Unmanned aerial vehicle test platform

Abstract

The utility model discloses an unmanned aerial vehicle test platform, which belongs to the technical field of unmanned aerial vehicle test, and comprises a chassis and an unmanned aerial vehicle, four corners of the chassis are provided with double-layer angle irons, a baffle plate is inserted between the double-layer angle irons, the top of the chassis is fixedly connected with a support ring, and the top of the chassis is provided with a tension sensor corresponding to the center of the support ring. A plurality of laser range finders are arranged on the surface of the case, a protection assembly is placed in the supporting ring, a counterweight assembly is arranged in the protection assembly, and the bottom of the protection assembly is connected with a tension sensor through a steel wire rope. Under the combined action of the protection assembly, the tension sensor, the laser range finder and the steel wire rope, vertical take-off and landing of the whole unmanned aerial vehicle during loading can be tested, the unmanned aerial vehicle can be prevented from being crashed, hang stability data of the unmanned aerial vehicle can be collected through the arrangement of the ball body, and the balance weight assembly is arranged. The gravity center of the unmanned aerial vehicle during testing is consistent with the gravity center of the unmanned aerial vehicle during use, and the load weight of the unmanned aerial vehicle can be changed by arranging a balancing weight.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle testing, in particular to a unmanned aerial vehicle testing platform. Background Art

[0002] UAVs are multifunctional small aircraft used in many industries such as agriculture, military, and express delivery. In order to ensure the reliability of UAVs during use, a test platform is required to test the UAVs during the development process.

[0003] Existing drone testing platforms fix the drone's tripod to the test equipment and simulate the drone's load through tension. This cannot effectively simulate the position of the drone's center of gravity when loaded, making it impossible to test loaded vertical takeoff and landing data. If the drone starts at an excessive speed due to tester error, the tripod may break and cause an uncontrolled crash, resulting in damage to the drone.

[0004] Therefore, a UAV testing platform is proposed to solve the above problems. Utility Model Content

[0005] The purpose of the utility model is to solve the problems that the UAV test platform in the prior art cannot effectively simulate the vertical take-off and landing of the UAV when loaded and may crash out of control during testing.

[0006] In order to achieve the above purpose, the present invention adopts the following technical solutions:

[0007] A drone testing platform includes a chassis and a drone. Double-layer angle irons are fixedly installed at the four corners of the chassis, and baffles are inserted between the double-layer angle irons. A support ring is fixedly connected to the top of the chassis. A tension sensor is provided at the center of the top of the chassis corresponding to the support ring. Multiple laser rangefinders are provided around the support ring on the upper surface of the chassis. A protective assembly is placed in the support ring, and a counterweight assembly is provided inside the protective assembly. A steel wire rope is fixedly connected to the bottom of the protective assembly, and the other end of the steel wire rope is fixedly connected to the tension sensor.

[0008] Preferably, a plurality of observation holes are provided on the surface of the baffle.

[0009] Preferably, the protective assembly includes a fixing ring and a clamping ring, a plurality of spheres are fixedly connected to the edge of the fixing ring, a plurality of clamping grooves are opened on the top of the fixing ring, a first protective net is fixedly connected to the bottom of the fixing ring, a mounting block is provided inside the fixing ring, the bottom of the mounting block is fixedly connected to the wire rope, a counterweight assembly is provided on the top of the mounting block, a plurality of support rods are fixedly connected to the outer wall of the mounting block, and the other end of the support rod is fixedly connected to the fixing ring.

[0010] Preferably, a plurality of clamping blocks are fixedly installed at the bottom of the clamping ring corresponding to the clamping grooves, and the top of the clamping ring is fixedly connected to a second protective net.

[0011] Preferably, a through pipe is fixedly connected to the center of the bottom of the first protective net.

[0012] Preferably, the counterweight assembly includes a tray fixedly connected to the top of the mounting block, the center of the tray is fixedly connected to a limiting screw, the top of the screw is threadedly connected to a mounting plate, and the mounting plate is fixedly connected to the bottom of the drone.

[0013] Preferably, a plurality of counterweight blocks are provided between the mounting plate and the tray, and a through hole matching the screw rod is opened at the center of the counterweight block.

[0014] Compared with the prior art, the beneficial effects of the present invention are:

[0015] 1. The utility model, with the joint action of the protective component, the tension sensor, the laser rangefinder and the steel wire rope, can test the vertical take-off and landing of the entire drone under load, and prevent the drone from crashing. When the drone takes off and lands vertically, the laser rangefinder continuously measures the distance from the sphere to the surface of the chassis, and the swing data of the drone during vertical take-off and landing is obtained by the numerical changes of multiple groups of laser rangefinders. By setting the sphere, the drone's hovering stability data can be collected. When the drone is swaying in the air, the reading of the laser rangefinder will continue to change under the action of the sphere surface. The hovering stability of the drone can be obtained by analyzing the frequency and amplitude of the change in the reading. If the drone loses control and falls due to a malfunction, the drone carrying the protective component will hit the baffle, and the test personnel will be protected by the baffle, and the drone will be protected by the first protective net and the second protective net.

