A simulated load testing device for an actuator of a drone

Abstract

The utility model belongs to the technical field of unmanned aerial vehicle landing gear, and relates to a simulated load testing device for an unmanned aerial vehicle actuator cylinder, comprising a driving member, a first support frame, a test bench and an actuator cylinder; the first support frame is used to connect the driving member to the test bench; the actuator cylinder is placed above the test bench; the driving member is connected to the actuator cylinder, and the driving member drives the actuator cylinder to perform reciprocating linear motion; the utility model arranges the first support frame to connect the driving member and the test bench, so that the driving member will not shake or tilt during operation, thereby improving the stability of the driving member during operation, thereby making the force transmitted to the actuator cylinder by the driving member consistent with the target force, and improving the accuracy and reliability of the simulated load test of the actuator cylinder.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle landing gear, in particular to a simulated load testing device for an actuating cylinder of a unmanned aerial vehicle. Background Art

[0002] The actuator is an important component of the UAV landing gear system and is responsible for controlling the retraction and extension of the landing gear. Fighter jets on aircraft carriers need to unfold their folding wings before taking off and landing to ensure that they have sufficient lift and stability during flight. Before unfolding the folding wings, it is necessary to ensure that the unlocking mechanism of the folding wings is reliable enough. Therefore, it is usually necessary to simulate the real load environment to ensure that the actuator can work reliably in actual operations.

[0003] The actuator includes a cylinder body, a piston disposed in the cylinder body and capable of reciprocating along the axial direction of the cylinder body, and a piston rod connected to the piston; during the load simulation process, the reciprocating motion of the piston in the cylinder body simulates the unlocking and locking actions, and the piston rod transmits and bears the simulated load. By simulating the resistance when unlocking and the force required when locking, the performance data of the actuator under different working conditions is provided.

[0004] Referring to the patent document with application number 201520746666.1, an actuator load simulation device and a semi-physical simulation tester are disclosed, including: a drive control unit, a motor, and an actuator. The drive control unit sends a control current signal to the motor to drive and control the motor to transmit output power to the actuator, and the actuator applies a simulated working load to the actuator test piece.

[0005] It can be seen from this that the driving member in the prior art lacks a supporting structure. When performing a load simulation test, the driving member is prone to shaking during operation, causing the force transmitted by the driving member to the actuator to deviate from the target force, affecting the accuracy and reliability of the actuator simulation load test. Utility Model Content

[0006] In order to solve the technical problem in the background technology that the driving member lacks a supporting structure and is prone to shaking during operation, resulting in a deviation between the force transmitted by the driving member to the actuator and the target force, the utility model provides a simulated load testing device for the actuator of a drone.

[0007] The utility model provides a simulated load testing device for the actuator of an unmanned aerial vehicle, and a first support frame is provided to connect the driving member and the test bench, so that the driving member will not shake or tilt during operation, thereby improving the stability of the driving member during operation, and further ensuring that the force transmitted to the actuator by the driving member is consistent with the target force, thereby improving the accuracy and reliability of the simulated load test of the actuator.

[0008] In order to solve the above technical problems, the utility model provides the following technical solutions:

[0009] A simulated load test device for an actuator cylinder of an unmanned aerial vehicle comprises a driving member, a first support frame, a test bench and an actuator cylinder; the first support frame is used to connect the driving member to the test bench; the actuator cylinder is placed above the test bench; the driving member is connected to the actuator cylinder, and the driving member drives the actuator cylinder to perform reciprocating linear motion.

[0010] In a specific possible implementation manner, the driving element is a servo electric cylinder.

[0011] In a specific possible implementation scheme, it also includes a servo electric cylinder control system; the servo electric cylinder control system is electrically connected to both the actuator and the drive member.

[0012] In a specific possible implementation scheme, the driving member includes a driving member body, a driving output shaft and a guide member; the driving output shaft is connected to the actuator cylinder, and the driving member body drives the actuator cylinder to perform reciprocating linear motion through the driving output shaft; the driving output shaft is movably connected to the guide member, and the driving member is connected to the first support frame through the guide member.

[0013] In a specific implementation scheme, it also includes a tension pressure sensor; the tension pressure sensor is arranged close to the drive output shaft, used to measure the feedback force of the drive output shaft, and the tension pressure sensor is electrically connected to the servo electric cylinder control system.

[0014] In a specific possible implementation scheme, it also includes a micro switch and a proximity switch; the micro switch is connected to the tension pressure sensor, and the micro switch is electrically connected to the servo electric cylinder control system; the proximity switch is connected to the actuator, and the proximity switch is electrically connected to the servo electric cylinder control system.

