Small unmanned aerial vehicle testing device for synchronously testing lift force and multidirectional torque

Abstract

The utility model provides a small unmanned aerial vehicle testing device for synchronously testing lift force and multidirectional torque, and relates to the technical field of unmanned aerial vehicle testing. Comprising a mounting plate, a horizontal mounting rack, a vertical mounting rack, a lift force test sensor, an unmanned aerial vehicle mounting table, a steering torque test sensor, a steering torque test sensor mounting rack, a rolling and pitching torque test sensor and a rolling and pitching torque test sensor mounting rack, a third mounted bearing mounting plate and a fourth mounted bearing mounting plate are rotationally connected to the first rotating shaft, one end of the fourth mounted bearing mounting plate is connected with a fixed contact end, a second rotating shaft is arranged on the vertical mounting frame, the end of the second rotating shaft is rotationally connected with a fifth fixed beam, the unmanned aerial vehicle is mounted on the unmanned aerial vehicle mounting table, and the center of the unmanned aerial vehicle is aligned with the axis of the second rotating shaft. According to the utility model, the lifting force, the steering torque, the rolling torque and the pitching torque of the unmanned aerial vehicle can be measured without dismounting, and the mechanical properties of the unmanned aerial vehicle can be tested more comprehensively.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane test technical field especially, it relates to a kind of small unmanned plane testing device of synchronous test lift and multidirectional torque. BACKGROUND

[0002] In recent years, with the vigorous development of low-altitude industry, the field of civil unmanned planes develops rapidly, and in civil unmanned planes, small unmanned planes account for a large proportion, and the mechanical properties such as lift and maneuverability of small unmanned planes are key factors considered by the public when purchasing.

[0003] Currently, most unmanned plane whole machine testing devices focus on lift testing, and ignore the calibration of key parameters such as torque.

[0004] In existing unmanned plane comprehensive testing devices, although the torque and lift of unmanned planes can be tested, there are problems such as incomplete testing content, unreasonable device design leading to turbulence and errors, and complex design leading to increased costs, so there is currently a lack of an effective and cost-effective comprehensive testing device for small unmanned planes.

[0005] Patent document CN118907431B discloses a kind of unmanned plane testing system, realizes the determination of vertical tension, inclined tension and torque of unmanned plane whole machine, but can only test the torque when unmanned plane turns, cannot test the torque when unmanned plane rolls and pitches, and the testing content is not comprehensive, and its test table, outer turntable and other structures are relatively large in size, when related testing of unmanned plane is carried out, it will interfere with the airflow of unmanned plane, affect the accuracy of related testing results of unmanned plane, at the same time, its complex structure design also increases the manufacturing cost of the device, so the problems are high device cost, difficult to guarantee the accuracy of testing results, and incomplete testing content.

[0006] Patent document CN111086652B discloses a kind of unmanned plane lift testing platform, realizes relatively accurate determination of unmanned plane lift, and has certain compatibility, but cannot realize the determination of torque, so the problem is that the testing content is not comprehensive, and only the determination of unmanned plane lift can be realized. UTILITY MODEL CONTENT

[0007] According to the above-mentioned technical problems of existing devices, such as high cost, difficult to guarantee the accuracy of testing results, and incomplete testing content, a small unmanned plane testing device for synchronous testing of lift and multidirectional torque is provided. The technical means adopted by the utility model are as follows:

[0008] A small unmanned aerial vehicle (UAV) test device for synchronously testing lift and multi-directional torque comprises: a mounting plate, a horizontal mounting frame, a vertical mounting frame, a lift test sensor, a UAV mounting platform, a steering torque test sensor, a steering torque test sensor mounting frame, a roll and pitch torque test sensor, and a roll and pitch torque test sensor mounting frame, wherein the horizontal mounting frame, the steering torque test sensor mounting frame, and the roll and pitch torque test sensor mounting frame are all fixedly connected to the mounting plate, the steering torque test sensor is fixedly connected to the steering torque test sensor mounting frame, and the roll and pitch torque test sensor is fixedly connected to the roll and pitch torque test sensor mounting frame;

[0009] The horizontal mounting frame is provided with a first rotating shaft, the third seat bearing mounting plate and the fourth seat bearing mounting plate are rotatably connected to the first rotating shaft, the lower side of one end of the fourth seat bearing mounting plate is fixedly connected to a fixed contact end, and the fixed contact end is in contact with the roll and pitch torque test sensor;