[0016] 2. The utility model sets a counterweight assembly. Under the joint action of the mounting block and the support rod, the weight of the protection assembly is borne by the UAV's bracket, so that the center of gravity of the UAV during testing is consistent with that during actual use, avoiding the center of gravity shift caused by the protection assembly. By setting the counterweight block, the load weight of the UAV can be changed, realizing the function of supporting load vertical take-off and landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the three-dimensional structure of a UAV test platform proposed in the utility model;

[0018] Figure 2 This is a schematic diagram of the internal structure of a UAV test platform proposed in this utility model;

[0019] Figure 3 This is an assembly diagram of double-layer angle iron and baffle in a UAV test platform proposed in the utility model;

[0020] Figure 4 This is a cross-sectional view of a protective component and a counterweight component in a UAV test platform proposed in the present invention;

[0021] Figure 5 for Figure 4 Enlarged view of point A in the middle;

[0022] Figure 6 This is an assembly diagram of the protective component and counterweight component in the UAV test platform proposed by the utility model.

[0023] In the figure: 1. Chassis; 2. UAV; 3. Double-layer angle iron; 4. Baffle; 5. Support ring; 6. Tension sensor; 7. Laser rangefinder; 8. Wire rope; 9. Observation hole; 10. Fixing ring; 11. Snap ring; 12. Sphere; 13. Slot; 14. First protective net; 15. Mounting block; 16. Support rod; 17. Block; 18. Second protective net; 19. Through pipe; 20. Pallet; 21. Limit screw; 22. Mounting plate; 23. Counterweight. DETAILED DESCRIPTION

[0024] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0025] Reference Figure 1-6 A UAV test platform includes a chassis 1 and a UAV 2. Double-layer angle irons 3 are fixedly installed at the four corners of the chassis 1, and baffles 4 are inserted between the double-layer angle irons 3. A support ring 5 is fixedly connected to the top of the chassis 1. A tension sensor 6 is provided at the center of the top of the chassis 1 corresponding to the support ring 5. Multiple laser rangefinders 7 are provided around the support ring 5 on the upper surface of the chassis 1. A protective component is placed in the support ring 5, and a counterweight component is provided inside the protective component. A steel wire rope 8 is fixedly connected to the bottom of the protective component, and the other end of the steel wire rope 8 is fixedly connected to the tension sensor 6.

[0026] Furthermore, a plurality of observation holes 9 are provided on the surface of the baffle 4 , through which the test status of the UAV 2 can be observed.

[0027] Furthermore, the protective assembly includes a fixed ring 10 and a clamping ring 11, the edge of the fixed ring 10 is fixedly connected with multiple spheres 12, the top of the fixed ring 10 is provided with multiple slots 13, the bottom of the fixed ring 10 is fixedly connected with a first protective net 14, the interior of the fixed ring 10 is provided with a mounting block 15, the bottom of the mounting block 15 is fixedly connected to the wire rope 8, the outer wall of the mounting block 15 is fixedly connected with multiple support rods 16, the other end of the support rod 16 is fixedly connected to the fixed ring 10, multiple blocks 17 are fixedly installed at the bottom of the clamping ring 11 corresponding to the slots 13, the top of the clamping ring 11 is fixedly connected with a second protective net 18, and the center of the bottom of the first protective net 14 is fixedly connected to a through pipe 19.

[0028] It should be noted that the number and positions of the spheres 12 match those of the laser rangefinder 7 .

[0029] A further benefit of adopting the above method is that when the drone 2 takes off and lands vertically, by comparing the changes in the values ​​of multiple groups of laser rangefinders 7, the swing data of the drone 2 during vertical takeoff and landing can be obtained. By setting the sphere 12, the reading of the laser rangefinder 7 will continue to change under the action of the surface of the sphere 12. By analyzing the frequency and amplitude of the changes in the readings, the hovering stability of the drone 2 can be obtained. If the drone 2 loses control and falls due to a malfunction, the protective component will protect the tester and the drone 2 itself.

[0030] Furthermore, the counterweight assembly includes a tray 20 fixedly connected to the top of the mounting block 15, a limiting screw 21 fixedly connected to the center of the tray 20, a mounting plate 22 threadedly connected to the top of the screw, the mounting plate 22 is fixedly connected to the bottom of the drone 2, and a plurality of counterweight blocks 23 are arranged between the mounting plate 22 and the tray 20, and a through hole matching the screw is opened in the center of the counterweight block 23.

[0031] It should be noted that the counterweight 23 is provided as follows Figure 6 The various sizes shown can be configured with weights according to test requirements before testing.

[0032] A further advantage of adopting the above method is that, under the joint action of the mounting block 15 and the support rod 16, the weight of the protective component is borne by the bracket of the drone 2, so that the center of gravity is consistent with that when mounted, avoiding the center of gravity shift caused by the protective component. By setting the counterweight block 23, the load weight of the drone 2 can be changed, thereby achieving the function of supporting load vertical take-off and landing.

