Urban rescue unmanned aerial vehicle flight performance testing device

Abstract

The utility model relates to the field of unmanned aerial vehicles, and discloses an urban rescue unmanned aerial vehicle flight performance test device, which comprises a test board; the two supporting frames are installed on the test bench, and the unmanned aerial vehicle is arranged between the two supporting frames; the adjusting seat is mounted between the two supporting frames; the rotating seat is mounted on the inner ring of the adjusting seat; and the cross flow fan is mounted on the inner ring of the rotating seat. According to the utility model, by integrating the adjustable cross flow fan, the rotating seat and the adjusting seat, complex environments with different wind speeds, wind directions and flight heights can be simulated, so that the testing device can restore various wind conditions possibly encountered in actual rescue more truly, thereby evaluating the flight performance of the unmanned aerial vehicle more comprehensively; by stacking the counterweight plate and installing the load test plate on the test bench, the flight state of the unmanned aerial vehicle under the load condition can be simulated, so that the stability of the unmanned aerial vehicle under different loads can be tested.

Description

Technical Field

[0001] The utility model relates to the field of unmanned aerial vehicles (UAVs), and in particular to a flight performance testing device for urban rescue UAVs. Background Art

[0002] As an efficient and flexible rescue tool, drones are playing an increasingly important role in urban rescue. In order to ensure the effectiveness and safety of drones in rescue operations, their flight performance must be tested comprehensively and accurately.

[0003] Existing urban rescue drone flight performance test equipment has significant limitations in terms of test conditions. Most of these devices only provide a relatively simple test environment, making it difficult to test the drone's stability under load in different wind speeds, directions, and weather conditions. These devices are unable to simulate the various complex environments that may be encountered in actual rescue operations. Especially under load conditions, drone flight stability is crucial to the success of rescue operations. This, to a certain extent, limits the application of drones in rescue operations. Utility Model Content

[0004] In order to solve the above-mentioned problems, the present invention is implemented through the following technical solutions.

[0005] A flight performance test device for an urban rescue UAV comprises: a test bench; two support frames installed on the test bench, with a UAV arranged between the two support frames; an adjustment seat installed between the two support frames; a rotating seat installed on the inner ring of the adjustment seat; a cross-flow fan installed on the inner ring of the rotating seat, for generating controllable wind speed and direction; the rotating seat is configured to rotate on the adjustment seat, for driving the cross-flow fan to rotate, so as to adjust the blowing direction; the adjustment seat is configured to rise and fall between the two support frames, for driving the cross-flow fan to rise and fall, so as to adjust the blowing position of the cross-flow fan; the cross-flow fan is configured to rotate on the rotating seat, for adjusting the blowing direction.

[0006] The rotating seat includes: a groove, which is opened on the inner circle of the rotating seat, and the cross flow fan is installed in the groove; a third power source, which is installed on the inner wall of the groove, and the power shaft of the third power source is connected to the cross flow fan.

[0007] The rotating seat also includes: a second power source installed on the bottom of the rotating seat; and a small gear installed on the power shaft of the second power source.

[0008] The adjusting seat comprises an internal gear mounted on the bottom of the adjusting seat, a small gear connected to the internal gear, and the projection shapes of the adjusting seat, the rotating seat and the internal gear are all ring-shaped.

[0009] The support frame includes: a moving block, a through hole is opened on one side of the support frame, the moving block is connected in the through hole, and the adjustment seat is connected to the moving block; a first power source is installed on the support frame, and the power shaft of the first power source is connected to the moving block.

[0010] The test bench includes: several counterweight plates, which are stacked on the test bench, and each counterweight plate has two symmetrically arranged slots; a load test plate, which is installed on top of the several counterweight plates; a lifting ring, which is connected to the load test plate by a lifting rope and is used to connect the drone; two control rods, which are installed on the load test plate and are symmetrically arranged, and the several counterweight plates are set between the two control rods.

