A UAV test system

Abstract

The present invention belongs to the field of drones, and provides a drone testing system, including a testing device and a processing module, wherein the testing device includes a test bench, on which a torque testing module is installed, and the torque testing module is used to test the torque when the drone turns, and a tension testing module is installed on the torque testing module, and the tension testing module is used to test the vertical tension and tilt tension of the drone. The present invention sets a tension sensor, an angle sensor, a winding drum, a pull rope, and a second motor, and when testing the tilt tension of the drone, the drone is tilted to fly, and the drone tilts and pulls the pull rope, the tension sensor can measure the vertical tension of the pull rope, the angle sensor can detect the tilt angle of the pull rope, and then the tension of the pull rope and its horizontal tension component can be calculated, and the system can comprehensively and accurately test the tension parameters of the drone when it is tilted.

Description

Technical Field

[0001] The invention belongs to the field of unmanned aerial vehicles, and in particular relates to a unmanned aerial vehicle testing system. Background Art

[0002] With the rapid development of science and technology, the application of drones in various industries has become increasingly extensive in recent years. At this stage, the application of drones has involved aerial photography, agricultural and forestry plant protection, geological exploration, power inspection, oil and gas pipeline inspection, highway accident management, forest fire inspection, pollution environment investigation, emergency rescue and relief, disaster relief and coastline inspection.

[0003] In the prior art, during the development of a drone, a series of functional parameters of the drone need to be tested so that the drone can achieve its intended functions.

[0004] When conducting torque and tension tests on drones, the general method is to fix the drone on a test bench and make it turn in order to test its steering torque, or to make the drone rise and fall vertically in order to test its vertical tension. However, in actual applications, drones not only need to fly vertically, but also need to fly at an angle. The existing testing equipment can only test the vertical tension of drones, and it is impossible to fully understand the flight parameters of drones. Summary of the invention

[0005] The purpose of the present invention is to provide a drone testing system, aiming to solve the technical problem in the prior art that the pulling force of a drone during tilted flight cannot be accurately tested.

[0006] The present invention is implemented as follows: a drone testing system includes a testing device and a processing module, the testing device includes a test bench, a torque testing module is installed on the test bench, the torque testing module is used to test the torque when the drone turns, a tension testing module is installed on the torque testing module, the tension testing module is used to test the vertical tension and tilt tension of the drone, the output end of the tension testing module is connected to a bearing plate, the torque testing module and the tension testing module are both electrically connected to the processing module, the processing module is used to process the data measured by the torque testing module and the tension testing module, a clamping mechanism is installed on the bearing plate, the clamping mechanism is used to fix the drone, so that the drone can be connected to the tension testing module, which is convenient for the tension testing module to test the drone, a positioning column is fixedly connected to the torque testing module, a positioning hole adapted to the positioning column is opened on the bearing plate, the positioning column can be plugged into the positioning hole, when the positioning column is inserted into the positioning hole, the bearing plate and the torque testing module are relatively fixed on the horizontal plane, so that the torque testing module can test the torque when the drone turns.

[0007] Further technical solution: the torque testing module includes an outer turntable, which is rotatably connected to the test bench, on which a torque sensor is fixedly installed, the input end of the torque sensor is fixedly connected to the outer turntable, and the processing module is electrically connected to the torque sensor.

[0008] Further technical solution: the tension testing module includes a accommodating cylinder, which is rotatably connected to the outer turntable, a tension sensor is fixedly installed inside the outer turntable, the input end of the tension sensor is fixedly connected to a mounting plate, the processing module is electrically connected to the tension sensor, the top of the mounting plate is fixedly connected to a vertical plate, a winding disk is rotatably connected to the vertical plate, a pull rope is wound on the winding disk, a second motor is fixedly installed on the side of the vertical plate, the output shaft of the second motor is fixedly connected to the side of the winding disk, and one end of the pull rope is connected to the bottom of the supporting plate.

[0009] Further technical solution: The tension testing module also includes a rotating column, which is rotatably connected to the bottom of the supporting plate, and an angle sensor is fixedly installed on the rotating column. The input end of the angle sensor is fixedly connected to a measuring wheel, one end of the pull rope is fixedly connected to the measuring wheel, and the angle sensor and the processing module are electrically connected.

