker arm 04 A cable inlet hole is formed at the position; a plurality of the first sensors 08 are evenly distributed on the bottom of the balance platform 07 . The torque testing structure includes a bracket 12 and a pulley 10 arranged on the bracket 12; one end of the pull wire 09 is connected to the wire inlet hole on the rocker arm 04, and the other end bypasses the pulley 10 and connects with the weight 13 Connection; the weight 13 is set on the second sensor 14 . The computer is electrically connected to a plurality of the first sensors 08 and the second sensors 14, and displays the pulling force and torque of the motor 02 to be tested according to the detection results of the first sensors 08 and the second sensors 14 .

It should be noted that the test bench 15 can be a dedicated test bench in the laboratory, or directly use the ground as the test bench, and the above-mentioned structure can also be fixed on the ground.

As shown in FIG. 4 , when the motor 02 to be tested needs to be tested, the propeller 01 is tightly connected to the motor 02 to be tested, and the propeller 01 can be tightened on the motor 02 to be tested with matching nuts and washers. The motor 02 to be tested is fixedly connected to the motor base 03, and the area at the bottom of the motor can be increased through the motor base 03, which is convenient for fixing. The motor base 03 and the rocking arm 04 are fastened to the outside of the linear flange bearing 05 by bolts, so that the rocking arm 04 cannot be independently displaced. The linear flange bearing 05 is sleeved outside the cylinder 16 with an appropriate internal diameter, and the cooperation of the above-mentioned structure is very small in order to ensure the rotation resistance of the rocker arm 04. The cylinder 16 is tightly connected with the balance platform 07, and the connection between the limit cylinder 16 and the balance platform 07 should be firm, for example, it can be welded together without loosening. The contact area between the balance platform 07 and the test platform 15 is large enough, and the weight should be as large as possible to prevent the overall measurement device from being unstable or even rollover when the motor 02 to be tested rotates at high speed; the linear flange bearing 05 and the balance platform 07 can be Increase the polytetrafluoroethylene gasket 17 to minimize the friction between the bottom surface of the linear flange bearing 05 and the balance platform 07. The bottom surface of the balance platform 07 is connected with multiple first sensors 08 by bolts, and the first sensor 08 can use tension /Pressure sensors, the first sensors 08 should be evenly distributed to prevent the balance platform from tilting, and the first sensors and the test bench 15 are fixed together. Preferably, the number of the first sensors 08 is an even number, such as four shown in the figure, and the four first sensors 08 are preferably symmetrically placed at the four corners of the bottom of the balance platform 07 to prevent the balance platform 07 from tilting and turning over.

The pulley 10 is assembled completely, the pulley 10 is arranged on the support 12 through the pulley fixing part 11, the support 12 is fixed on the appropriate position of the test bench 15, and the pulley 10 is adjusted to an appropriate height and fixed. The centers of the wire inlet holes on the arm 04 correspond to each other and have the same height, so as to reduce the friction between the pulley 10 and the stay wire 09 when sliding. Stay wire 09 is walked around pulley 10, and one end is tied on the weight 13, and the other end passes the wire inlet hole of rocking arm 04 and is tied on the rocking arm 04, and then weight 13 is placed on the second sensor 14, and the second sensor 14 can also be a pressure/tension sensor, and the second sensor and the test bench 15 can also be fixedly connected by bolts and other connecting pieces. Adjust the relationship between the rocker arm 04, the pulley 10 and the weight 13 so that the stay wire 09 is in a tight state and wait for the measurement.

It can be understood that, in order to ensure the normal operation of the above test device, it must also be connected to a power source to provide power for the devices in the test device. When the test fixture is assembled, the components that require power are connected to the power source by wires. After the motor 02 to be tested is fixed on the test device according to the above connection relationship, connect the terminals of the first sensors 08 and the second sensors 14, connect the wires of the motor 02 to be tested to a suitable electronic speed controller 19, and connect The computer is powered on and controls the rotation of the motor 02 to be tested. The rotation of the motor 02 to be tested can drive the rocker arm 04 to rotate, and the rocker arm 04 drives the pull wire 09 to rotate around the pulley 10, thereby applying a pulling force to the weight 13. The pulling force is the The torque when the motor rotates can be directly measured by the second sensor 14 . In addition, when the motor 02 to be tested rotates, the propeller 01 rotates to generate a pulling force, which can be applied to the first sensor 08 after passing through the flange bearing 05 and the balance table 07, so the rotation of the motor to be tested can be directly measured through the first sensor 08 After the pull.

According to the above 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, it can be obtained that the motor 02 to be tested is equipped with the propeller 01 Measured tensile and torque values.

Using the test device for the small unmanned aerial vehicle motor provided in this embodiment, the pulling force and torque of the motor can be measured conveniently and quickly at the same time, and the overall structure design is simple, the cost is low, and it is efficient and practical; the measured data such as pulling force and torque can be transmitted to the computer in real time to facilitate data processing.

