A power test device for hydrogen-powered UAV

Abstract

The present invention relates to the technical field of unmanned aerial vehicle testing equipment, and specifically discloses a power testing device for a hydrogen-powered unmanned aerial vehicle, comprising a detection structure, a fixing structure and a docking structure, wherein the fixing structure is fixedly arranged in the detection structure, and the docking structure is movably inserted in a bearing in the detection mechanism. The present invention can support hydrogen-powered motors of different sizes through the fixing structure, can adapt to motors of various models and sizes, improves the versatility and flexibility of the equipment, integrates a wind force detector, a pressure detector and an infrared speed meter, can comprehensively collect multiple data such as wind force, driving force and rotation speed generated by a motor-driven propeller, is connected to the propeller blades through the docking structure, drives the shaft frame to rotate during motor drive, and the entire testing process is integrated on one platform, simplifies the testing process, and improves the testing efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle testing equipment, and in particular to a power testing device for a hydrogen-powered unmanned aerial vehicle. Background Art

[0002] A hydrogen-powered drone is a drone that uses hydrogen as fuel and converts hydrogen into electricity through a fuel cell to drive an electric motor; or uses hydrogen as fuel to power the engine. Compared with traditional lithium battery drones, hydrogen-powered drones have higher energy density, longer flight time and lower emissions.

[0003] However, in production, the power will be tested to see if it meets the corresponding power requirements to ensure the smooth flight of the drone; and in testing, in order to better detect the power output, a corresponding propeller test will be installed on the motor. Therefore, a power test device for hydrogen-powered drones is designed. Summary of the invention

[0004] The object of the present invention is to provide a power testing device for a hydrogen-powered UAV to solve the problems raised in the above-mentioned background technology.

[0005] In order to solve the above-mentioned problem, the present invention provides the following technical solution: a power testing device for a hydrogen-powered UAV, comprising a detection structure, a fixing structure and a docking structure, wherein the fixing structure is fixedly arranged in the detection structure, and the docking structure is movably inserted into a bearing in the detection mechanism.

[0006] Preferably, the detection structure includes a first test box, a pair of first electric slide rails, a slide plate, a pair of adapter claws, a second test box, a bearing, an air duct, a wind force detector, a display, a control keyboard and an infrared speed meter; the first test box is a rectangular box without an upper wall and a front side wall, and the lower wall of the first test box is provided with mounting grooves near the four corners, a slide groove is provided along the middle of the upper wall of the left and right side walls of the first test box, a pair of the first electric slide rails are symmetrically arranged on the left and right side walls of the first test box and are located below the slide groove, the slide plate is rectangular and the lower wall is symmetrically provided with tracks that match the slide groove, the slide plate is movably arranged on the first test box and the track of the lower wall of the slide plate is inserted into the slide groove, an air outlet is provided in the middle of the rear end of the slide plate, and The air outlet is located in the middle of the upper wall of the first test box, and a docking port that matches with the upper wall of the first test box is provided in the middle of the front end of the skateboard. One end of a pair of the transfer claws is respectively fixed on the first electric slide rail and the other end of the transfer claws is fixedly connected to the left and right side walls of the skateboard. The second test box is a rectangular box without a lower wall and a left side wall. The second test box is fixed on the upper wall of the front end of the skateboard, and the second test box matches with the first test box. The bearing is fixedly embedded in the middle of the upper wall of the second test box, and the air duct is detachably placed in the middle of the upper wall of the rear end of the skateboard. The wind detector is fixed on the inner wall of the air duct, and the display is fixed on the front wall of the second test box. The control keyboard is fixed on the front wall of the second detection box and is located on the right side of the display.

[0007] Preferably, the fixed structure includes a hydraulic cylinder, a support plate, a second electric slide rail, a pair of clamping seats, a first support rod and a second support rod; one end of the hydraulic cylinder is fixedly arranged in the middle of the lower wall of the first test box, the support plate is fixedly arranged on the telescopic end of the hydraulic cylinder, and the support plate is movably embedded in the first test box, the second electric slide rail is fixedly arranged in the middle of the upper wall of the support plate, and a pair of second slide seats that are relatively movable are arranged on the second electric slide rail, one end of a pair of the clamping seats are symmetrically arranged on the second electric slide rail, and the other ends of the pair of the clamping seats are both arc structures, one of which has a rectangular socket in the middle of the clamping seat, the first support rod is concave, the first support rod is fixedly arranged in the middle of one of the clamping seats, the two ends of the first support rod are respectively located at the front and rear sides of the middle of the other clamping seat, one end of the second support rod is detachably arranged in the middle of the left side wall of the other clamping seat, and the other end of the second support rod movably passes through the socket of one of the clamping seats, and the upper wall of the second support rod is on the same horizontal plane as the upper walls at both ends of the first support rod.