[0010] Further technical solution: the clamping mechanism includes a placement plate, the placement plate is fixedly mounted on the top of the carrying plate, first slide grooves are provided on both sides of the top of the placement plate, adjustment blocks are slidably connected inside the two first slide grooves, a second slide groove is provided on the top of the adjustment block, two sliders are slidably connected inside the second slide groove, a lifting column is vertically slidably connected to the slider, a clamping limit rod is fixedly connected to the top of the lifting column, the clamping limit rod is L-shaped, an inclined surface is provided at one end of the clamping limit rod close to the middle of the placement plate, so as to facilitate sliding the legs of the drone under the clamping limit rod, and a tension spring is connected between the lifting column and the slider;

[0011] In order to make the two adjustment blocks move toward or away from each other and then fix the drone, a first double-headed screw is rotatably connected to the placement plate, and the two adjustment blocks are respectively threadedly connected to the two ends of the first double-headed screw. In order to drive the two sliders to move, a second double-headed screw is rotatably connected to the adjustment block, and the two sliders are respectively threadedly connected to the two ends of the second double-headed screw. For ease of operation, one end of the second double-headed screw extends out of the placement plate, and the placement plate is provided with a movable hole for the movement of the second double-headed screw.

[0012] Further technical solution: multiple limiting mechanisms are also provided, one end of each of the limiting mechanisms is respectively installed on a plurality of clamping limiting rods, and the other end of each of the limiting mechanisms is installed on a slider. When the clamping limiting rods clamp the legs of the drone, the limiting mechanisms are used to relatively fix the clamping limiting rods and the slider, thereby limiting the legs of the drone on the slider, avoiding excessive gaps between the clamping limiting rods and the legs of the drone, and improving the stability of the drone.

[0013] Further technical solution: the limit mechanism includes a receiving groove opened on the side of the clamping limit rod away from the middle part of the second double-headed screw rod, the storage groove is slidably connected with an extrusion strip inside the storage groove, a first compression spring is connected between the extrusion strip and the side wall of the storage groove, a storage cavity is opened inside the extrusion strip, a stopper is slidably connected inside the storage cavity, a second compression spring is connected between the stopper and the side wall of the storage cavity away from the middle part of the adjusting block, the stopper is fixedly connected to the side of the stopper close to the middle part of the adjusting block, the limit rod passes through the extrusion strip and the clamping limit rod, and the clamping limit rod is provided with a fine hole for the limit rod to move. Initially, one end of the limit rod does not extend out of the clamping limit rod, and a limit plate is fixedly connected to the adjusting block, and a plurality of equidistant limit grooves are opened on the side of the limit plate close to the limit rod.

[0014] Further technical solution: A wind simulation module is also provided, and the wind simulation module is used to simulate a strong wind environment.

[0015] Further technical solution: The wind simulation module includes an annular turntable, which is installed on a test bench. The top of the annular turntable is fixedly connected with an arc-shaped wind gathering plate, and a fan is installed on the arc-shaped wind gathering plate.

[0016] Further technical solution: The annular turntable is rotatably mounted on the test bench, so that the fan can blow air in any direction of the UAV, and the performance of the UAV in a variable wind environment can be tested;

[0017] In order to drive the fan to move, the wind simulation module also includes a mounting frame and a first motor. The mounting frame is fixedly connected to the test bench, the first motor is fixedly installed on the mounting frame, the output shaft of the first motor is fixedly connected to a gear, the annular turntable is fixedly connected to a gear ring, and the gear and the gear ring are meshingly connected.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. The present invention sets a tension sensor, an angle sensor, a winding drum, a pull rope and a second motor. When testing the tilt tension of the drone, the drone is tilted to fly. The drone tilts and pulls the pull rope. The tension sensor can measure the vertical tension of the pull rope, and the angle sensor can detect the tilt angle of the pull rope. Then, the tension of the pull rope and its horizontal tension component can be calculated. The system can comprehensively and accurately test the tension parameters of the drone when it is tilted.