[0010] The vertical mounting frame is fixedly connected above the third seat bearing mounting plate and the fourth seat bearing mounting plate, and a second rotating shaft is provided on the vertical mounting frame. The end of the second rotating shaft is rotatably connected to the fifth fixed beam, and the lift test sensor is fixedly connected to one end of the fifth fixed beam, and the other end of the fifth fixed beam is in contact with the steering torque test sensor. The UAV mounting platform is fixedly connected to the upper side of the lift test sensor, and the UAV is fixedly installed on the UAV mounting platform, and the center of the UAV is aligned with the axis of the second rotating shaft.

[0011] Furthermore, the horizontal mounting frame includes a first fixed beam and a second fixed beam, the first fixed beam and the second fixed beam are fixedly connected to the mounting plate, the upper ends of the first fixed beam and the second fixed beam on both sides are respectively fixedly connected to the first seat bearing mounting plate and the second seat bearing mounting plate, the inner sides of the middle positions of the first seat bearing mounting plate and the second seat bearing mounting plate are respectively fixedly connected to the first diamond seat bearing and the second diamond seat bearing, the first diamond seat bearing and the second diamond seat bearing are respectively rotatably connected to the two ends of the first rotating shaft, the first vertical seat bearing and the second vertical seat bearing are respectively rotatably connected on both sides of the first rotating shaft, the first vertical seat bearing and the second vertical seat bearing are located between the first diamond seat bearing and the second diamond seat bearing, the third seat bearing mounting plate is fixedly connected to the second vertical seat bearing, and the fourth seat bearing mounting plate is fixedly connected to the first vertical seat bearing.

[0012] Furthermore, a limit plate is placed on the first bearing seat mounting plate and the second bearing seat mounting plate.

[0013] Furthermore, the first fixed beam and the second fixed beam are arranged in parallel.

[0014] Further, the vertical mounting frame comprises a third fixed beam and a fourth fixed beam, the third fixed beam and the fourth fixed beam are fixedly installed on the third belt bearing mounting plate and the fourth belt bearing mounting plate in parallel, a third rhombic belt bearing is fixedly connected to the upper side of the middle position of the third fixed beam and the fourth fixed beam, the third rhombic belt bearing is rotatably connected to one end of the second rotating shaft, a fifth belt bearing mounting plate and a sixth belt bearing mounting plate are fixedly connected to one side of the upper surface of the middle position of the third fixed beam, a third vertical belt bearing and a fourth vertical belt bearing are installed on the inner side of the fifth belt bearing mounting plate and the sixth belt bearing mounting plate, the third vertical belt bearing and the fourth vertical belt bearing are rotatably connected to the second rotating shaft, a fourth rhombic belt bearing is rotatably connected to the other end of the second rotating shaft, and the fourth rhombic belt bearing is fixedly connected to the fifth fixed beam.

[0015] Further, the fifth fixed beam is provided with two cylindrical protrusions at one end, and the lift test sensor is fixedly connected to the two protrusions.

[0016] Further, the unmanned aerial vehicle mounting table comprises a sixth fixed beam, the sixth fixed beam is fixedly connected to the upper side of the lift test sensor, the two ends of the sixth fixed beam are fixedly connected with a first sliding rail mounting plate and a second sliding rail mounting plate respectively, the two ends of the first sliding rail mounting plate and the second sliding rail mounting plate are fixedly connected with a first sliding rail and a second sliding rail respectively, a first unmanned aerial vehicle fixed beam and a second unmanned aerial vehicle fixed beam are slidably connected to the first sliding rail and the second sliding rail, and an unmanned aerial vehicle is fixedly installed on the first unmanned aerial vehicle fixed beam and the second unmanned aerial vehicle fixed beam.

[0017] Further, the first sliding rail is slidably connected with a first sliding block and a fourth sliding block, the second sliding rail is slidably connected with a second sliding block and a third sliding block, the two ends of the first unmanned aerial vehicle fixed beam are fixedly connected with the first sliding block and the fourth sliding block respectively, and the two ends of the second unmanned aerial vehicle fixed beam are fixedly connected with the second sliding block and the third sliding block respectively.