[0011] The control rod includes: a moving hole, which is opened on one side of the control rod; a moving seat, which is connected to the moving hole and has a connecting groove at one end of the moving seat; an insertion rod, one end of which is installed in the connecting groove and the other end is inserted into the slot, which is used to limit the counterweight plate; a connecting rod, one end of which is connected to the moving seat and the other end passes through the connecting groove and extends to the outside of the moving seat; an elastic member, one end of which is connected to the insertion rod and the other end is connected to the inner wall of the connecting groove.

[0012] The test bench also includes a guide rod installed on the top of the test bench, and the load test plate and the counterweight plate are both sleeved on the guide rod.

[0013] This utility model provides a flight performance test device for urban rescue drones. Compared with existing technologies, it has the following advantages:

[0014] 1. By integrating an adjustable cross-flow fan, a rotating base, and an adjustment base, it is possible to simulate complex environments with different wind speeds, directions, and flight altitudes. This allows the test device to more realistically reproduce the various wind conditions that may be encountered in actual rescue operations, thereby more comprehensively evaluating the flight performance of the drone.

[0015] 2. By stacking counterweight plates and installing load test plates on the test bench, the flight state of the drone under load conditions can be simulated. By connecting the drone with rings and ropes, the size of the load can be precisely adjusted to test the drone's stability under different loads, which is crucial for evaluating the drone's flight capabilities when carrying supplies or personnel in rescue operations.

[0016] 3. The adjustment seat, rotating seat and cross-flow fan in this solution are all highly adjustable and can be flexibly adjusted according to different test requirements, so that the test device can be applied to drones of different models and weights, improving the flexibility and adaptability of the test. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the three-dimensional structure proposed by the utility model.

[0018] Figure 2This is a schematic diagram of the three-dimensional structure from another perspective proposed by the utility model.

[0019] Figure 3 This is a schematic diagram of the cross-sectional structure of the adjustment seat and the rotating seat proposed in the utility model.

[0020] Figure 4 This is a schematic diagram of the cross-sectional structure of the test bench, load test plate and counterweight plate proposed in the utility model.

[0021] Figure 5 This is an enlarged cross-sectional view of the control rod, movable seat and insertion rod proposed in the present invention.

[0022] The reference numerals in the figures are:

[0023] 1. Test bench; 101. Guide rod;

[0024] 2. Support frame; 201. Moving block; 202. First power source;

[0025] 3. Adjustment seat; 301. Internal gear;

[0026] 4. Rotating seat; 401. Second power source; 402. Pinion; 403. Groove; 404. Third power source;

[0027] 5. Cross flow fan;

[0028] 6. Load test plate; 601. Lifting ring; 602. Control rod; 603. Moving seat; 604. Insert rod; 605. Moving hole; 606. Connecting rod; 607. Elastic member;

[0029] 7. Counterweight plate; 701. Slot. DETAILED DESCRIPTION

[0030] The present invention will be further described below with reference to specific embodiments. It should be understood that these embodiments are only used to illustrate the present invention and are not used to limit the scope of protection of the present invention.

[0031] The following describes the embodiments of the present invention through specific examples. Those skilled in the art will readily understand the other advantages and benefits of the present invention from the disclosure herein. The present invention may also be implemented or applied through various other specific embodiments, and the details in this specification may be modified or altered based on different perspectives and applications without departing from the spirit of the present invention.

[0032] Reference Figure 1-Figure 5A flight performance test device for an urban rescue UAV includes: a test bench 1; two support frames 2, mounted on the test bench 1, with the UAV set between the two support frames 2; an adjustment seat 3, mounted between the two support frames 2; a rotating seat 4, mounted on the inner ring of the adjustment seat 3; a cross-flow fan 5, mounted on the inner ring of the rotating seat 4, for generating controllable wind speed and direction. The cross-flow fan 5 can simulate the wind conditions that the UAV may encounter during flight; the rotating seat 4 is configured to rotate on the adjusting seat 3 to drive the cross-flow fan 5 to rotate to adjust the blowing direction; the rotating seat 4 can simulate the flight performance of the UAV under different wind directions; the adjusting seat 3 is set to rise and fall between the two support frames 2, and is used to drive the cross flow fan 5 to rise and fall to adjust the blowing position of the cross flow fan 5; it rises and falls between the two support frames 2, driving the cross flow fan 5 to rise and fall to adjust the blowing position, simulating the wind conditions that the UAV may encounter when flying at different altitudes; the cross flow fan 5 is set to rotate on the rotating seat 4 to adjust the blowing direction; by rotating on the rotating seat 4, the blowing direction can be flexibly adjusted to meet different test requirements.