[0020] 2. The present invention provides a positioning column and a positioning hole, inserts the positioning column into the positioning hole, and makes the UAV turn, so that the torque sensor can test the steering torque of the UAV;

[0021] 3. The present invention provides a clamping mechanism and a limiting mechanism. After the clamping mechanism fixes the UAV, the limiting mechanism limits the clamping mechanism itself, so that the UAV can be fixed more firmly, preventing the UAV from escaping from the clamping mechanism, and the clamping mechanism can fix UAVs of different models;

[0022] 4. The present invention sets a wind simulation module. During the test, the wind turbine blows wind toward the UAV, so as to test the stability and wind resistance of the UAV in strong winds.

[0023] 5. During the test, the first motor drives the gear to rotate, the gear drives the gear ring and the annular turntable to rotate, and the annular turntable drives the fan to rotate. The fan can blow air in different directions of the UAV, simulating a strong wind environment with changing directions, making it closer to natural conditions, thereby making the test results of the UAV more accurate. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the overall structure of the present invention when testing torque.

[0025] Figure 2 It is a schematic diagram of the overall structure of the present invention when testing tension.

[0026] Figure 3 This is a schematic diagram of the installation structure of the tensile test module in the present invention.

[0027] Figure 4 For the present invention Figure 3 Enlarged schematic diagram at point A in the middle.

[0028] Figure 5 It is a structural schematic diagram of the clamping mechanism in the present invention.

[0029] Figure 6 For the present invention Figure 5 Enlarged schematic diagram of point B in the middle.

[0030] Figure 7 It is a structural schematic diagram of the installation of the limiting mechanism in the present invention.

[0031] Figure 8 It is a schematic structural diagram of the clamping limit rod in the present invention.

[0032] In the attached drawings: 1. test bench; 2. external turntable; 3. torque sensor; 4. bearing plate; 5. clamping mechanism; 51. placement plate; 52. first double-headed screw; 53. first slide slot; 54. adjustment block; 55. second double-headed screw; 56. second slide slot; 57. slider; 58. clamping limit rod; 59. movable hole; 510. lifting column; 511. tension spring; 6. wind simulation module; 61. fan; 62. arc-shaped wind gathering plate; 63. annular turntable; 64. gear ring; 65. mounting frame; 66. first motor; 67. Gear; 7. Positioning column; 8. Tension test module; 81. Rotating column; 82. Measuring wheel; 83. Angle sensor; 84. Pull rope; 85. Accommodating cylinder; 86. Mounting plate; 87. Second motor; 88. Vertical plate; 89. Winding reel; 810. Tension sensor; 9. Limiting mechanism; 91. Limiting groove; 92. Limiting plate; 93. Limiting rod; 94. First compression spring; 95. Stopper; 96. Storage groove; 97. Storage cavity; 98. Second compression spring; 99. Extrusion strip; 10. Positioning hole; 11. UAV. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0034] The specific implementation of the present invention is described in detail below in conjunction with specific embodiments.

[0035] like Figure 1-Figure 8As shown, a UAV test system provided by the present invention includes a test device and a processing module (not shown), wherein the test device includes a test bench 1, on which a torque test module is installed, and the torque test module is used to test the torque of the UAV 11 when turning, and a tension test module 8 is installed on the torque test module, and the tension test module 8 is used to test the vertical tension and tilt tension of the UAV 11, and the output end of the tension test module 8 is connected to a bearing plate 4, and the torque test module and the tension test module 8 are both electrically connected to the processing module, and the processing module is used to test the data measured by the torque test module and the tension test module 8. According to the processing, a clamping mechanism 5 is installed on the supporting plate 4, and the clamping mechanism 5 is used to fix the UAV 11, so that the UAV 11 can be connected to the tensile testing module 8, which is convenient for the tensile testing module 8 to test the UAV 11. A positioning column 7 is fixedly connected to the torque testing module, and a positioning hole 10 adapted to the positioning column 7 is opened on the supporting plate 4. The positioning column 7 can be plugged into the positioning hole 10. When the positioning column 7 is inserted into the positioning hole 10, the supporting plate 4 and the torque testing module are relatively fixed on the horizontal plane, so that the torque testing module can test the torque when the UAV 11 turns.

