Unmanned aerial vehicle performance test system and test method thereof

Abstract

The invention discloses an unmanned aerial vehicle performance test system and a test method thereof, relates to the technical field of unmanned aerial vehicle performance test, and solves the problems that when the unmanned aerial vehicle performance test system tests the takeoff stability and tension of an unmanned aerial vehicle, the influence of wind power and wind direction on the takeoff of the unmanned aerial vehicle is difficult to simulate, and the takeoff stability of the unmanned aerial vehicle is difficult to measure. The unmanned aerial vehicle performance test system comprises a base, and a test mechanism is arranged at the top end of the base. A servo motor is started through a console, the servo motor drives a rotating shaft to rotate, then a fan is driven to rotate, and a wind simulation mechanism blows wind to the unmanned aerial vehicle, so that the takeoff stability of the unmanned aerial vehicle under the condition of wind action is simulated, and a sliding plate can be moved on the surface of a circular track to simulate the takeoff stability of the unmanned aerial vehicle. The sliding plate drives the wind simulation mechanism to move to any angle position on the outer side of the unmanned aerial vehicle to simulate conditions of different wind directions, so that the take-off performance of the unmanned aerial vehicle is conveniently tested.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicle performance testing, and in particular to a unmanned aerial vehicle performance testing system and a testing method thereof. Background Art

[0002] A drone is an unmanned aircraft controlled by radio remote control equipment and self-contained program control devices, or operated completely or intermittently autonomously by an onboard computer;

[0003] During actual use, drones need to be tested and experimented with to obtain test parameters and characteristics and verify reliability.

[0004] The existing UAV performance test system has difficulty simulating the impact of wind force and wind direction on the takeoff of the UAV when testing the takeoff stability and pulling force of the UAV, and the stability of the UAV during takeoff is difficult to measure; therefore, it does not meet the existing needs. In this regard, we propose a UAV performance test system and its test method. Summary of the invention

[0005] The purpose of the present invention is to provide a UAV performance test system and a test method thereof, so as to solve the problems proposed in the above background technology that the UAV performance test system is difficult to simulate the influence of wind force and wind direction on the UAV take-off when testing the UAV take-off stability and pulling force, and the stability of the UAV during take-off is difficult to measure.

[0006] To achieve the above object, the present invention provides the following technical solution: a UAV performance test system, comprising a base, a testing mechanism is provided at the top of the base, a moving mechanism is provided on the outside of the base, two wind simulation mechanisms are provided at the top of the moving mechanism, and a UAV is provided at the top of the testing mechanism;

[0007] The testing mechanism includes a testing platform, a pulling platform, a movable rod, a spring groove, a compression spring, an extrusion plate, an upper pressure sensor and a lower pressure sensor. The testing platform is movably installed at the upper position of the base, the pulling platform is movably installed at the top of the testing platform, and four movable rods are fixedly installed at the bottom of the pulling platform. The top surface of the testing platform is provided with four spring grooves, and the movable rods are slidably inserted into the inside of the spring grooves. The top of the inner wall of the spring groove is provided with an upper pressure sensor, and the bottom of the inner wall of the spring groove is provided with a lower pressure sensor. The bottom end of the movable rod is fitted with the top surface of the lower pressure sensor, and the outer surface of the movable rod is movably installed with a compression spring, and the top of the compression spring is fixedly installed with an extrusion plate, and the top of the extrusion plate is fitted with the bottom surface of the upper pressure sensor.

[0008] Preferably, the testing mechanism also includes a UAV positioning plate, a pull rope, a first electric push rod and a telescopic rod. The telescopic rod is fixedly installed on the bottom end of the testing platform. The bottom end of the telescopic rod is provided with a first electric push rod. The output end of the first electric push rod is fixedly connected to the bottom end of the telescopic rod. The top of the pulling platform and the position corresponding to the spring groove are both fixedly installed with a UAV positioning plate. A pull rope is provided at the center of the top of the pulling platform, and the end of the pull rope is connected to the bottom end of the UAV through a hook.