[0018] Further, the center position of the sixth fixed beam is aligned with the axis of the second rotating shaft.

[0019] Compared with the prior art, the utility model has the advantages of the following:

[0020] 1. The present invention provides a small drone test device for synchronously testing lift and multi-directional torque, which improves upon the overall drone test device. After the drone is fixedly mounted on first and second drone fixing beams, different aspects of the test can be performed by controlling the drone's motion mode. When the drone is controlled in vertical ascent mode, the lift test sensor transmits relevant signals; when the drone is controlled in horizontal steering mode, the steering torque test sensor transmits relevant signals; and when the drone is controlled in roll and pitch motion mode, the roll and pitch torque test sensors transmit relevant signals. With a single fixed installation, the drone can be tested simultaneously or separately for all three aspects, eliminating the need for multiple disassembly. Therefore, the drone's lift, steering torque, roll, and pitch torque can be measured without disassembly, enriching the measurement content and enabling more comprehensive testing of the drone's mechanical properties.

[0021] 2. The small UAV test device for synchronously testing lift and multi-directional torque provided by the utility model optimizes the device structure and has a simple UAV mounting platform structure. By reducing the windward surface area of ​​the UAV mounting platform, the impact of this device on the flow field around the UAV is reduced, making the working conditions of the UAV during testing closer to its actual working conditions when working in the air, thereby making the test results more accurate and reliable.

[0022] 3. The small UAV test device for synchronously testing lift and multi-directional torque provided by the utility model optimizes the device structure, has a simple structure, and reduces manufacturing costs.

[0023] 4. The small UAV test device for synchronously testing lift and multi-directional torque provided by the utility model has an adjustable size between the first UAV fixed beam and the second UAV fixed beam, which can adapt to the testing of small UAVs of different sizes, and thus has good compatibility. At the same time, the first slide rail mounting plate and the second slide rail mounting plate further reinforce the UAV mounting platform. Compared with directly fixing the first UAV fixed beam and the second UAV fixed beam to the sixth fixed beam, this design provides better rigidity, further ensuring the accuracy and safety of the test.

[0024] Based on the above reasons, the utility model can be widely promoted in fields such as drone testing. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0026] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0027] Figure 2 It is a partial schematic diagram of the horizontal mounting frame of the utility model;

[0028] Figure 3 It is a partial schematic diagram of the vertical mounting frame of the present utility model;

[0029] Figure 4 This is a partial schematic diagram of the UAV mounting platform of the present invention.

[0030] In the figure: 1. Mounting plate; 2. Horizontal mounting frame; 201. First fixed beam; 202. Second fixed beam; 203. First bearing seat mounting plate; 204. First diamond bearing seat; 205. First vertical bearing seat; 206. First rotating shaft; 207. Second bearing seat mounting plate; 208. Limiting plate; 209. Second vertical bearing seat; 210. Second diamond bearing seat; 211. Third bearing seat mounting plate; 212. Fourth bearing seat mounting plate; 213. Fixed contact end; 3. Vertical mounting frame; 301. Third fixed beam; 302. Fourth fixed beam; 303. Third diamond bearing seat; 304. Fifth bearing seat mounting plate; 305. Sixth bearing seat mounting plate; 306. Second rotating shaft; 307. Third vertical seat bearing; 308. Fourth vertical seat bearing; 309. Fourth diamond seat bearing; 310. Fifth fixed beam; 4. Lift test sensor; 5. UAV mounting platform; 501. Sixth fixed beam; 502. First slide rail mounting plate; 503. Second slide rail mounting plate; 504. First slide rail; 505. First slider; 506. First UAV fixed beam; 507. Second slide rail; 508. Second slider; 509. Third slider; 510. Second UAV fixed beam; 511. Fourth slider; 601. Steering torque test sensor; 602. Steering torque test sensor mounting bracket; 701. Roll and pitch torque test sensor; 702. Roll and pitch torque test sensor mounting bracket. DETAILED DESCRIPTION

[0031] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the embodiments described are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0032] To address existing issues such as high device costs, difficulty ensuring test accuracy, and incomplete test content, this utility model provides a small UAV test device that simultaneously tests lift and multi-directional torque. This comprehensive test device for small UAVs offers more accurate and reliable test results, comprehensive test content, and a high cost-effectiveness ratio. Through optimized design, this device addresses existing issues such as incomplete test content, prone to errors, and high costs, thereby improving test accuracy and overall cost-effectiveness.