[0036] like Figure 1-Figure 3 As shown, a UAV test system provided by the present invention, in this embodiment, the torque test module includes an outer turntable 2, the outer turntable 2 is rotatably connected to the test bench 1, a torque sensor 3 is fixedly installed on the test bench 1, the input end of the torque sensor 3 is fixedly connected to the outer turntable 2, and the processing module and the torque sensor 3 are electrically connected.

[0037] like Figure 2-Figure 4 As shown, a UAV testing system provided by the present invention, in this embodiment, the tension testing module 8 includes a accommodating cylinder 85, the accommodating cylinder 85 is rotatably connected to the outer turntable 2, a tension sensor 810 is fixedly installed inside the outer turntable 2, the input end of the tension sensor 810 is fixedly connected to a mounting plate 86, the processing module is electrically connected to the tension sensor 810, the top of the mounting plate 86 is fixedly connected to a vertical plate 88, a winding drum 89 is rotatably connected to the vertical plate 88, a pull rope 84 is wound on the winding drum 89, a second motor 87 is fixedly installed on the side of the vertical plate 88, the output shaft of the second motor 87 is fixedly connected to the side of the winding drum 89, and one end of the pull rope 84 is connected to the bottom of the supporting plate 4.

[0038] The drone 11 is fixedly mounted on the clamping mechanism 5 to lift the drone 11. The drone 11 drives the carrying plate 4 to rise through the clamping mechanism 5. The carrying plate 4 pulls the winding drum 89 and the mounting plate 86 through the pull rope 84. The tension sensor 810 can measure the tension of the mounting plate 86. The tension plus the weight of the mounting plate 86, the second motor 87, the vertical plate 88, the winding drum 89, the pull rope 84, the carrying plate 4 and the clamping mechanism 5 can be used to obtain the lifting tension of the drone 11.

[0039] The second motor 87 drives the winding drum 89 to rotate, and the winding drum 89 pays out the pull rope 84 to make the drone 11 fly at an angle. The drone 11 drives the pull rope 84 to move, and the pull rope 84 is in an inclined state, so that the tilt tension of the drone 11 can be tested.

[0040] like Figure 3-Figure 4 As shown, a UAV testing system provided by the present invention is provided. When the UAV 11 is flying at an angle, the pull rope 84 is subjected to the tilting tension of the UAV 11. Since the tension sensor 810 is installed vertically, the detection direction of the tension sensor 810 is a single vertical direction, and it can only detect the tension in the vertical direction. However, the tension on the pull rope 84 has not only a vertical component, but also a horizontal component, which makes the detection result of the tension sensor 810 inaccurate. In this embodiment, the tension testing module 8 also includes a rotating column 81, which is rotatably connected to the bottom of the supporting plate 4, and an angle sensor 83 is fixedly installed on the rotating column 81. The input end of the angle sensor 83 is fixedly connected to a measuring wheel 82, one end of the pull rope 84 is fixedly connected to the measuring wheel 82, and the angle sensor 83 is electrically connected to the processing module.

[0041] When the drone 11 flies to other directions, the rotating column 81 will automatically change the direction of the measuring wheel 82 according to the deflection direction of the pull rope 84, so that the rotation angle of the measuring wheel 82 is the tilt angle of the pull rope 84, making the measurement result more accurate.

[0042] When the UAV 11 is flying at a tilt, the UAV 11 pulls the pull rope 84 to move. When the pull rope 84 is tilted, the pull rope 84 drives the measuring wheel 82 to rotate, causing the measuring wheel 82 to deflect by a certain angle. The angle sensor 83 can detect the deflection angle of the measuring wheel 82, and then measure the tilt angle of the pull rope 84. Then, the vertical and horizontal tension components of the pull rope 84 can be calculated. The value detected by the tension sensor 810 is the vertical tension component of the pull rope 84. Then, the tilt tension of the pull rope 84 and the horizontal component of the pull rope 84 can be inversely calculated, so that the tension of the UAV 11 during tilted flight can be comprehensively and accurately tested.