[0009] Preferably, the moving mechanism includes a circular track, a sliding plate, a pulley, a second electric push rod and a lifting rod, two sliding plates are slidably installed on the top end of the circular track, four pulleys are provided at the bottom end of the sliding plate, and the pulleys are both in contact with the two side surfaces of the circular track, the top end of the sliding plate is connected to the second electric push rod by bolts, and the output end of the second electric push rod is fixedly connected to the lifting rod.

[0010] Preferably, the wind simulation mechanism includes a fixed box, a vent, a servo motor, a rotating shaft, a fan and a fixed bracket, the fixed box is fixedly installed on the top surface of the lifting rod, vents are provided on both side surfaces of the fixed box, a servo motor is provided inside the fixed box, the side of the servo motor close to the drone is the output end, the output end of the servo motor is connected to the rotating shaft through a coupling, a plurality of fans are fixedly installed on the outer surface of the rotating shaft, a fixed bracket is fixedly installed on the other side of the servo motor, and the other end of the fixed bracket is fixedly connected to the surface of the vent.

[0011] Preferably, two UAV legs are fixedly mounted on the bottom surface of the UAV, and two positioning pads are provided at the bottom ends of the UAV legs, and the positioning pads correspond to the positions of the UAV positioning plate.

[0012] Preferably, the first electric push rod is fixedly installed at the center of the base, and the weight of the test platform is greater than the pulling force of the drone.

[0013] Preferably, the pulling platform is made of PVC plastic, and the weight of the pulling platform is less than the pulling force of the drone.

[0014] Preferably, a plurality of support plates are fixedly mounted on the bottom end of the base.

[0015] Preferably, a control console is provided on the outside of the moving mechanism, the first electric push rod, the second electric push rod and the servo motor are all electrically connected to the control console through wires, and the upper pressure sensor and the lower pressure sensor are both electrically connected to the control console.

[0016] A method for testing a drone performance test system, the method comprising the following steps:

[0017] Step A: First check and record the pressure of the pressure sensor through the console, then place the drone on the surface of the pulling platform, and check and record the pressure of the pressure sensor after placing the drone through the console again, then connect the pull rope to the bottom of the drone through the hook, so that the drone is restricted by the pull rope to prevent the drone from flying out. At the same time, the drone can be pulled upward by pulling the pull rope, so as to facilitate the testing of the pulling force of the drone;

[0018] Step B: After the drone legs at the bottom of the drone are aligned with the positions of the drone positioning plate, the drone is placed on the surface of the drone positioning plate. At this time, the first electric push rod is controlled to start, so that the first electric push rod drives the telescopic rod to be pushed out, so that the test platform drives the drone to rise and fall, and then adjusts the take-off level of the drone, so that the device can detect the performance status of the drone at different take-off level heights when taking off;

[0019] Step C: When the drone takes off, the pulling platform will be pulled upward by pulling the rope. At this time, the pulling platform will drive the movable rod to rise synchronously, so that the movable rod squeezes the compression spring and contracts the compression spring. At this time, the elastic potential energy of the compression spring will be released to the squeezing plate, so that the squeezing plate squeezes in the direction of the upper pressure sensor, and then the upper pressure sensor is stressed. At the same time, due to the rise of the movable rod, the force on the lower pressure sensor is released, so that the device can judge the take-off pulling force of the drone by the pressure on the upper pressure sensor, and can judge whether the chassis of the drone is stable when taking off according to whether the time when the pressure counts of the four lower pressure sensors decrease is synchronized, and detect whether the drone takes off vertically upward and whether it is skewed;

[0020] Step D: When testing the drone, the servo motor can be started through the console to drive the rotating shaft to rotate, thereby driving the fan to rotate, so that the wind simulation mechanism blows wind in the direction of the drone, thereby simulating the stability of the drone taking off under the action of wind. The sliding plate can be moved on the surface of the circular track so that the sliding plate drives the wind simulation mechanism to move to any angle position outside the drone to simulate different wind directions, which is convenient for testing the take-off performance of the drone.