[0033] Reference Figure 1 The present invention proposes a small drone test device for simultaneously testing lift and multi-directional torque, comprising a mounting plate 1, a horizontal mounting frame 2, a vertical mounting frame 3, a lift test sensor 4, a drone mounting platform 5, a steering torque test sensor 601, a steering torque test sensor mounting frame 602, a roll and pitch torque test sensor 701, and a roll and pitch torque test sensor mounting frame 702. The lift test sensor 4, steering torque test sensor 601, and roll and pitch torque test sensor 701 are all PW6DC3MR. In this embodiment, the lift test sensor 4, steering torque test sensor 601, and roll and pitch torque test sensor 701 are all of the same model, and are all pressure test sensors. During testing, pressure data is primarily collected, and torque is not directly measured. Torque data is converted based on pressure and device size. The torque measurement method is prior art.

[0034] A horizontal mounting frame 2 is fixedly connected to the mounting plate 1, a vertical mounting frame 3 is fixedly connected to the upper end of the horizontal mounting frame 2, a lift test sensor 4 is fixedly connected to the upper end of the vertical mounting frame 3, a UAV mounting platform 5 is fixedly connected to the upper side of the lift test sensor 4, one end of the UAV mounting platform 5 is in contact with the steering torque test sensor 601, the steering torque test sensor 601 is fixedly connected to the steering torque test sensor mounting frame 602, the steering torque test sensor mounting frame 602 is fixedly connected to the mounting plate 1, one end of the horizontal mounting frame 2 is in contact with the roll and pitch torque test sensor 701, the roll and pitch torque test sensor 701 is fixedly connected to the roll and pitch torque test sensor mounting frame 702, and the roll and pitch torque test sensor mounting frame 702 is fixedly connected to the mounting plate 1.

[0035] Further, such as Figure 2As shown, the horizontal mounting frame 2 comprises a first fixed beam 201, a second fixed beam 202, a first belt bearing mounting plate 203, a first rhombic belt bearing 204, a first vertical belt bearing 205, a first rotating shaft 206, a second belt bearing mounting plate 207, a limiting plate 208, a second vertical belt bearing 209, a second rhombic belt bearing 210, a third belt bearing mounting plate 211 and a fourth belt bearing mounting plate 212. The first fixed beam 201 and the second fixed beam 202 are symmetrically and fixedly connected to the mounting plate 1 in parallel. The upper end of one side of the first fixed beam 201 and the second fixed beam 202 is fixedly connected with the first belt bearing mounting plate 203. The inner side of the middle position of the first belt bearing mounting plate 203 is fixedly connected with the first rhombic belt bearing 204. The first rhombic belt bearing 204 and the first vertical belt bearing 205 are both rotationally connected with one end of the first rotating shaft 206. The other side of the first fixed beam 201 and the second fixed beam 202 is fixedly connected with the second belt bearing mounting plate 207. The first belt bearing mounting plate 203 and the second belt bearing mounting plate 207 are placed with the limiting plate 208. The second vertical belt bearing 209 and the second rhombic belt bearing 210 are both rotationally connected with the other end of the first rotating shaft 206. The first vertical belt bearing 205 and the second vertical belt bearing 209 are located between the first rhombic belt bearing 204 and the second rhombic belt bearing 210. The second rhombic belt bearing 210 is fixedly connected with the inner side of the middle position of the second belt bearing mounting plate 207. The third belt bearing mounting plate 211 is fixedly connected with the second vertical belt bearing 209. The fourth belt bearing mounting plate 212 is fixedly connected with the first vertical belt bearing 205. The end of the fourth belt bearing mounting plate 212 away from the first vertical belt bearing 205 is fixedly connected with a fixed contact end 213 on the lower side.

[0036] Further, the limiting plate 208 is placed between the first belt bearing mounting plate 203 and the second belt bearing mounting plate 207 and between the third belt bearing mounting plate 211 and the fourth belt bearing mounting plate 212, limiting the counterclockwise rotation of the third belt bearing mounting plate 211 and the fourth belt bearing mounting plate 212.