[0043] like Figure 5-Figure 8As shown, a UAV test system provided by the present invention is provided. In this embodiment, the clamping mechanism 5 includes a placement plate 51, and the placement plate 51 is fixedly installed on the top of the bearing plate 4. First slide grooves 53 are provided on both sides of the top of the placement plate 51. Adjustment blocks 54 are slidably connected inside the two first slide grooves 53. A second slide groove 56 is provided on the top of the adjustment block 54. Two sliders 57 are slidably connected inside the second slide groove 56. A lifting column 510 is vertically slidably connected to the slider 57. A clamping limit rod 58 is fixedly connected to the top of the lifting column 510. The clamping limit rod 58 is L-shaped. An inclined surface is provided at one end of the clamping limit rod 58 close to the middle of the placement plate 51, so as to facilitate sliding the legs of the UAV 11 under the clamping limit rod 58. A tension spring 511 is connected between the lifting column 510 and the slider 57.

[0044] In order to make the two adjustment blocks 54 move toward or away from each other and then fix the drone 11, a first double-headed screw 52 is rotatably connected to the placement plate 51, and the two adjustment blocks 54 are respectively threadedly connected to the two ends of the first double-headed screw 52. In order to drive the two sliders 57 to move, a second double-headed screw 55 is rotatably connected to the adjustment block 54, and the two sliders 57 are respectively threadedly connected to the two ends of the second double-headed screw 55. For ease of operation, one end of the second double-headed screw 55 extends out of the placement plate 51, and the placement plate 51 is provided with a movable hole 59 for the second double-headed screw 55 to move.

[0045] like Figure 7-Figure 8 As shown, a UAV testing system provided by the present invention is provided. Since the legs of different UAVs 11 are also different, in order to avoid the gap between the clamping limit rod 58 and the legs of the UAV 11 being too large and causing the UAV 11 to fall out, in this embodiment, a plurality of limit mechanisms 9 are further provided, one end of each of the limit mechanisms 9 is respectively mounted on a plurality of clamping limit rods 58, and the other end of each of the limit mechanisms 9 is mounted on a slider 57. When the clamping limit rod 58 clamps the legs of the UAV 11, the limit mechanism 9 is used to relatively fix the clamping limit rod 58 and the slider 57, thereby limiting the legs of the UAV 11 on the slider 57, avoiding the gap between the clamping limit rod 58 and the legs of the UAV 11 being too large, and improving the stability of the UAV 11.

[0046] like Figure 7-Figure 8As shown, a drone testing system provided by the present invention is provided. In this embodiment, the limiting mechanism 9 includes a receiving groove 96 provided on the side of the clamping limiting rod 58 away from the middle part of the second double-headed screw 55, and the interior of the receiving groove 96 is slidably connected with an extrusion strip 99, and a first compression spring 94 is connected between the extrusion strip 99 and the side wall of the receiving groove 96, and a receiving cavity 97 is provided inside the extrusion strip 99, and a stopper 95 is slidably connected inside the receiving cavity 97, and the stopper 95 and the receiving cavity 97 are away from the middle of the adjustment block 54. A second compression spring 98 is connected between the side walls of the part, and the stop head 95 is fixedly connected to the side surface near the middle of the adjusting block 54 with a limiting rod 93, and the limiting rod 93 passes through the extrusion strip 99 and the clamping limiting rod 58, and the clamping limiting rod 58 is provided with a fine hole for the limiting rod 93 to move. Initially, one end of the limiting rod 93 does not extend out of the clamping limiting rod 58, and the adjusting block 54 is fixedly connected with a limiting plate 92, and the limiting plate 92 is provided with a plurality of equidistant limiting grooves 91 on the side surface near the limiting rod 93.