Example 2

The test device for the small unmanned aerial vehicle motor provided by this embodiment, as shown in the figure, also includes a tachometer 06 for measuring the rotational speed of the motor 02 to be tested, and the tachometer 06 is arranged on the balance table 07 On the other hand, the distance between it and the central axis of the balance platform 07 is smaller than the rotation diameter of the propeller 01 connected to the motor 02 to be tested. Specifically, the tachometer 06 is a digital infrared tachometer. When the motor 02 to be tested rotates, it drives the propeller 01 to rotate. Since the digital infrared tachometer is set within the radius of rotation of the propeller 01, the rotational speed of the propeller 01 can be directly detected, which is also the rotational speed of the motor 02 to be tested.

Further, the test device also includes an ammeter 18, which is clamped between the two power lines of the motor 02 to be tested, and measures the working current of the motor 02 to be tested after it rotates. The ammeter 18 can be a clamp-type ammeter. After the power line of the motor 02 to be tested is connected, the clamp-type ammeter is clamped between the two power lines. time current.

Adopt the test device of the small unmanned aerial vehicle motor provided by the embodiment of the present invention, comprise the tension test structure, torque test structure and computer that are placed on the test bench, at least can measure motor pull force, torque conveniently and quickly at the same time, and overall structural design Simple, low cost, efficient and practical; measurement data such as tension and torque can be transmitted to the computer in real time for data processing.

The test device for the small unmanned aerial vehicle motor provided by this embodiment can conveniently and quickly measure the pulling force, torque, rotating speed, and current of the motor at the same time, and the overall structure design is simple, low in cost, efficient and practical; pulling force, torque, rotating speed, and current And other measurement data can be transmitted to the computer in real time, which is convenient for data processing, and it is convenient to obtain curves such as tension-rotational speed and rotational speed-torque for testers to use.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: it can still be Modifications are made to the technical solutions described in the foregoing embodiments, or equivalent replacements are made to some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims (10)

1. a kind of testing device of small unmanned aircraft motor, it is characterized in that, comprise the tension test structure, torque test structure and computer that are placed on the test bench; The tensile test structure includes a motor base, a rocker arm, a flange bearing assembly, a balance platform and a plurality of first sensors fixedly connected in sequence from top to bottom; wherein, the flange bearing assembly includes The cylinder on the top and the flange bearing sleeved on the outside of the cylinder; the motor seat, the rocker arm and the flange bearing are fixedly connected, and the edge of the rocker arm is formed with a wire hole; a plurality of the The first sensors are evenly distributed on the bottom of the balance platform; The torque testing structure includes a bracket and a pulley arranged on the bracket; one end of the pull wire is connected to the wire inlet hole on the rocker arm, and the other end is connected to the weight after bypassing the pulley; the weight is set on the second sensor, wherein the centerline of the pulley has the same height as the center of the inlet hole; The computer is electrically connected to a plurality of the first sensors and the second sensors, and displays the pulling force and torque of the motor to be tested obtained according to the detection results of the first sensors and the second sensors. 2. the testing device of small unmanned aerial vehicle motor according to claim 1, is characterized in that, also comprises: The tachometer measures the rotating speed of the motor to be tested, and is arranged on the balance platform, and the distance between it and the central axis of the balance platform is smaller than the rotation diameter of the propeller connected to the motor to be tested. 3. according to the testing device of the small unmanned aerial vehicle motor described in claim 2, it is characterized in that: The tachometer is a digital infrared tachometer. 4. The test device of the described small unmanned aircraft motor of claim 1, is characterized in that, also comprises: The ammeter is clamped between the two power lines of the motor to be tested, and measures the working current of the motor to be tested after it rotates. 5 . The test device for a small unmanned aerial vehicle motor according to claim 4 , wherein the ammeter is a clamp-on ammeter. 6. according to the testing device of the described small unmanned aerial vehicle motor of any one of claim 1-5, it is characterized in that, also comprises: The electronic governor is placed on the test bench, electrically connected with the motor to be tested, and adjusts the speed of the motor to be tested. 7. the testing device of small unmanned aerial vehicle motor according to claim 6, is characterized in that, also comprises in the described tension test structure: The gasket is arranged between the flange bearing and the balance platform. 8. The test device for a small unmanned aerial vehicle motor according to claim 7, wherein the gasket is a polytetrafluoroethylene gasket. 9. The test device for a small unmanned aerial vehicle motor according to claim 8, wherein, in the tensile test structure, there are four first sensors, which are symmetrically arranged at the bottom of the balance platform. 10. The test device for a small unmanned aerial vehicle motor according to claim 9, wherein the first sensor and the second sensor are fixedly connected to the bottom of the balance platform by bolts.