[0033] The rotating seat 4 includes: a groove 403, which is opened on the inner ring of the rotating seat 4, and the cross-flow fan 5 is installed in the groove 403; a third power source 404, which is installed on the inner wall of the groove 403, and the power shaft of the third power source 404 is connected to the cross-flow fan 5; a second power source 401, which is installed at the bottom of the rotating seat 4; a pinion 402, which is installed on the power shaft of the second power source 401; the adjusting seat 3 includes: an internal gear 301, which is installed at the bottom of the adjusting seat 3, and the pinion 402 is connected to the internal gear 301; the second power source 401 drives the pinion 402 to rotate, so that the rotating seat 4 can rotate smoothly on the adjusting seat 3, further improving the adjustment accuracy of the blowing direction.

[0034] The projection shapes of the adjustment base 3 , the rotating base 4 and the internal gear 301 are all ring-shaped.

[0035] The support frame 2 includes: a moving block 201, a through hole is opened on one side of the support frame 2, the moving block 201 is connected in the through hole, and the adjustment seat 3 is connected to the moving block 201; a first power source 202 is installed on the support frame 2, and the power shaft of the first power source 202 is connected to the moving block 201; the moving block 201 is driven to move by the first power source 202, and the height of the adjustment seat 3 can be adjusted, thereby changing the blowing position of the cross flow fan 5 to adapt to different test scenarios. The first power source 202 uses a cylinder and can also use a linear motor.

[0036] The test bench 1 includes: several counterweight plates 7, which are stacked on the test bench 1, and each counterweight plate 7 has two symmetrically arranged slots 701; by stacking the counterweight plates 7, the weight and stability of the test bench 1 can be adjusted as needed to adapt to the testing requirements of drones of different weights and models; a load test plate 6, which is installed on the top of several counterweight plates 7; a lifting ring 601, which is connected to the load test plate 6 through a lifting rope, and the lifting ring 601 is used to connect the drone; two control rods 602, which are installed on the load test plate 6, are symmetrically arranged, and several counterweight plates 7 are arranged between the two control rods 602; the counterweight plate 7 is used to increase the weight of the load test plate 6; through the cooperation of the slots 701 and the insertion rods 604, the number of counterweight plates 7 can be conveniently increased or decreased to adapt to the testing requirements of drones of different weights.

[0037] The control rod 602 includes: a moving hole 605, which is opened on one side of the control rod 602; a moving seat 603, which is connected to the moving hole 605, and a connecting groove is opened at one end of the moving seat 603; an insertion rod 604, one end of which is installed in the connecting groove, and the other end is inserted into the slot 701, which is used to limit the counterweight plate 7; a connecting rod 606, one end of which is connected to the moving seat 603, and the other end passes through the connecting groove and extends to the outside of the moving seat 603; an elastic member 607, one end of which is connected to the insertion rod 604, and the other end is connected to the inner wall of the connecting groove; through the cooperation of the moving seat 603, the insertion rod 604, the connecting rod 606 and the elastic member 607, the insertion rod 604 can be easily inserted or pulled out to achieve rapid fixation and release of the counterweight plate 7; the design of the control rod 602 enables the tester to easily adjust the number and position of the counterweight plates 7, thereby improving the flexibility and efficiency of the test.

[0038] The guide rod 101 is installed on the top of the test bench 1 , and the load test plate 6 and the counterweight plate 7 are both sleeved on the guide rod 101 .

