An apparatus for dynamic testing of unmanned aerial vehicle power systems

Abstract

The application discloses a device for dynamic testing of a power system of an unmanned aerial vehicle, which comprises a base, a torque sensor, a first support plate, a second support plate, a sliding sleeve, a sliding rod, a pressure sensor and a spring, wherein the torque sensor is installed on the base, the second support plate is installed on the torque sensor, the sliding sleeve is installed on the second support plate, the first support plate is installed on the sliding sleeve, the pressure sensor is further arranged on the second support plate, the sliding rod is arranged in the sliding sleeve, a motor mounting disc is installed at the top end of the sliding rod, a second mounting seat is arranged at the bottom end of the sliding rod, a first mounting seat is arranged on the pressure sensor, the spring is arranged between the first mounting seat and the second mounting seat, the sliding rod and the sliding sleeve form a moving pair, the second support plate and the torque sensor form a rotating pair, and the motor mounting disc is further provided with a rotating speed sensor; and the device can measure the tension, torque and rotating speed of the power system during movement.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) power system testing, and in particular to a device for dynamic performance testing and evaluation of UAV power systems. Background Technology

[0002] With the widespread application of vertical takeoff and landing (VTOL) drone technology in fields such as military reconnaissance, logistics transportation, agricultural plant protection, and aerial photography, the requirements for its reliability, endurance, and flight performance are also increasing. As the core subsystem of a drone, the power system directly determines its power output, energy efficiency, vibration and noise characteristics, and overall flight quality. Therefore, accurate and reliable testing of the power system is crucial in the research, development, production, and maintenance of drones.

[0003] Currently, the most common method for testing UAV power systems is to fix the motor and propellers to a rigid support, making the propeller disk plane perpendicular to the ground, and then directly measure relevant parameters of the motor during operation using sensors. However, this method has significant limitations: it cannot accurately reflect the actual working state and performance of the power system under flight attitudes such as climb or descent.

[0004] Therefore, there is an urgent need in the field for a dedicated testing device that can safely, reliably, and repeatably simulate typical flight attitudes of UAVs (such as climb and descent) in a ground-based laboratory environment and achieve comprehensive, high-precision measurements. Utility Model Content

[0005] To overcome the problem that existing technologies cannot accurately reflect the actual working state and performance of the power system of a UAV during flight attitudes such as climbing or descending, this invention provides a device for dynamic testing of UAV power systems. The device uses a sliding sleeve and a sliding rod to form a sliding pair, allowing the propeller and motor to move up and down, thereby simulating the flight process of a UAV and measuring the required data simultaneously.

[0006] The technical solution adopted by this invention to solve its technical problem is: a device for dynamic testing of a UAV power system, comprising a base, a torque sensor, a first support plate, a second support plate, a sliding sleeve, a sliding rod, a pressure sensor, and a spring. The base is equipped with a torque sensor, the torque sensor is mounted on the second support plate, the second support plate is equipped with a sliding sleeve, the sliding sleeve is mounted on the first support plate, and the second support plate is also equipped with a pressure sensor. The sliding sleeve contains a sliding rod, the top of which is equipped with a motor mounting plate, and the bottom of which is equipped with a second mounting seat. The pressure sensor is equipped with a first mounting seat, and a spring is provided between the first and second mounting seats. The sliding rod and the sliding sleeve form a sliding pair, and the second support plate and the torque sensor form a rotating pair. The motor mounting plate is also equipped with a speed sensor.

[0007] In the aforementioned device for dynamic testing of a drone power system, the sliding sleeve and the sliding rod are in at least three sets.

[0008] In the aforementioned device for dynamic testing of a drone power system, the sliding sleeve is a linear bearing.

[0009] The aforementioned device for dynamic testing of a drone power system includes a motor mounting plate equipped with a propeller-shaped motor.

[0010] The aforementioned device for dynamic testing of a drone power system includes an electrical box mounted on its base.

[0011] The aforementioned device for dynamic testing of a drone power system includes a connecting rod between the first support plate and the second support plate.