[0037] Further, as Figure 3As shown, the vertical mounting frame 3 includes a third fixed beam 301, a fourth fixed beam 302, a third diamond seat bearing 303, a fifth seat bearing mounting plate 304, a sixth seat bearing mounting plate 305, a second rotating shaft 306, a third vertical seat bearing 307, a fourth vertical seat bearing 308, a fourth diamond seat bearing 309 and a fifth fixed beam 310. The third fixed beam 301 and the fourth fixed beam 302 are fixedly mounted on the third seat bearing mounting plate 211 and the fourth seat bearing mounting plate 212 in parallel. The third diamond seat bearing 303 is fixedly connected to the upper side of the middle position of the third fixed beam 301 and the fourth fixed beam 302. The fifth seat bearing mounting plate 304 and the sixth seat bearing mounting plate 305 are fixedly connected to one side of the middle position of the upper surface of the beam 301, the third diamond seat bearing 303 is rotatably connected to one end of the second rotating shaft 306, and the third vertical seat bearing 307 and the fourth vertical seat bearing 308 are installed on the inner side of the fifth seat bearing mounting plate 304 and the sixth seat bearing mounting plate 305. The third vertical seat bearing 307 and the fourth vertical seat bearing 308 are both rotatably connected to the second rotating shaft 306, and the other end of the second rotating shaft 306 is rotatably connected to the fourth diamond seat bearing 309, and the fourth diamond seat bearing 309 is fixedly connected to the fifth fixed beam 310.

[0038] Furthermore, two small cylindrical protrusions are provided at one end of the fifth fixing beam 310 .

[0039] Furthermore, the two cylindrical small protrusions of the fifth fixed beam 310 are fixedly connected with the lift test sensor 4, and the upper side of the lift test sensor 4 is fixedly connected with the sixth fixed beam 501, as shown in FIG. Figure 4 As shown, the two ends of the sixth fixed beam 501 are respectively fixedly connected to the first slide rail mounting plate 502 and the second slide rail mounting plate 503, one end of the first slide rail mounting plate 502 and the second slide rail mounting plate 503 is fixedly connected to the first slide rail 504, the first slide rail 504 is slidably connected to the first slider 505, the first slider 505 is fixedly connected to one end of the first UAV fixed beam 506, the other end of the first slide rail mounting plate 502 and the second slide rail mounting plate 503 is fixedly installed with the second slide rail 507, the first slide rail 504 is parallel to the second slide rail 507, the second slide rail 507 is slidably connected to the second slide rail 508 and the third slider 509, the second slider 508 is fixedly connected to the other end of the first UAV fixed beam 506, the third slider 509 is fixedly connected to one end of the second UAV fixed beam 510, the other end of the second UAV fixed beam 510 is fixedly connected to the fourth slider 511, and the fourth slider 511 is slidably connected to the first slide rail 504.

[0040] Furthermore, the center position of the sixth fixed beam 501 is aligned with the axis of the second rotating shaft 306 .

[0041] Furthermore, the first drone fixing beam 506 and the second drone fixing beam 510 are respectively fixedly connected to the first slider 505 and the second slider 508 and the third slider 509 and the fourth slider 511, and can slide on the first slide rail 504 and the second slide rail 507. Therefore, the distance between the first drone fixing beam 506 and the second drone fixing beam 510 is adjustable.

[0042] During the test, the drone is fixedly mounted on the first drone fixing beam 506 and the second drone fixing beam 510 on the drone mounting platform 5. Since the first drone fixing beam 506 and the second drone fixing beam 510 are respectively fixedly connected to the first slider 505, the second slider 508, the third slider 509 and the fourth slider 511, they can slide on the first slide rail 504 and the second slide rail 507, so that the position of the drone can be adjusted. Subsequently, the first slider 505, the second slider 508, the third slider 509 and the fourth slider 511 are fixed to the first slide rail 504 and the second slide rail 507 by external force means such as screw locking or clamp fixing, thereby fixing the first drone fixing beam 506 and the second drone fixing beam 510 so that the center of the drone is aligned with the center of the sixth fixing beam 501. Since the center of the sixth fixing beam 501 is required to be aligned with the axis of the second rotating shaft 306 during device installation, the center of the drone will be aligned with the axis of the second rotating shaft 306.