[0047] When the legs of the drone 11 are fixed, the second double-headed screw 55 drives the slider 57 to move toward the two sides of the adjustment block 54, and is squeezed by the legs of the drone 11. Under the reaction force, the squeezing bar 99 retracts into the storage groove 96, and the squeezing bar 99 drives the stopper 95 and the limit rod 93 to move through the second compression spring 98, and one end of the limit rod 93 is inserted into the limit groove 91, so that the clamping limit rod 58 and the adjustment block 54 are relatively fixed;

[0048] Since the thickness of the legs of different types of drones 11 is different, when the legs of the drone 11 are fixed, one end of the first slide groove 53 may be just stuck between two adjacent limit grooves 91, so that the limit rod 93 cannot be inserted into the limit groove 91. At this time, the limit rod 93 is blocked by the limit plate 92 and cannot move, then the stopper 95 will move in the storage cavity 97, avoiding the extrusion bar 99 from being blocked. When the drone 11 is tested and the drone 11 rises, the drone 11 drives the clamping limit rod 58 to rise, and the clamping limit rod 58 drives the first slide groove 53 to rise. When the axis of one end of the first slide groove 53 coincides with the axis of the limit groove 91, under the action of the second compression spring 98, the limit rod 93 is inserted into the limit groove 91 to fix the legs of the drone 11, and the gap between the legs of the drone 11 and the adjustment block 54 is not greater than the distance between the two adjacent limit grooves 91, thereby preventing the drone 11 from escaping from the clamping mechanism 5.

[0049] When disassembling the drone 11, the clamping limit rod 58 and the legs of the drone 11 are separated. Under the action of the first compression spring 94, the extrusion bar 99 drives the stop head 95 and the limit rod 93 to move in the opposite direction, and the limit rod 93 is pulled out of the limit groove 91, and then the next drone 11 can be fixed.

[0050] like Figure 1-Figure 2 As shown, a UAV testing system provided by the present invention is provided. In order to test the tension and torque of the UAV 11 under strong wind conditions in a natural environment, in this embodiment, a wind simulation module 6 is also provided, and the wind simulation module 6 is used to simulate a strong wind environment.

[0051] like Figure 1-Figure 2 As shown, a UAV test system provided by the present invention is provided. In this embodiment, the wind simulation module 6 includes an annular turntable 63, and the annular turntable 63 is installed on the test bench 1. The top of the annular turntable 63 is fixedly connected with an arc-shaped wind gathering plate 62, and a fan 61 is installed on the arc-shaped wind gathering plate 62.

[0052] During the test, the fan 61 blows air toward the UAV 11 to test the stability and wind resistance of the UAV 11 in strong winds.

[0053] like Figure 1-Figure 2 As shown, a UAV test system provided by the present invention is provided. In order to more realistically simulate the strong wind environment under natural conditions, in this embodiment, the annular turntable 63 is rotatably mounted on the test bench 1, so that the fan 61 can blow air in any direction of the UAV 11, and the performance of the UAV 11 under a variable strong wind environment can be tested;

[0054] In order to drive the fan 61 to move, the wind simulation module 6 also includes a mounting frame 65 and a first motor 66. The mounting frame 65 is fixedly connected to the test bench 1, and the first motor 66 is fixedly installed on the mounting frame 65. The output shaft of the first motor 66 is fixedly connected to a gear 67. A gear ring 64 is fixedly connected to the annular turntable 63, and the gear 67 and the gear ring 64 are meshingly connected.

[0055] Working principle: when installing the drone 11, first place the drone 11 on the placement plate 51, then rotate the first double-headed screw 52, ​​the first double-headed screw 52 drives the two adjustment blocks 54 to approach each other, the adjustment block 54 drives the clamping limit rod 58 to move, under the action of the inclined surface of the clamping limit rod 58, the clamping limit rod 58 presses the legs of the drone 11 on the adjustment block 54, and then rotate the two second double-headed screws 55, the second double-headed screws 55 drive the two sliders 57 to move in reverse, the sliders 57 drive the clamping limit rod 58 to move, the two clamping limit rods 58 fix the legs of the drone 11, and, under the reaction force, the extrusion bar 99 retracts into the storage groove 96, the extrusion bar 99 drives the stopper 95 and the limit rod 93 to move through the second compression spring 98, and one end of the limit rod 93 is inserted into the limit groove 91, so that the clamping limit rod 58 and the adjustment block 54 are relatively fixed, thereby fixing the drone 11 on the placement plate 51;