[0008] Preferably, the docking structure includes an axle frame, three flip seats, three clamping pieces, three first bolts, three docking arms, three clamping arms and three clamping bolts; one end of the axle frame is fixedly passed through the middle of the bearing, and one end of the axle frame is opposite to the infrared speed meter, and three slides are equidistantly arranged on the side wall of the other end of the axle frame, one ends of the three flip seats are respectively movably passed through the middle of the slide, the three clamping pieces are respectively movably arranged on the slide and are opposite to the flip seats, the three first bolts are respectively movably passed through the middle of the clamping pieces and are screwed to the flip seats, one ends of the three docking arms are respectively movably connected to the other ends of the flip seats, and the docking arms can be flipped left and right, one ends of the three clamping arms are respectively movably connected to the other ends of the docking arms and the clamping arms can be flipped forward and backward, and the other ends of the three clamping arms are all concave, the three clamping bolts are respectively movably screwed on the side walls of the other ends of the docking arms, and a circular top sheet is arranged on one end of the clamping bolts, and the top sheet is located inside the other end of the clamping arm.

[0009] Preferably, the first support rod and the second support rod are used to carry the test motor or engine, and the motor or engine is clamped and fixed by a clamping seat.

[0010] Preferably, the height of the clamp arm is adjusted by flipping the docking arm on a flip seat in the docking structure, so that the clamp arm can be clamped on the propeller blade.

[0011] Preferably, the clamping arm cooperates with the clamping bolt to be clamped on the propeller blade.

[0012] Preferably, a pressure detector can be installed between the left and right ends of the support plate and the second electric slide rail.

[0013] Preferably, the installation position of the clamp arm can be adjusted by moving the flip seat on the slide, and after the flip seat moves, the first bolt is tightened to cooperate with the flip seat to fix on the slide with the help of the clamping piece.

[0014] The invention provides a power test device for a hydrogen-powered UAV, which has the following beneficial effects:

[0015] 1. High flexibility and adaptability: The fixed structure can support hydrogen-powered motors of different sizes and can adapt to motors of various models and sizes, thus improving the versatility and flexibility of the equipment.

[0016] 2. Comprehensive data collection: It integrates wind force detector, pressure detector and infrared speed meter, which can comprehensively collect multiple data such as wind force, thrust and speed generated by the motor-driven propeller.

[0017] 3. Efficient testing process: The propeller blades are connected through a docking structure, and the shaft frame is driven by the motor. The entire testing process is integrated on one platform, which simplifies the testing process and improves the testing efficiency.

[0018] 4. Real-time monitoring and feedback: The infrared tachometer can detect the motor speed in real time and provide instant feedback data. It supports hydrogen-powered motors of different sizes through a fixed structure, integrates wind detectors, pressure detectors and infrared tachometers, and realizes comprehensive data collection and precise test environment. Its advantages include flexibility and adaptability, comprehensive data collection, precise test environment, efficient test process, real-time monitoring and feedback, as well as safety and reliability. These advantages make this solution have significant advantages in the testing and evaluation of hydrogen-powered motors, and can provide strong support for the research and development and optimization of motors. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the assembly structure of the present invention;

[0020] Figure 2 It is a schematic diagram of a first assembly structure of the present invention;

[0021] Figure 3 is a schematic diagram of a second assembly structure of the present invention;

[0022] Figure 4 It is a schematic diagram of the split structure of the detection structure of the present invention;

[0023] Figure 5 It is a schematic diagram of the split structure of the fixed structure of the present invention;

[0024] Figure 6 It is a schematic diagram of the split structure of the docking structure of the present invention;

[0025] Figure 7 For the present invention Figure 5 A local enlarged view of point A in FIG.

[0026] Figure 8 For the present invention Figure 5 A local enlarged view of point B in FIG.

[0027] Fig. 9 For the present invention Figure 6 A partial enlarged view of point C in the figure.