[0043] The UAV mounting platform 5 of the present invention has a simple structure and reduces the size and windward surface area of ​​the device to a certain extent. By reducing the windward surface area of ​​the UAV mounting platform 5, the impact and interference on the flow field around the UAV is reduced, which better conforms to the actual working conditions of the UAV when operating in the air, making the test results more accurate and reliable.

[0044] When the drone simply generates lift, it causes a slight deformation of the lift test sensor 4. This slight deformation can be converted into an electrical signal via a strain gauge, and the lift can then be reflected on the terminal (prior art) via related equipment (existing equipment). When the drone generates steering torque, the drone mounting platform 5, lift test sensor 4, fifth fixing beam 310, and the entire drone can rotate horizontally about the second rotation axis 306. The distal end of the fifth fixing beam 310 (the end away from the lift test sensor 4) contacts and compresses the steering torque test sensor 601, converting the torque generated by the drone into a slight deformation of the steering torque test sensor 601. This slight deformation can be converted into an electrical signal via a strain gauge, and the steering torque can then be reflected on the terminal (prior art) via related equipment (existing equipment). When the drone generates a roll or pitch torque, the vertical mounting frame 3, the lift test sensor 4, the drone mounting platform 5, the third bearing mounting plate 211, the fourth bearing mounting plate 212 and the drone can rotate around the first rotation axis 206, and the fixed contact end 213 fixedly installed at the far end of the fourth bearing mounting plate 212 contacts the roll and pitch torque test sensor 701, squeezing the roll and pitch torque test sensor 701, and converting the roll or pitch torque of the drone into a small deformation of the roll and pitch torque test sensor 701. The small deformation can be converted into an electrical signal through a strain gauge, and then the pitch torque can be reflected on the terminal (existing technology) through related equipment (existing equipment). At the same time, the limit plate 208 limits the counterclockwise rotation of the third bearing mounting plate 211 and the fourth bearing mounting plate 212, preventing the reverse roll or pitch movement of the drone and ensuring the safe conduct of the test.

[0045] 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 it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A small UAV test device for synchronously testing lift and multi-directional torque, characterized in that: include: A mounting plate (1), a horizontal mounting frame (2), a vertical mounting frame (3), a lift test sensor (4), a UAV mounting platform (5), a steering torque test sensor (601), a steering torque test sensor mounting frame (602), a roll and pitch torque test sensor (701), and a roll and pitch torque test sensor mounting frame (702), wherein the horizontal mounting frame (2), the steering torque test sensor mounting frame (602), and the roll and pitch torque test sensor mounting frame (702) are all fixedly connected to the mounting plate (1), the steering torque test sensor (601) is fixedly connected to the steering torque test sensor mounting frame (602), and the roll and pitch torque test sensor (701) is fixedly connected to the roll and pitch torque test sensor mounting frame (702); The horizontal mounting frame (2) is provided with a first rotating shaft (206), a third seat bearing mounting plate (211) and a fourth seat bearing mounting plate (212) are rotatably connected to the first rotating shaft (206), a fixed contact end (213) is fixedly connected to the lower side of one end of the fourth seat bearing mounting plate (212), and the fixed contact end (213) is in contact with the roll and pitch torque test sensor (701); The vertical mounting frame (3) is fixedly connected above the third seat bearing mounting plate (211) and the fourth seat bearing mounting plate (212); a second rotating shaft (306) is provided on the vertical mounting frame (3); an end of the second rotating shaft (306) is rotatably connected to a fifth fixed beam (310); the lift test sensor (4) is fixedly connected to one end of the fifth fixed beam (310); the other end of the fifth fixed beam (310) is in contact with the steering torque test sensor (601); the UAV mounting platform (5) is fixedly connected to the upper side of the lift test sensor (4); the UAV is fixedly mounted on the UAV mounting platform (5), and the center of the UAV is aligned with the axis of the second rotating shaft (306).