[0012] The aforementioned device for dynamic testing of a drone power system includes a second mounting base with a fixing plate mounted on a slide bar. Attached Figure Description

[0013] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0014] Figure 1 This is a schematic diagram of the present invention;

[0015] Figure 2 This is a front view of the present invention;

[0016] In the diagram, 1 is the motor mounting plate, 2 is the slide rod, 3 is the sliding sleeve, 4 is the first bracket plate, 5 is the second bracket plate, 6 is the connecting rod, 7 is the base, 8 is the electrical box, 9 is the spring, 10 is the pressure sensor, 11 is the torque sensor, 12 is the first mounting base, 13 is the second mounting base, 14 is the fixing plate, 15 is the motor, 16 is the blade, and 17 is the speed sensor. Detailed Implementation

[0017] A device for dynamic testing of a drone's power system includes a base 7, a torque sensor 11, a first support plate 4, a second support plate 5, a sliding sleeve 3, a sliding rod 2, a pressure sensor 10, and a spring 9. The torque sensor 11 is mounted on the base 7, and the second support plate 5 is fixed to the sensor. The sliding sleeve 3 is mounted on the second support plate 5, and the first support plate 4 is fixed to the upper end of the sliding sleeve 3. To improve the overall structural resistance to deformation, the first support plate 4 and the second support plate 5 are reinforced by a connecting rod 6. The pressure sensor 10 is also mounted on the second support plate 5.

[0018] A sliding rod 2 is inserted inside the sliding sleeve 3. The top end of the sliding rod 2 is fixed to the motor mounting plate 1, and the bottom end is provided with a second mounting seat 13. The pressure sensor 10 is provided with a first mounting seat 12, and a spring 9 is provided between the two. The sliding rod 2 and the sliding sleeve 3 form a sliding pair to realize axial relative movement. The fixing plate 14 fixes the second mounting seat 13 to the sliding rod 2.

[0019] During testing, motor 15 drives blade 16 to rotate, generating lift. As the rotational speed increases, the lift lifts slide rod 2 via motor mounting plate 1, compresses spring 9, and transmits the pressure to pressure sensor 10, where the pressure value F1 is measured. Simultaneously, the motor's counter-torque acts on slide rod 2, transmitted through sliding sleeve 3 to torque sensor 11, where the torque value N1 is measured. The counter-torque causes radial pressure F3 between slide rod 2 and sliding sleeve 3, which in turn generates sliding friction force F2. F3 can be calculated using torque N1 and lever arm L (F3 = N1 / L). Combining this with the friction coefficient μ of sliding sleeve 3 (known or calibrable), the friction force F2 = F3 × μ is calculated. Finally, the pulling force generated by the power system is F = F2 + F1 + G, where G is the total weight of motor 15, blade 16, speed sensor 17, and slide rod 2.

[0020] The motor mounting plate 1 is equipped with a speed sensor 17 for measuring the speed of the motor 15. The base 7 has an electrical box 8 with a built-in data acquisition unit to collect pressure, torque, and speed sensor data in real time. Through data processing by a host computer, the three key parameters for evaluating the power system—motor speed, tension, and torque—can be acquired simultaneously.

Claims

1. A device for dynamic testing of a UAV power system, comprising a base, a torque sensor, a first support plate, a second support plate, a sliding sleeve, a sliding rod, a pressure sensor, and a spring, characterized in that... A torque sensor is mounted on the base, a second support plate is mounted on the torque sensor, a sliding sleeve is mounted on the second support plate, a first support plate is mounted on the sliding sleeve, a pressure sensor is also provided on the second support plate, a sliding rod is provided inside the sliding sleeve, a motor mounting plate is mounted on the top of the sliding rod, a second mounting seat is provided at the bottom of the sliding rod, a first mounting seat is provided on the pressure sensor, a spring is provided between the first mounting seat and the second mounting seat, and a speed sensor is provided on the motor mounting plate.

2. The apparatus for dynamic testing of a UAV power system according to claim 1, characterized in that, There are at least three sets of the sliding sleeve and the sliding rod.

3. The apparatus for dynamic testing of a UAV power system according to claim 1, characterized in that, The sliding sleeve is a linear bearing.

4. The apparatus for dynamic testing of a UAV power system according to claim 1, characterized in that, The motor mounting plate is equipped with a motor with blades.

5. The apparatus for dynamic testing of a UAV power system according to claim 1, characterized in that, A connecting rod is provided between the first support plate and the second support plate.

6. The apparatus for dynamic testing of a UAV power system according to claim 1, characterized in that, An electrical box is mounted on the base.

7. The apparatus for dynamic testing of a UAV power system according to claim 1, characterized in that, The second mounting base is provided with a fixing plate for mounting the slide bar.

Images