[0015] In a specific possible implementation scheme, it also includes a second support frame; the second support frame is used to connect the actuator cylinder to the test bench.

[0016] In a specific possible implementation scheme, it also includes a third support frame; one side of the third support frame is connected to the drive output shaft through a tension pressure sensor, and the other side is connected to the input end of the actuator.

[0017] In a specific possible implementation scheme, it also includes a display; the display is electrically connected to the servo electric cylinder control system.

[0018] In a specific possible implementation scheme, it also includes a power supply; the power supply is electrically connected to the display, the servo electric cylinder control system, the tension and pressure sensor, the micro switch and the proximity switch.

[0019] In summary, the utility model includes the following beneficial technical effects:

[0020] 1. The simulated load test device for the actuator of the unmanned aerial vehicle of the utility model is provided with a first support frame connecting the driving member and the test bench, so that the driving member will not shake or tilt during operation, thereby improving the stability of the driving member during operation, and further making the force transmitted to the actuator by the driving member consistent with the target force, thereby improving the accuracy and reliability of the simulated load test of the actuator.

[0021] 2. The simulated load test device of the actuator of the unmanned aerial vehicle of the utility model is provided with a tension and pressure sensor to measure the feedback force on the drive output shaft in real time and monitor whether the feedback force on the drive output shaft is consistent with the target force, so that the servo electric cylinder control system can adjust the output of the drive member according to the feedback force monitored by the tension and pressure sensor to ensure that the force transmitted to the actuator by the drive member is consistent with the target force, thereby improving the accuracy of the simulated load test of the actuator.

[0022] 3. The simulated load test device for the actuator of the unmanned aerial vehicle of the utility model is provided with a micro switch to collect the unlocking signal of the actuator and transmit it to the servo electric cylinder control system to complete the unlocking of the actuator; a proximity switch is provided to collect the locking signal of the actuator and transmit it to the servo electric cylinder control system to complete the locking of the actuator; the micro switch and proximity switch are provided so that the servo electric cylinder control system can obtain the unlocking state and locking state of the actuator in real time and accurately, thereby improving the test accuracy of the simulated load test of the actuator. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 The utility model is a schematic diagram of the overall structure of a simulated load test device for an actuator of a UAV.

[0024] Figure 2 It is a partial schematic diagram of a simulated load test device for an actuator of a UAV of the present invention, and is intended to illustrate the connection relationship between a driving member and the actuator.

[0025] Figure 3 It is a partial schematic diagram of the simulated load test device of the actuator cylinder of the unmanned aerial vehicle of the utility model, and is intended to illustrate the connection relationship between the actuator cylinder, the third support frame and the tension and pressure sensor.

[0026] Figure 4 It is a partial schematic diagram of a simulated load test device for an actuator of a UAV of the utility model, and is intended to illustrate a driving part.

[0027] Figure 5 It is a partial schematic diagram of the simulated load test device of the actuator of the unmanned aerial vehicle of the utility model, and is intended to illustrate the first support frame.

[0028] Figure 6It is a partial schematic diagram of a simulated load test device for an actuator of a UAV of the utility model, and is intended to illustrate the actuator.

[0029] Figure 7 It is a partial schematic diagram of the simulated load test device of the actuator of the unmanned aerial vehicle of the utility model, and is intended to illustrate the second support frame.

[0030] Figure 8 It is a partial schematic diagram of a simulated load test device for an actuator of a UAV of the utility model, and is intended to illustrate a tension pressure sensor.

[0031] Fig. 9 It is a partial schematic diagram of the simulated load test device of the actuator of the unmanned aerial vehicle of the utility model, and is intended to illustrate the third support frame.

[0032] Explanation of the accompanying drawings: 1. driving member; 11. driving output shaft; 12. guide member; 13. driving member body; 2. first support frame; 3. test bench; 4. actuator; 5. second support frame; 6. third support frame; 7. tension pressure sensor; 8. proximity switch. DETAILED DESCRIPTION

[0033] The technical solution of the present invention is further explained below in conjunction with the accompanying drawings and embodiments, but the present invention is not limited to the implementation methods described below.

[0034] Reference Figure 1 , Figure 2 and Figure 3 A simulated load test device for an actuator of a drone includes: a driving member 1, a first support frame 2, a test bench 3, and an actuator 4. The first support frame 2 is used to connect the driving member 1 with the test bench 3; the actuator 4 is placed above the test bench 3; the driving member 1 is connected to the actuator 4, and the driving member 1 drives the actuator 4 to perform reciprocating linear motion. Figure 1 The middle driving member 1 and the actuator 4 are in a disconnected state.

[0035] Specifically, the driving member 1 can be configured as a servo electric cylinder, an electric push rod, etc., and any configuration in which the driving member 1 drives the actuator 4 to perform reciprocating linear motion is acceptable.