[0039] During use, first, according to the model and weight requirements of the drone, the weight and stability of the test bench 1 are adjusted by stacking the counterweight plates 7, and the connecting rod 606 is pulled to drive the insertion rod 604 to slide out of the slot 701, and the movable seat 603 and the position of the insertion rod 604 on the control rod 602 are movable, and the insertion rod 604 is inserted into the slot 701 on the corresponding counterweight plate 7 to facilitate the rapid increase or decrease of the number of counterweight plates 7, and the load test plate 6 is installed on the top of several counterweight plates 7, and the drone is connected through the lifting ring 601 and the lifting rope to ensure that the drone is firmly suspended under the load test plate 6, and according to the test requirements, the height of the adjustment seat 3 is adjusted by the first power source 202, thereby changing the blowing position of the cross flow fan 5, which can simulate the wind conditions that the drone may encounter when flying at different altitudes, and start the third power source 404 to drive the cross flow fan 5 to rotate in the groove 403 of the rotating seat 4 to adjust the blowing direction. This can simulate the flight performance of the UAV under different wind directions. The wind speed of the crossflow fan 5 is set through the control panel to simulate different wind intensities. When the UAV is suspended stably and the test parameters are set, the crossflow fan 5 is started to simulate the wind conditions. The flight status of the UAV under the simulated wind conditions is observed and recorded, including key indicators such as flight trajectory, stability, and response time. According to the test requirements, the rotating seat 4 can be driven by the second power source 401 to rotate on the adjustment seat 3 to further adjust the blowing direction to comprehensively evaluate the flight performance of the UAV under different wind directions. During the test, the sensors and data acquisition system are used to collect real-time data of the UAV. The flight data of the human and the machine, including flight speed, altitude, attitude angle, etc., are imported into the data analysis software for processing and analysis to evaluate the flight performance and stability of the UAV. According to the analysis results, the UAV is adjusted and optimized as necessary to improve its performance in urban rescue operations. After the test is completed, the cross flow fan 5 and all power sources are turned off, and the counterweight plate 7 is quickly released through the cooperation of the moving seat 603, the insertion rod 604, the connecting rod 606 and the elastic member 607, and the load test plate 6 and the UAV are removed from the test bench 1. The test device is checked and cleaned to ensure that it is in good working condition for the next test.

[0040] In summary, compared with the existing technology, it has the following beneficial effects:

[0041] By integrating the adjustable cross-flow fan 5, the rotating seat 4 and the adjusting seat 3, it is possible to simulate complex environments with different wind speeds, wind directions and flight altitudes, so that the test device can more realistically restore the various wind conditions that may be encountered in actual rescue operations, thereby more comprehensively evaluating the flight performance of the UAV.

[0042] By stacking the counterweight plates 7 and installing the load test plate 6 on the test bench 1, the flight state of the UAV under load conditions can be simulated. By connecting the UAV with the lifting ring 601 and the lifting rope, the size of the load can be accurately adjusted to test the UAV under different loads and stability, which is crucial for evaluating the flight ability of the UAV when carrying supplies or personnel in rescue operations.

[0043] The adjustment seat 3, rotating seat 4 and cross-flow fan 5 in this solution are all highly adjustable and can be flexibly adjusted according to different test requirements, so that the test device can be applied to drones of different models and weights, thereby improving the flexibility and adaptability of the test.

[0044] Thus, although the present invention has been described herein with reference to specific embodiments thereof, freedom of modification, various changes and substitutions are within the foregoing disclosure, and it should be understood that in some cases, some features of the present invention will be employed without the corresponding use of other features without departing from the scope and spirit of the proposed invention. Thus, many modifications may be made to adapt particular circumstances or materials to the true scope and spirit of the present invention. The present invention is not intended to be limited to the specific terminology used in the claims below and / or to the specific embodiments disclosed as the best mode contemplated for carrying out the invention, but the present invention will include any and all embodiments and equivalents falling within the scope of the appended claims. Therefore, the scope of the present invention will be determined solely by the appended claims.