[0021] Step E: When simulating wind conditions through the wind simulation mechanism, the second electric push rod can also be started through the console to drive the lifting rod to push out, thereby changing the height position of the wind simulation mechanism, thereby simulating the impact of different wind heights on the take-off of the drone.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. The present invention cooperates with the moving mechanism and the wind simulation mechanism so that when the device is testing the drone, the servo motor can be started through the console to drive the rotating shaft to rotate, thereby driving the fan to rotate, so that the wind simulation mechanism blows wind in the direction of the drone, thereby simulating the stability of the drone taking off under the action of wind. The sliding plate can be moved on the surface of the circular track so that the sliding plate drives the wind simulation mechanism to move to any angle position outside the drone to simulate different wind directions, which is convenient for testing the take-off performance of the drone.

[0024] 2. The present invention cooperates with the upper pressure sensor and the lower pressure sensor. When the drone takes off, the pull rope will pull the pulling platform upward. At this time, the pulling platform will drive the movable rod to rise synchronously, thereby causing the movable rod to squeeze the compression spring and shrink the compression spring. At this time, the elastic potential energy of the compression spring will be released toward the squeezing plate, thereby squeezing the squeezing plate in the direction of the upper pressure sensor, thereby causing the upper pressure sensor to be subjected to force. At the same time, due to the rise of the movable rod, the force on the lower pressure sensor is released, so that the device can judge the take-off pulling force of the drone by the pressure on the upper pressure sensor, and can judge whether the chassis of the drone is stable when taking off according to whether the time when the pressure counts of the four lower pressure sensors decrease is synchronized, and detect whether the drone takes off vertically upward and whether it is skewed. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0026] Figure 2 It is a structural schematic diagram of the test platform of the present invention;

[0027] Figure 3 A cross-sectional front view of the present invention as a whole;

[0028] Figure 4 It is a cross-sectional front view of the position of the positioning plate of the UAV of the present invention;

[0029] Figure 5 It is a cross-sectional front view of the test platform of the present invention when it is retracted;

[0030] Figure 6 For the present invention Figure 4 Schematic diagram of the local structure of part A.

[0031] In the figure: 1. base; 2. test mechanism; 201. test platform; 202. pulling platform; 203. drone positioning plate; 204. pull rope; 205. first electric push rod; 206. telescopic rod; 207. movable rod; 208. spring groove; 209. compression spring; 210. extrusion plate; 211. upper pressure sensor; 212. lower pressure sensor; 3. moving mechanism; 301. circular track; 302. sliding plate; 303. pulley; 304. second electric push rod; 305. lifting rod; 4. wind simulation mechanism; 401. fixed box; 402. vent; 403. servo motor; 404. rotating shaft; 405. fan; 406. fixed bracket; 5. drone; 6. drone leg; 7. support plate. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present invention will be described clearly and completely below 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.

[0033] See also Figures 1 to 6 , an embodiment of the present invention: a drone performance test system, comprising a base 1, a test mechanism 2 is provided at the top of the base 1, a moving mechanism 3 is provided on the outer side of the base 1, two wind simulation mechanisms 4 are provided at the top of the moving mechanism 3, and a drone 5 is provided at the top of the test mechanism 2;

[0034] The test mechanism 2 includes a test platform 201, a pulling platform 202, a movable rod 207, a spring groove 208, a compression spring 209, an extrusion plate 210, an upper pressure sensor 211 and a lower pressure sensor 212. The test platform 201 is movably installed at the upper position of the base 1. The pulling platform 202 is movably installed on the top of the test platform 201. Four movable rods 207 are fixedly installed on the bottom of the pulling platform 202. Four spring grooves 208 are provided on the top surface of the test platform 201. The movable rods 207 are provided on the bottom surface of the pulling platform 202. 207 are slidably inserted into the interior of the spring groove 208, the top of the inner wall of the spring groove 208 is provided with an upper pressure sensor 211, the bottom of the inner wall of the spring groove 208 is provided with a lower pressure sensor 212, the bottom end of the movable rod 207 is in contact with the top surface of the lower pressure sensor 212, and the outer surface of the movable rod 207 is movably installed with a compression spring 209, and the top of the compression spring 209 is fixedly installed with an extrusion plate 210, and the top of the extrusion plate 210 is in contact with the bottom surface of the upper pressure sensor 211.