[0028] In the figure: 1. detection structure; 10. first test box; 11. first electric slide rail; 12. slide plate; 13. adapter claw; 14. second test box; 15. bearing; 16. air duct; 17. wind detector; 18. display; 19. control keyboard; 20. infrared speed meter; 2. fixing structure; 21. hydraulic cylinder; 22. support plate; 23. second electric slide rail; 24. clamping seat; 25. first support rod; 26. second support rod; 3. docking structure; 31. shaft frame; 32. flip seat; 33. clamping piece; 34. first bolt; 35. docking arm; 36. clamping arm; 37. clamping bolt; 4. slide groove; 5. socket; 6. slide; 7. pressure detector. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only 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 creative work are within the scope of protection of the present invention.

[0030] See also Figure 1-Figure 9 The present invention provides a technical solution: a power test device for a hydrogen-powered UAV, comprising a detection structure 1, a fixing structure 2 and a docking structure 3, wherein the fixing structure 2 is fixedly arranged in the detection structure 1, and the docking structure 3 is movably inserted into a bearing 15 in the detection mechanism; the motor is fixed by the fixing structure 2, the wind force and thrust generated by the motor driving the propeller to rotate are detected by the detection structure 1, and the rotation speed of the propeller driven by the motor is detected by the docking structure 3.

[0031] As a further solution of the present invention, the detection structure 1 includes a first test box 10, a pair of first electric slide rails 11, a slide plate 12, a pair of adapter claws 13, a second test box 14, a bearing 15, an air duct 16, a wind detector 17, a display 18, a control keyboard 19 and an infrared speed meter 20; the first test box 10 is a rectangular box without an upper wall and a front side wall, and the lower wall of the first test box 10 is provided with mounting grooves near the four corners, and the upper wall of the left and right side walls of the first test box 10 is opened through the middle There is a slide 4, a pair of first electric slide rails 11 are symmetrically arranged on the left and right side walls of the first test box 10 and are located below the slide 4, the slide plate 12 is rectangular and the lower wall is symmetrically provided with tracks that match the slide 4, the slide plate 12 is movably arranged on the first test box 10 and the track on the lower wall of the slide plate 12 is inserted into the slide 4, an air outlet is arranged in the middle of the rear end of the slide plate 12, and the air outlet is located in the middle of the upper wall of the first test box 10, and a docking interface that matches the upper wall of the first test box 10 is arranged in the middle of the front end of the slide plate 12. One end of the transfer claw 13 is fixedly arranged on the first electric slide rail 11 and the other end of the transfer claw 13 is fixedly connected to the left and right side walls of the slide plate 12. The second test box 14 is a rectangular box without a lower wall and a left side wall. The second test box 14 is fixedly arranged on the upper wall of the front end of the slide plate 12, and the second test box 14 is matched with the first test box 10. The bearing 15 is fixedly embedded in the middle of the upper wall of the second test box 14. The air duct 16 is detachably arranged in the middle of the upper wall of the rear end of the slide plate 12. The wind force detector 17 is fixedly arranged on the inner wall of the air duct 16. The display 18 is fixedly arranged on the front side wall of the second test box 14. The control keyboard 19 is fixedly arranged on the front side wall of the second test box and is located on the right side of the display 18; the slide plate 12 is driven to move forward and backward by the first electric slide rail 11, and the second test box 14 is adjusted relative to the first test box 10 for connection with the docking machine structure. The air duct 16 on the slide plate 12 is adjusted relative to the first test box 10 for detecting wind force. The control is performed through the control keyboard 19, and various test data are displayed through the display 18.