[0033] When the present invention is in use, the fixing ring 10 is placed on the top of the supporting ring 5 through the first protective net 14, and a suitable counterweight block 23 is selected and placed on the surface of the tray 20 through the limiting screw 21, and the mounting plate 22 is connected to the limiting screw 21, and then the bottom of the drone 2 is connected through the mounting plate 22, and the clamping ring 11 is clamped with the fixing ring 10 through the clamping groove 13 to complete the assembly. After the assembly is completed, the weight of the protective component is borne by the mounting bracket of the drone 2, so that the center of gravity is consistent with that when mounted, avoiding the center of gravity offset caused by the protective component. Finally, the fixing ring 10 is manually adjusted to the posture of the sphere 12 corresponding to the laser rangefinder 7 and the baffle 4 is inserted between the double-layer angle iron 3 to complete the test preparation;

[0034] When the UAV 2 takes off and lands vertically, the lift of the UAV 2 is tested through the tension sensor 6 and the steel wire rope 8, and the distance from the sphere 12 to the surface of the chassis 1 is continuously measured through the laser rangefinder 7. The swing data of the UAV 2 during vertical take-off and landing is obtained through the numerical changes of multiple groups of laser rangefinders 7. By setting the sphere 12, the hovering stability data of the UAV 2 can be collected. When the UAV 2 is swaying in the air, the reading of the laser rangefinder 7 will continue to change under the action of the surface of the sphere 12. The hovering stability of the UAV 2 can be obtained by analyzing the frequency and amplitude of the change in the reading, thereby achieving the purpose of testing the vertical take-off and landing of the UAV 2 with load and the stability of the load hovering in the air. During this process, the test status can be observed through the observation hole 9;

[0035] If the drone 2 loses control and falls due to a malfunction, the wire rope 8 can prevent the drone 2 from leaving the test area. The out-of-control drone 2 will carry the protective components and hit the baffle 4. The baffle 4 protects the tester and prevents the tester from being cut by the blades of the drone 2. The first protective net 14 and the second protective net 18 protect the drone 2 and prevent it from being damaged by the collision.

[0036] The above is only a preferred specific implementation method of the present invention, but the protection scope of the present invention is not limited to this. Any technician familiar with the technical field within the technical scope disclosed by the present invention can make equivalent replacements or changes based on the technical solution and utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A UAV test platform, comprising a chassis (1) and a UAV (2), characterized in that: Double-layer angle irons (3) are fixedly installed at the four corners of the chassis (1), and baffles (4) are inserted between the double-layer angle irons (3). A support ring (5) is fixedly connected to the top of the chassis (1), and a tension sensor (6) is provided at the center of the support ring (5) corresponding to the top of the chassis (1). A plurality of laser rangefinders (7) are provided around the support ring (5) on the upper surface of the chassis (1). A protective component is placed in the support ring (5), and a counterweight component is provided inside the protective component. A steel wire rope (8) is fixedly connected to the bottom of the protective component, and the other end of the steel wire rope (8) is fixedly connected to the tension sensor (6).

2. The UAV test platform according to claim 1, characterized in that: A plurality of observation holes (9) are provided on the surface of the baffle (4).

3. The UAV test platform according to claim 1, characterized in that: The protective assembly comprises a fixing ring (10) and a snap ring (11), the edge of the fixing ring (10) is fixedly connected with a plurality of spheres (12), the top of the fixing ring (10) is provided with a plurality of snap grooves (13), the bottom of the fixing ring (10) is fixedly connected with a first protective net (14), a mounting block (15) is provided inside the fixing ring (10), the bottom of the mounting block (15) is fixedly connected with a steel wire rope (8), a counterweight assembly is provided on the top of the mounting block (15), the outer wall of the mounting block (15) is fixedly connected with a plurality of support rods (16), and the other end of the support rod (16) is fixedly connected with the fixing ring (10).

4. The UAV test platform according to claim 3, characterized in that: A plurality of clamping blocks (17) are fixedly installed at the bottom of the clamping ring (11) corresponding to the clamping groove (13), and a second protective net (18) is fixedly connected to the top of the clamping ring (11).

5. The UAV test platform according to claim 3, characterized in that: A through pipe (19) is fixedly connected to the center of the bottom of the first protective net (14).

6. The UAV test platform according to claim 3, characterized in that: The counterweight assembly comprises a tray (20) fixedly connected to the top of the mounting block (15); a limiting screw (21) is fixedly connected to the center of the tray (20); a mounting plate (22) is threadedly connected to the top of the screw; and the mounting plate (22) is fixedly connected to the bottom of the drone (2).

7. The UAV test platform according to claim 6, characterized in that: A plurality of counterweight blocks (23) are provided between the mounting plate (22) and the tray (20), and a through hole for matching the screw is opened at the center of the counterweight block (23).

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