[0035] The testing mechanism 2 also includes a UAV positioning plate 203, a pull rope 204, a first electric push rod 205 and a telescopic rod 206. The telescopic rod 206 is fixedly installed at the bottom end of the testing platform 201. The bottom end of the telescopic rod 206 is provided with a first electric push rod 205. The output end of the first electric push rod 205 is fixedly connected to the bottom end of the telescopic rod 206. The UAV positioning plate 203 is fixedly installed at the top of the pulling platform 202 and the position corresponding to the spring groove 208. A pull rope 204 is provided at the center of the top of the pulling platform 202, and the end of the pull rope 204 is connected to the bottom end of the UAV 5 through a hook.

[0036] Through the cooperation of the upper pressure sensor 211 and the lower pressure sensor 212, when the UAV 5 takes off, the pull rope 204 will pull the pulling platform 202 upward, and at this time, the pulling platform 202 will drive the movable rod 207 to rise synchronously, thereby causing the movable rod 207 to squeeze the compression spring 209, causing the compression spring 209 to shrink. At this time, the elastic potential energy of the compression spring 209 will be released toward the squeezing plate 210, thereby squeezing the squeezing plate 210 in the direction of the upper pressure sensor 211, thereby causing the upper pressure sensor 211 to be stressed. At the same time, due to the rise of the movable rod 207, the force on the lower pressure sensor 212 is released, so that the device can judge the take-off pulling force of the UAV 5 through the pressure on the upper pressure sensor 211, and can judge whether the chassis of the UAV 5 is stable when taking off according to whether the time when the pressure counts of the four lower pressure sensors 212 decrease is synchronized, and detect whether the UAV 5 takes off vertically upwards and whether it is skewed.

[0037] The moving mechanism 3 includes a circular track 301, a sliding plate 302, a pulley 303, a second electric push rod 304 and a lifting rod 305. Two sliding plates 302 are slidably installed on the top of the circular track 301, and four pulleys 303 are provided at the bottom of the sliding plate 302. The pulleys 303 are both in contact with the two side surfaces of the circular track 301. The top of the sliding plate 302 is connected to the second electric push rod 304 by bolts, and the output end of the second electric push rod 304 is fixedly connected to the lifting rod 305.

[0038] Through the cooperation of the moving mechanism 3 and the wind simulation mechanism 4, when the device is testing the drone 5, the servo motor 403 can be started through the console, so that the servo motor 403 drives the rotating shaft 404 to rotate, and then drives the fan 405 to rotate, so that the wind simulation mechanism 4 blows wind in the direction of the drone 5, thereby simulating the stability of the drone 5 taking off under the action of wind. The sliding plate 302 can be moved on the surface of the circular track 301, so that the sliding plate 302 drives the wind simulation mechanism 4 to move to any angle position outside the drone 5, so as to simulate different wind directions, which is convenient for testing the take-off performance of the drone 5.

[0039] The wind simulation mechanism 4 includes a fixed box 401, a vent 402, a servo motor 403, a rotating shaft 404, a fan 405 and a fixed bracket 406. The fixed box 401 is fixedly installed on the top surface of the lifting rod 305. Ventilation holes 402 are arranged on both side surfaces of the fixed box 401. Servo motors 403 are arranged inside the fixed box 401. The side of the servo motor 403 close to the drone 5 is the output end. The output end of the servo motor 403 is connected to the rotating shaft 404 through a coupling. Multiple fans 405 are fixedly installed on the outer surface of the rotating shaft 404. A fixed bracket 406 is fixedly installed on the other side of the servo motor 403. The other end of the fixed bracket 406 is fixedly connected to the surface of the vent 402.