[0036] Reference Figure 1 , Figure 4 and Figure 5The driving member 1 includes a driving member body 13, a driving output shaft 11 and a guide member 12. The driving output shaft 11 is connected to the actuator 4, and the driving member body 13 drives the actuator 4 to perform reciprocating linear motion through the driving output shaft 11; the driving output shaft 11 is movably connected to the guide member 12, and the driving member 1 is connected to the first support frame 2 through the guide member 12. Specifically, the guide member 12 can be set as a guide sleeve, a bearing seat, etc., and the driving member 1 is connected to the test bench 3 through the guide member 12 and the motion trajectory of the driving output shaft 11 is guided.

[0037] Embodiment 1:

[0038] Reference Figure 1 and Figure 4 In the simulated load test device of the actuator of the drone in this embodiment, the driving member 1 is a servo electric cylinder. The servo electric cylinder realizes very precise speed control, position control and force control through a high-precision servo control system, thereby improving the accuracy of the simulated load test of the actuator.

[0039] Embodiment 2:

[0040] Reference Figure 1 The simulated load test device for the actuator of the unmanned aerial vehicle in this embodiment, based on the embodiment 1, further includes a servo electric cylinder control system. The servo electric cylinder control system is electrically connected to the actuator 4 and the driving member 1. In this embodiment, the brand of the servo electric cylinder control system (including software products and hardware products) is Huichuan, and the model is AM402-1608TN.

[0041] Embodiment 3:

[0042] Reference Figure 3 The simulated load test device for the actuator of the drone of this embodiment, based on the embodiment 2, further includes a tension pressure sensor 7. The tension pressure sensor 7 is arranged close to the drive output shaft 11, and is used to measure the feedback force of the drive output shaft 11, and the tension pressure sensor 7 is electrically connected to the servo electric cylinder control system.

[0043] Embodiment 4:

[0044] Reference Figure 3 and Figure 6 The simulated load test device for the actuator of the drone of this embodiment, on the basis of the third embodiment, further comprises a proximity switch 8 and a micro switch. The micro switch is connected to the tension pressure sensor 7, and the micro switch is electrically connected to the servo electric cylinder control system; the proximity switch 8 is connected to the actuator 4, and the proximity switch 8 is electrically connected to the servo electric cylinder control system.

[0045] Embodiment 5:

[0046] The simulated load test device for the actuator of the unmanned aerial vehicle of this embodiment, based on the embodiment 1, further comprises a display. The display is electrically connected to the servo electric cylinder control system.

[0047] Embodiment 6:

[0048] Reference Figure 3 The simulated load test device for the actuator of the drone of this embodiment, based on the fifth embodiment, further comprises a power supply. The power supply is electrically connected to the display, the servo electric cylinder control system, the tension and pressure sensor 7, the micro switch and the proximity switch 8.

[0049] Embodiment 7:

[0050] Reference Figure 1 , Figure 6 and Figure 7 The simulated load test device for the UAV actuator of this embodiment further includes a second support frame 5. The second support frame 5 is used to connect the actuator 4 to the test bench 3. Specifically, a first ear piece is connected to the top of the second support frame 5, and a second ear piece corresponding to the first ear piece is connected to the actuator 4. The first ear piece and the second ear piece are connected by a latch to realize the connection between the actuator 4 and the second support frame 5.

[0051] Embodiment 8:

[0052] Reference Figure 3 , Figure 8 and Fig. 9 , the simulated load test device of the actuator cylinder of the unmanned aerial vehicle in this embodiment, on the basis of embodiment 7, further includes a third support frame 6. One side of the third support frame 6 is connected to the drive output shaft 11 through the tension and pressure sensor 7, and the other side is connected to the input end of the actuator cylinder 4. Specifically, a connecting ear is provided at the input end of the actuator cylinder 4, and two third ear pieces are connected to the third support frame 6 near the side of the actuator cylinder 4, and a mounting cavity is formed between the two third ear pieces. The connecting ear is placed in the mounting cavity, and the connecting ear is connected to the two second ear pieces by a latch to achieve the connection between the actuator cylinder 4 and the third support frame 6. A first mounting hole is provided on the tension and pressure sensor 7, and a second mounting hole corresponding to the first mounting hole is provided on the third support frame 6. The first mounting hole and the second mounting hole are connected by a latch to achieve the connection between the tension and pressure sensor 7 and the third support frame 6. A screw is connected to the end of the tension and pressure sensor 7 away from the actuator cylinder 4, and a threaded hole matching the screw is provided on the end of the drive output shaft 11 near the tension and pressure sensor 7. The screw is screwed into the threaded hole to achieve the connection between the drive member 1 and the tension and pressure sensor 7.