[0056] When testing the vertical tension of the drone 11, the drone 11 is made to rise vertically, and then the second motor 87 drives the reel 89 to rotate, and the reel 89 pays off the pull rope 84. The drone 11 drives the load plate 4 to rise through the clamping mechanism 5, and the load plate 4 pulls the reel 89 and the mounting plate 86 through the pull rope 84. The tension sensor 810 can measure the tension of the mounting plate 86. The tension plus the weight of the mounting plate 86, the second motor 87, the vertical plate 88, the reel 89, the pull rope 84, the load plate 4 and the clamping mechanism 5 can be used to obtain the rising tension of the drone 11.

[0057] When testing the tilt tension of the drone 11, the drone 11 is tilted to fly, and the drone 11 drives the load-bearing plate 4 to tilt through the clamping mechanism 5. The load-bearing plate 4 pulls the winding disk 89 and the mounting plate 86 through the pull rope 84. The tension sensor 810 can measure the vertical tension of the mounting plate 86, and then the angle sensor 83 can detect the deflection angle of the measuring wheel 82, and then the tilt angle of the pull rope 84 can be measured, and then the vertical and horizontal tension components of the pull rope 84 can be calculated, and the value detected by the tension sensor 810 is the vertical tension component of the pull rope 84, and then the tilt tension of the pull rope 84 and the horizontal component of the pull rope 84 can be calculated, so that the tension of the drone 11 during tilted flight can be fully and accurately tested;

[0058] When testing the turning torque of the drone 11, the second motor 87 drives the winding drum 89 to reel in the pull rope 84, so that the bearing plate 4 falls on the outer turntable 2, and the positioning column 7 is inserted into the positioning hole 10, and then the drone 11 is operated to turn. The drone 11 will drive the outer turntable 2 to rotate through the clamping mechanism 5 and the bearing plate 4, and the torque sensor 3 detects the torsional force of the outer turntable 2, so that the steering torque of the drone 11 can be calculated;

[0059] When the UAV 11 is subjected to a tension test, a strong wind environment can also be simulated by the wind simulation module 6 to test the flight performance of the UAV 11 in a strong wind environment. During the test, the first motor 66 drives the gear 67 to rotate, the gear 67 drives the gear ring 64 and the annular turntable 63 to rotate, the annular turntable 63 drives the fan 61 to rotate, and the fan 61 can blow air in different directions of the UAV 11, so as to simulate a strong wind environment with changing directions, making it closer to natural conditions, thereby making the test results of the UAV 11 more accurate.