[0040] Through the cooperation between the second electric push rod 304 and the lifting rod 305, the device can start the second electric push rod 304 through the console, so that the second electric push rod 304 drives the lifting rod 305 to be pushed out, thereby changing the height position of the wind simulation mechanism 4, and then simulating the influence of different wind heights on the take-off of the drone 5.

[0041] Two drone legs 6 are fixedly mounted on the bottom surface of the drone 5 , and two positioning pads are arranged at the bottom of each of the drone legs 6 , and the positioning pads correspond to the positions of the drone positioning plate 203 .

[0042] The first electric push rod 205 is fixedly installed at the center of the base 1 , and the weight of the test platform 201 is greater than the pulling force of the drone 5 .

[0043] The pulling platform 202 is made of PVC plastic, and the weight of the pulling platform 202 is less than the pulling force of the drone 5 .

[0044] A plurality of support plates 7 are fixedly mounted on the bottom end of the base 1 .

[0045] A control console is provided outside the moving mechanism 3 , and the first electric push rod 205 , the second electric push rod 304 and the servo motor 403 are all electrically connected to the control console through wires, and the upper pressure sensor 211 and the lower pressure sensor 212 are both electrically connected to the control console.

[0046] A test method for a drone performance test system, the test method comprising the following steps:

[0047] Step A: First, check and record the pressure of the pressure sensor 212 through the console, then place the drone 5 on the surface of the pulling platform 202, and check and record the pressure of the pressure sensor 212 after placing the drone 5 through the console again, then connect the pull rope 204 to the bottom of the drone 5 through a hook, so that the drone 5 is restricted by the pull rope 204 to prevent the drone 5 from flying out, and at the same time, the drone 5 can pull the pulling platform 202 upward by pulling the pull rope 204, so as to facilitate the testing of the pulling force of the drone 5;

[0048] Step B: After the drone legs 6 at the bottom of the drone 5 are aligned with the positions of the drone positioning plate 203, the drone 5 is placed on the surface of the drone positioning plate 203. At this time, the first electric push rod 205 is controlled to start, so that the first electric push rod 205 drives the telescopic rod 206 to be pushed out, so that the test platform 201 drives the drone 5 to rise and fall, and then adjusts the take-off horizontal plane height of the drone 5, so that the device can detect the performance status of the drone 5 at different take-off horizontal plane heights when taking off;

[0049] Step C: When the UAV 5 takes off, the pulling platform 202 is pulled upward by the pull rope 204. At this time, the pulling platform 202 will drive the movable rod 207 to rise synchronously, thereby causing the movable rod 207 to squeeze the compression spring 209 and shrink the compression spring 209. At this time, the elastic potential energy of the compression spring 209 will be released to the squeezing plate 210, thereby squeezing the squeezing plate 210 in the direction of the upper pressure sensor 211, thereby causing the upper pressure sensor 211 to be stressed. At the same time, due to the rise of the movable rod 207, the force on the lower pressure sensor 212 is released, so that the device can judge the take-off pulling force of the UAV 5 by the pressure on the upper pressure sensor 211. At the same time, it can judge whether the chassis of the UAV 5 is stable when taking off according to whether the time when the pressure counts of the four lower pressure sensors 212 decrease is synchronized, and detect whether the UAV 5 takes off vertically upwards and whether it is skewed;

[0050] Step D: When testing the drone 5, the servo motor 403 can be started through the console, so that the servo motor 403 drives the rotating shaft 404 to rotate, thereby driving the fan 405 to rotate, so that the wind simulation mechanism 4 blows wind in the direction of the drone 5, thereby simulating the stability of the drone 5 taking off under the action of wind. In addition, the sliding plate 302 can be moved on the surface of the circular track 301, so that the sliding plate 302 drives the wind simulation mechanism 4 to move to any angle position outside the drone 5, so as to simulate different wind directions, which is convenient for testing the take-off performance of the drone 5;

[0051] Step E: When simulating wind conditions through the wind simulation mechanism 4, the second electric push rod 304 can also be started through the console to drive the lifting rod 305 to be pushed out, thereby changing the height position of the wind simulation mechanism 4, and then simulating the impact of different wind heights on the take-off of the drone 5.