Claims

1. A flight performance test device for urban rescue drones, characterized in that: include: Testbench (1); Two support frames (2) are mounted on the test bench (1), and the drone is arranged between the two support frames (2); An adjustment seat (3) is installed between the two support frames (2); A rotating seat (4) mounted on the inner ring of the adjusting seat (3); A cross-flow fan (5) is mounted on the inner ring of the rotating seat (4) and is used to generate controllable wind speed and direction; The rotating seat (4) is configured to rotate on the adjusting seat (3) to drive the cross-flow fan (5) to rotate so as to adjust the blowing direction; The adjustment seat (3) is configured to be raised and lowered between the two support frames (2) and is used to drive the cross-flow fan (5) to be raised and lowered, so as to adjust the blowing position of the cross-flow fan (5); The cross-flow fan (5) is configured to rotate on the rotating seat (4) to adjust the blowing direction.

2. The urban rescue UAV flight performance test device according to claim 1, characterized in that: The rotating seat (4) comprises: The groove (403) is provided on the inner ring of the rotating seat (4), and the cross-flow fan (5) is installed in the groove (403).

3. The urban rescue UAV flight performance test device according to claim 2, characterized in that: The rotating seat (4) also includes: The third power source (404) is installed on the inner wall of the groove (403), and the power shaft of the third power source (404) is connected to the cross-flow fan (5).

4. The urban rescue UAV flight performance test device according to claim 1, characterized in that: The rotating seat (4) also includes: A second power source (401) is installed at the bottom of the rotating seat (4); The pinion (402) is mounted on the power shaft of the second power source (401).

5. The urban rescue UAV flight performance test device according to claim 4, characterized in that: The adjustment seat (3) comprises: The internal gear (301) is mounted on the bottom of the adjustment seat (3), and the pinion (402) is connected to the internal gear (301).

6. The urban rescue UAV flight performance test device according to claim 5, characterized in that: The projection shapes of the adjustment seat (3), the rotating seat (4) and the internal gear (301) are all ring-shaped.

7. The urban rescue UAV flight performance test device according to claim 1, characterized in that: The support frame (2) comprises: A moving block (201), a through hole is provided on one side of the support frame (2), the moving block (201) is connected in the through hole, and the adjustment seat (3) is connected to the moving block (201); A first power source (202) is mounted on the support frame (2), and a power shaft of the first power source (202) is connected to the moving block (201).

8. The urban rescue UAV flight performance test device according to claim 1, characterized in that: The test bench (1) comprises: A plurality of counterweight plates (7) are stacked on the test bench (1), and each counterweight plate (7) is provided with two symmetrically arranged slots (701); A load test plate (6) mounted on top of a plurality of counterweight plates (7); A lifting ring (601) is connected to the load test plate (6) via a lifting rope, and the lifting ring (601) is used to connect to the drone; Two control rods (602) are mounted on the load test plate (6) and are symmetrically arranged, and a plurality of counterweight plates (7) are arranged between the two control rods (602).

9. The urban rescue UAV flight performance test device according to claim 8, characterized in that: The control lever (602) comprises: A movable hole (605) is provided on one side of the control rod (602); A movable seat (603) is connected to the movable hole (605), and a connecting groove is provided at one end of the movable seat (603); An insert rod (604), one end of which is mounted in the connecting groove and the other end of which is inserted into the slot (701), for limiting the counterweight plate (7); A connecting rod (606), one end of which is connected to the movable seat (603), and the other end of which passes through the connecting groove and extends to the outside of the movable seat (603); The elastic member (607) has one end connected to the insertion rod (604) and the other end connected to the inner wall of the connection groove.

10. The urban rescue UAV flight performance test device according to claim 8, characterized in that: The test bench (1) further comprises: A guide rod (101) is mounted on the top of the test bench (1), and the load test plate (6) and the counterweight plate (7) are both sleeved on the guide rod (101).

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