[0060] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

[0061] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A UAV testing system, comprising a testing device and a processing module, characterized in that: The testing device comprises a test bench (1), the test bench (1) being mounted with a torque test module, the torque test module being used to test the torque of the drone (11) when turning, the torque test module being mounted with a tension test module (8), the tension test module (8) being used to test the vertical tension and tilt tension of the drone (11), the output end of the tension test module (8) being connected to a bearing plate (4), the torque test module and the tension test module (8) being both electrically connected to a processing module, the processing module being used to process data measured by the torque test module and the tension test module (8), the bearing plate (4) being mounted with a clamping mechanism (5), the clamping mechanism (5) being used to fix the drone (11), the torque test module being fixedly connected with a positioning column (7), the bearing plate (4) being provided with a positioning hole (10) adapted to the positioning column (7); The test bench (1) is also equipped with a wind simulation module (6), and the wind simulation module (6) is used to simulate a strong wind environment; The torque test module comprises an outer rotating table (2), the outer rotating table (2) is rotatably connected to the test table (1), a torque sensor (3) is fixedly mounted on the test table (1), an input end of the torque sensor (3) is fixedly connected to the outer rotating table (2), and the processing module and the torque sensor (3) are electrically connected; The tension test module (8) comprises a containing cylinder (85), the containing cylinder (85) is rotatably connected to the outer turntable (2), a tension sensor (810) is fixedly installed inside the outer turntable (2), the input end of the tension sensor (810) is fixedly connected to a mounting plate (86), the processing module is electrically connected to the tension sensor (810), the top of the mounting plate (86) is fixedly connected to a vertical plate (88), a winding disk (89) is rotatably connected to the vertical plate (88), a pull rope (84) is wound on the winding disk (89), a second motor (87) is fixedly installed on the side of the vertical plate (88), the output shaft of the second motor (87) is fixedly connected to the side of the winding disk (89), and one end of the pull rope (84) is connected to the bottom of the bearing plate (4); The tension test module (8) further comprises a rotating column (81), the rotating column (81) being rotatably connected to the bottom of the bearing plate (4), an angle sensor (83) being fixedly mounted on the rotating column (81), an input end of the angle sensor (83) being fixedly connected to a measuring wheel (82), one end of the pull rope (84) being fixedly connected to the measuring wheel (82), and the angle sensor (83) being electrically connected to the processing module; The clamping mechanism (5) comprises a placement plate (51), the placement plate (51) is fixedly mounted on the top of the bearing plate (4), first slide grooves (53) are provided on both sides of the top of the placement plate (51), and adjustment blocks (54) are slidably connected inside the two first slide grooves (53), a second slide groove (56) is provided on the top of the adjustment block (54), and two sliders (57) are slidably connected inside the second slide groove (56), a lifting column (510) is vertically slidably connected to the slider (57), a clamping limit rod (58) is fixedly connected to the top of the lifting column (510), and a tension spring (511) is connected between the lifting column (510) and the slider (57); A first double-headed screw (52) is rotatably connected to the placement plate (51), the two adjustment blocks (54) are respectively threadedly connected to the two ends of the first double-headed screw (52), a second double-headed screw (55) is rotatably connected to the adjustment block (54), and the two sliding blocks (57) are respectively threadedly connected to the two ends of the second double-headed screw (55); The wind simulation module (6) comprises an annular turntable (63), the annular turntable (63) being mounted on the test bench (1), the top of the annular turntable (63) being fixedly connected to an arc-shaped wind gathering plate (62), and a fan (61) being mounted on the arc-shaped wind gathering plate (62).

2. The drone testing system according to claim 1, characterized in that: It also includes a plurality of limiting mechanisms (9), one end of each of the limiting mechanisms (9) being mounted on a plurality of clamping limiting rods (58), and the other end of each of the limiting mechanisms (9) being mounted on a slider (57); when the clamping limiting rods (58) clamp the legs of the drone (11), the limiting mechanisms (9) are used to relatively fix the clamping limiting rods (58) and the slider (57).

3. The drone testing system according to claim 2, characterized in that: The limiting mechanism (9) comprises a receiving groove (96) provided on the side of the clamping limiting rod (58) away from the middle of the second double-headed screw (55); an extrusion strip (99) is slidably connected inside the receiving groove (96); a first compression spring (94) is connected between the extrusion strip (99) and the side wall of the receiving groove (96); a receiving cavity (97) is provided inside the extrusion strip (99); a stopper (95) is slidably connected inside the receiving cavity (97); a second compression spring (94) is connected between the stopper (95) and the side wall of the receiving cavity (97) away from the middle of the adjusting block (54). The stopper (95) is fixedly connected to a limit rod (93) on the side near the middle of the adjustment block (54); the limit rod (93) passes through the extrusion strip (99) and the clamping limit rod (58); the clamping limit rod (58) is provided with a fine hole for the limit rod (93) to move; initially, one end of the limit rod (93) does not extend out of the clamping limit rod (58); the adjustment block (54) is fixedly connected to a limit plate (92); the limit plate (92) is provided with a plurality of equidistantly distributed limit grooves (91) on the side near the limit rod (93).

4. The drone testing system according to claim 1, characterized in that: The annular turntable (63) is rotatably mounted on the test bench (1); the wind simulation module (6) further comprises a mounting frame (65) and a first motor (66); the mounting frame (65) is fixedly connected to the test bench (1); the first motor (66) is fixedly mounted on the mounting frame (65); an output shaft of the first motor (66) is fixedly connected to a gear (67); a gear ring (64) is fixedly connected to the annular turntable (63); and the gear (67) and the gear ring (64) are meshingly connected.

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