2. The small UAV test device for synchronously testing lift and multi-directional torque according to claim 1, characterized in that: The horizontal mounting frame (2) comprises a first fixed beam (201) and a second fixed beam (202), wherein the first fixed beam (201) and the second fixed beam (202) are fixedly connected to the mounting plate (1), and the upper ends of both sides of the first fixed beam (201) and the second fixed beam (202) are respectively fixedly connected to a first seat bearing mounting plate (203) and a second seat bearing mounting plate (207), and the inner sides of the middle positions of the first seat bearing mounting plate (203) and the second seat bearing mounting plate (207) are respectively fixedly connected to a first diamond seat bearing (204) and a second diamond seat bearing (210), and the first diamond seat bearing The bearing (204) and the second diamond seat bearing (210) are rotatably connected to the two ends of the first rotating shaft (206), and the first vertical seat bearing (205) and the second vertical seat bearing (209) are rotatably connected to the two sides of the first rotating shaft (206), respectively. The first vertical seat bearing (205) and the second vertical seat bearing (209) are located between the first diamond seat bearing (204) and the second diamond seat bearing (210). The third seat bearing mounting plate (211) is fixedly connected to the second vertical seat bearing (209), and the fourth seat bearing mounting plate (212) is fixedly connected to the first vertical seat bearing (205).

3. The small UAV test device for synchronously testing lift and multi-directional torque according to claim 2, characterized in that: A limit plate (208) is placed on the first seat bearing mounting plate (203) and the second seat bearing mounting plate (207).

4. The small UAV test device for synchronously testing lift and multi-directional torque according to claim 2, characterized in that: The first fixed beam (201) and the second fixed beam (202) are arranged in parallel.

5. The small UAV test device for synchronously testing lift and multi-directional torque according to claim 1, characterized in that: The vertical mounting frame (3) includes a third fixed beam (301) and a fourth fixed beam (302), the third fixed beam (301) and the fourth fixed beam (302) being fixedly mounted in parallel on a third seat bearing mounting plate (211) and a fourth seat bearing mounting plate (212), a third diamond seat bearing (303) being fixedly connected to the upper side of the middle position of the third fixed beam (301) and the fourth fixed beam (302), the third diamond seat bearing (303) being rotatably connected to one end of the second rotating shaft (306), and a side of the middle position of the upper surface of the third fixed beam (301) being fixedly connected to the A fifth seat bearing mounting plate (304) and a sixth seat bearing mounting plate (305) are provided, and a third vertical seat bearing (307) and a fourth vertical seat bearing (308) are installed on the inner sides of the fifth seat bearing mounting plate (304) and the sixth seat bearing mounting plate (305). The third vertical seat bearing (307) and the fourth vertical seat bearing (308) are both rotatably connected to the second rotating shaft (306). The other end of the second rotating shaft (306) is rotatably connected to the fourth diamond seat bearing (309), and the fifth fixed beam (310) is fixedly connected to the fourth diamond seat bearing (309).

6. The small UAV test device for synchronously testing lift and multi-directional torque according to claim 1 or 5, characterized in that: One end of the fifth fixed beam (310) is provided with two cylindrical protrusions, and the lift test sensor (4) is fixedly connected to the two protrusions.

7. The small UAV test device for synchronously testing lift and multi-directional torque according to claim 1, characterized in that: The UAV mounting platform (5) comprises a sixth fixed beam (501), the sixth fixed beam (501) being fixedly connected to the upper side of the lift test sensor (4), the two ends of the sixth fixed beam (501) being fixedly connected to a first slide rail mounting plate (502) and a second slide rail mounting plate (503), the two ends of the first slide rail mounting plate (502) and the second slide rail mounting plate (503) being fixedly connected to a first slide rail (504) and a second slide rail (507), the first slide rail (504) and the second slide rail (507) being slidably connected to a first UAV fixed beam (506) and a second UAV fixed beam (510), and the UAV being fixedly mounted on the first UAV fixed beam (506) and the second UAV fixed beam (510).

8. The small UAV test device for synchronously testing lift and multi-directional torque according to claim 7, characterized in that: The first slide rail (504) is slidably connected to a first slider (505) and a fourth slider (511); the second slide rail (507) is slidably connected to a second slider (508) and a third slider (509); the two ends of the first UAV fixed beam (506) are respectively fixedly connected to the first slider (505) and the fourth slider (511); and the two ends of the second UAV fixed beam (510) are respectively fixedly connected to the second slider (508) and the third slider (509).

9. The small UAV test device for synchronously testing lift and multi-directional torque according to claim 7, characterized in that: The center position of the sixth fixed beam (501) is aligned with the axis of the second rotating shaft (306).

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