[0052] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

Claims

1. A drone performance test system, comprising a base (1), characterized in that: A testing mechanism (2) is provided at the top of the base (1), a moving mechanism (3) is provided on the outside of the base (1), two wind simulation mechanisms (4) are provided at the top of the moving mechanism (3), and a drone (5) is provided at the top of the testing mechanism (2); The testing mechanism (2) comprises a testing platform (201), a pulling platform (202), a movable rod (207), a spring groove (208), a compression spring (209), an extrusion plate (210), an upper pressure sensor (211) and a lower pressure sensor (212); the testing platform (201) is movably mounted above the base (1); the pulling platform (202) is movably mounted on the top of the testing platform (201); four movable rods (207) are fixedly mounted on the bottom of the pulling platform (202); four spring grooves (208) are provided on the top surface of the testing platform (201); The movable rods (207) are all slidably inserted into the interior of the spring grooves (208); the top ends of the inner walls of the spring grooves (208) are provided with upper pressure sensors (211); the bottom ends of the inner walls of the spring grooves (208) are provided with lower pressure sensors (212); the bottom ends of the movable rods (207) are in contact with the top end surfaces of the lower pressure sensors (212); a compression spring (209) is movably installed on the outer surface of the movable rods (207); an extrusion plate (210) is fixedly installed on the top end of the compression springs (209); the top end of the extrusion plate (210) is in contact with the bottom end surfaces of the upper pressure sensors (211).

2. The UAV performance testing system according to claim 1, characterized in that: The testing mechanism (2) further comprises a drone positioning plate (203), a pull rope (204), a first electric push rod (205) and a telescopic rod (206); the telescopic rod (206) is fixedly mounted at the bottom end of the testing platform (201); the first electric push rod (205) is disposed at the bottom end of the telescopic rod (206); the output end of the first electric push rod (205) is fixedly connected to the bottom end of the telescopic rod (206); the drone positioning plate (203) is fixedly mounted at the top end of the pulling platform (202) and at a position corresponding to the spring groove (208); a pull rope (204) is disposed at the center of the top end of the pulling platform (202); the end of the pull rope (204) is connected to the bottom end of the drone (5) via a hook.

3. The unmanned aerial vehicle performance testing system according to claim 2, characterized in that: The moving mechanism (3) comprises a circular track (301), a sliding plate (302), a pulley (303), a second electric push rod (304) and a lifting rod (305); two sliding plates (302) are slidably mounted on the top of the circular track (301); four pulleys (303) are arranged at the bottom of the sliding plates (302); the pulleys (303) are both in contact with the surfaces of both sides of the circular track (301); the top of the sliding plates (302) are both connected to the second electric push rod (304) by bolts; the output end of the second electric push rod (304) is fixedly connected to the lifting rod (305).

4. The UAV performance testing system according to claim 3, characterized in that: The wind simulation mechanism (4) comprises a fixed box (401), a vent (402), a servo motor (403), a rotating shaft (404), a fan (405) and a fixed bracket (406); the fixed box (401) is fixedly mounted on the top surface of the lifting rod (305); both sides of the fixed box (401) are provided with vents (402); the interior of the fixed box (401) is provided with a servo motor (403); the side of the servo motor (403) close to the drone (5) is an output end; the output end of the servo motor (403) is connected to the rotating shaft (404) via a coupling; a plurality of fans (405) are fixedly mounted on the outer surface of the rotating shaft (404); the other side of the servo motor (403) is fixedly mounted with a fixed bracket (406); the other end of the fixed bracket (406) is fixedly connected to the surface of the vent (402).

5. The unmanned aerial vehicle performance testing system according to claim 2, characterized in that: Two drone legs (6) are fixedly mounted on the bottom surface of the drone (5), and two positioning pads are provided at the bottom ends of the drone legs (6), and the positioning pads correspond to the positions of the drone positioning plate (203).