[0053] The working principle of the simulated load testing device of the actuator cylinder of an unmanned aerial vehicle according to the utility model is as follows: at the beginning of the test, the servo electric cylinder control system controls the preloading of the target force of the servo electric cylinder. During the preloading process of the target force, the tension pressure sensor 7 synchronously measures the feedback force on the drive output shaft 11 and transmits it to the servo electric cylinder control system. The servo electric cylinder control system determines whether the feedback force is consistent with the target force. If not, the loading continues. If so, the actuator cylinder 4 is unlocked and the servo electric cylinder works.

[0054] During the test, the tension and pressure sensor 7 synchronously measures the feedback force on the drive output shaft 11 and transmits it to the servo cylinder control system. The servo cylinder control system adjusts the output of the servo cylinder according to the feedback force measured by the tension and pressure sensor 7 to ensure that the feedback force on the drive output shaft 11 is consistent with the target force.

[0055] During the unlocking process, the microswitch collects the unlocking signal and transmits the unlocking signal to the servo cylinder control system. The servo cylinder control system unloads the force of the servo cylinder, and the actuator 4 stops moving and waits for the next running instruction. At this time, the actuator 4 completes the unlocking; during the locking process, the proximity switch 8 collects the locking signal and transmits the locking signal to the servo cylinder control system. The servo cylinder control system unloads the force of the servo cylinder, and the actuator 4 stops moving and waits for the next running instruction. At this time, the actuator 4 completes the locking.

[0056] After the test is finished, the servo electric cylinder control system controls the servo electric cylinder to stop, completing the simulated load test of the actuator 4.

[0057] The above are all preferred embodiments of the present utility model, and are not intended to limit the protection scope of the present utility model. Therefore, any equivalent changes made based on the structure, shape, and principle of the present utility model should be included in the protection scope of the present utility model.

Claims

1. A simulated load test device for an actuator of an unmanned aerial vehicle, comprising a driving member (1), a first support frame (2), a test bench (3) and an actuator (4); The first support frame (2) is used to connect the driving member (1) to the test bench (3); The actuator (4) is placed above the test bench (3); The driving member (1) is connected to the actuating cylinder (4), and the driving member (1) drives the actuating cylinder (4) to perform reciprocating linear motion.

2. The simulated load testing device for the UAV actuator according to claim 1, characterized in that: The driving member (1) is a servo electric cylinder.

3. The simulated load testing device for the UAV actuator according to claim 1, characterized in that: It also includes a servo electric cylinder control system; The servo electric cylinder control system is electrically connected to both the actuator (4) and the drive member (1).

4. The simulated load testing device for the UAV actuator according to claim 3 is characterized in that: The driving member (1) comprises a driving member body (13), a driving output shaft (11) and a guide member (12); The drive output shaft (11) is connected to the actuator cylinder (4), and the drive member body (13) drives the actuator cylinder (4) to perform reciprocating linear motion via the drive output shaft (11); The drive output shaft (11) is movably connected to the guide member (12), and the drive member (1) is connected to the first support frame (2) via the guide member (12).

5. The simulated load testing device for the UAV actuator according to claim 4, characterized in that: Also includes a tension pressure sensor (7); The tension and pressure sensor (7) is arranged close to the drive output shaft (11) and is used to measure the feedback force of the drive output shaft (11), and the tension and pressure sensor (7) is electrically connected to the servo electric cylinder control system.

6. The simulated load testing device for the UAV actuator according to claim 5, characterized in that: Also includes a micro switch and a proximity switch (8); The micro switch is connected to the tension pressure sensor (7), and the micro switch is electrically connected to the servo electric cylinder control system; The proximity switch (8) is connected to the actuator (4), and the proximity switch (8) is electrically connected to a servo electric cylinder control system.

7. The simulated load testing device for the UAV actuator according to claim 1, characterized in that: Also includes a second support frame (5); The second support frame (5) is used to connect the actuator (4) to the test bench (3).

8. The simulated load testing device for the actuator of a UAV according to claim 5, characterized in that: Also includes a third support frame (6); One side of the third support frame (6) is connected to the drive output shaft (11) via a tension pressure sensor (7), and the other side is connected to the input end of the actuator cylinder (4).

9. The simulated load testing device for the actuator of a UAV according to claim 6, characterized in that: Also includes a display; The display is electrically connected to the servo electric cylinder control system.

10. The simulated load testing device for the actuator of a UAV according to claim 9, characterized in that: Also includes a power supply; The power supply is electrically connected to the display, the servo electric cylinder control system, the tension pressure sensor (7), the micro switch and the proximity switch (8).

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