6. The unmanned aerial vehicle performance testing system according to claim 2, characterized in that: The first electric push rod (205) is fixedly mounted at the center of the base (1), and the weight of the test platform (201) is greater than the pulling force of the drone (5).

7. The unmanned aerial vehicle performance testing system according to claim 2, characterized in that: The pulling platform (202) is made of PVC plastic, and the weight of the pulling platform (202) is less than the pulling force of the drone (5).

8. The unmanned aerial vehicle performance testing system according to claim 1, characterized in that: A plurality of support plates (7) are fixedly mounted on the bottom end of the base (1).

9. The unmanned aerial vehicle performance testing system according to claim 4, characterized in that: A control console is provided on the outside of the moving mechanism (3); the first electric push rod (205), the second electric push rod (304) and the servo motor (403) are all electrically connected to the control console via wires; and the upper pressure sensor (211) and the lower pressure sensor (212) are both electrically connected to the control console.

10. A method for testing a UAV performance test system according to any one of claims 1 to 9, characterized in that: The test method comprises the following steps: Step A: first, the pressure of the pressure sensor (212) is checked and recorded through the control console, then the drone (5) is placed on the surface of the pulling platform (202), and the pressure of the pressure sensor (212) after the drone (5) is placed is checked and recorded again through the control console, and then the pull rope (204) is connected to the bottom end of the drone (5) through a hook, so that the drone (5) is restricted by the pull rope (204) to prevent the drone (5) from flying out, and at the same time, the drone (5) can pull the pulling platform (202) upward by pulling the pull rope (204), thereby facilitating the testing of the pulling force of the drone (5); Step B: After the drone legs (6) at the bottom of the drone (5) are aligned with the positions of the drone positioning plate (203), the drone (5) is placed on the surface of the drone positioning plate (203). At this time, the first electric push rod (205) is controlled to start, so that the first electric push rod (205) drives the telescopic rod (206) to be pushed out, so that the test platform (201) drives the drone (5) to rise and fall, and then adjusts the take-off level of the drone (5), so that the device can detect the performance status of the drone (5) at different take-off level heights when taking off; Step C: When the drone (5) takes off, the pulling platform (202) is pulled upward by the pulling rope (204). At this time, the pulling platform (202) drives the movable rod (207) to rise synchronously, thereby causing the movable rod (207) to squeeze the compression spring (209) and shrink the compression spring (209). At this time, the elastic potential energy of the compression spring (209) is released toward the squeezing plate (210), thereby causing the squeezing plate (210) to squeeze in the direction of the upper pressure sensor (211), thereby causing the upper pressure sensor (211) to be stressed. At the same time, due to the rise of the movable rod (207), the stress on the lower pressure sensor (212) is released, so that the device can judge the take-off pulling force of the drone (5) by the pressure on the upper pressure sensor (211). At the same time, it can judge whether the chassis of the drone (5) is stable when taking off according to whether the time when the pressure counts of the four lower pressure sensors (212) decrease synchronously, and detect whether the drone (5) takes off vertically upward and whether it is skewed; Step D: When testing the drone (5), the servo motor (403) can be started through the control console, so that the servo motor (403) drives the rotating shaft (404) to rotate, thereby driving the fan (405) to rotate, so that the wind simulation mechanism (4) blows wind in the direction of the drone (5), thereby simulating the stability of the drone (5) taking off under the action of wind. In addition, the sliding plate (302) can be moved on the surface of the circular track (301), so that the sliding plate (302) drives the wind simulation mechanism (4) to move to any angle position outside the drone (5), so as to simulate different wind directions, thereby facilitating the test of the take-off performance of the drone (5); Step E: When simulating the wind force through the wind simulation mechanism (4), the second electric push rod (304) can also be started through the control console to drive the lifting rod (305) to be pushed out, thereby changing the height position of the wind simulation mechanism (4), thereby simulating the influence of different wind heights on the take-off of the drone (5).

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