[0032] As a further solution of the present invention, the fixed structure 2 includes a hydraulic cylinder 21, a support plate 22, a second electric slide rail 23, a pair of clamping seats 24, a first support rod 25 and a second support rod 26; one end of the hydraulic cylinder 21 is fixedly arranged in the middle of the lower wall of the first test box 10, the support plate 22 is fixedly arranged on the telescopic end of the hydraulic cylinder 21, and the support plate 22 is movably embedded in the first test box 10, the second electric slide rail 23 is fixedly arranged in the middle of the upper wall of the support plate 22, and a pair of second slide seats that move relatively are arranged on the second electric slide rail 23, one end of a pair of clamping seats 24 are symmetrically arranged on the second electric slide rail 23, and the other ends of the pair of clamping seats 24 are both arc-shaped structures, one of the clamping seats 24 is provided with a rectangular socket 5 in the middle, and the second A support rod 25 is concave, and the first support rod 25 is fixedly set in the middle of one of the clamping seats 24. The two ends of the first support rod 25 are respectively located at the front and rear sides of the middle of the other clamping seat 24. One end of the second support rod 26 is detachably placed in the middle of the left side wall of the other clamping seat 24, and the other end of the second support rod 26 is movable through the socket 5 of one of the clamping seats 24. The upper wall of the second support rod 26 and the upper walls of the two ends of the first support rod 25 are on the same horizontal plane; the clamping seat 24 is driven to rise and fall by the hydraulic cylinder 21 for different tests of the motor to be tested, and the symmetrically arranged clamping seats 24 are driven to move relative to each other by the second electric slide rail 23 to support and fix the motor to be tested, and the motor to be tested is carried by the relatively staggered first support rod 25 and the second support rod 26.

[0033] As a further solution of the present invention, the docking structure 3 includes an axle frame 31, three flip seats 32, three clips 33, three first bolts 34, three docking arms 35, three clamping arms 36 and three clamping bolts 37; one end of the axle frame 31 is fixedly passed through the middle of the bearing 15, and one end of the axle frame 31 is opposite to the infrared speed meter 20, and three slides 6 are equidistantly arranged on the side wall of the other end of the axle frame 31, one end of the three flip seats 32 is respectively movably passed through the middle of the slide 6, the three clips 33 are respectively movably arranged on the slide 6 and opposite to the flip seat 32, the three first bolts 34 are respectively movably passed through the middle of the clip 33 and are screwed to the flip seat 32, and one end of the three docking arms 35 is respectively movably connected to the other end of the flip seat 32 The docking arm 35 can be flipped left and right, one end of the three clamping arms 36 is movably connected to the other end of the docking arm 35 and the clamping arm 36 can be flipped forward and backward, the other ends of the three clamping arms 36 are all concave, three clamping bolts 37 are movably screwed on the side wall of the other end of the docking arm 35, and a circular top plate is provided on one end of the clamping bolt 37, and the top plate is located inside the other end of the clamping arm 36; the height of the clamping arm 36 relative to the propeller blade is adjusted by flipping the docking arm 35 on the flip seat 32, the clamping arm 36 is clamped on the propeller by the clamping bolt 37 and then tightened and fixed, the docking position is moved and adjusted on the slide 6 by the flip seat 32, and the rotation speed is detected by the infrared detector through the shaft frame 31 with the help of the bearing 15.

[0034] As a further solution of the present invention, the first support rod 25 and the second support rod 26 are used to carry the test motor or engine, and the motor or engine is clamped and fixed by the clamp seat 24 to meet the design installation and fixing requirements.

[0035] As a further solution of the present invention, the clamping arm 36 cooperates with the clamping bolt 37 to clamp on the propeller blade for docking requirements.

[0036] As a further solution of the present invention, a pressure detector 7 can be installed between the left and right ends of the support plate 22 and the second electric slide rail 23 to detect the driving force after the motor drives the blade to rotate.

[0037] The detailed connection means are well-known in the art. The following mainly introduces the working principle and process. The specific work is as follows.

[0038] First, the motor to be tested is placed between the two clamping seats 24 and on the first support rod 25 and the second support rod 26. The control keyboard 19 in the detection structure 1 drives the second electric slide rail 23 on the support plate 22 to clamp and fix the motor to be tested through the two relatively movable clamping seats 24. If the motor to be tested is small, the second support rod 26 can pass through the socket 5 of one of the clamping seats 24.

[0039] Then, according to the test requirements, the first electric slide rail 11 in the detection structure 1 is controlled, and the sliding plate 12 is driven to slide on the first test box 10 through the sliding groove 4 by means of the transfer claw 13, so that the rear end of the sliding plate 12 corresponds to the first test box 10, and the second test box 14 is located at the front side of the first test box 10; the detected motor is driven to drive the propeller set in the opposite direction to rotate, and the propeller blows air upward, and the wind passes through the air duct 16 to drive the wind detector 17 to perform a wind test;

[0040] If a pressure detector 7 is provided between the second electric slide rail 23 and the support plate 22 in the fixed structure 2, the detected motor applies reverse force to the pressure detector 7 when blowing air upward to realize the detection driving force, and displays the corresponding data on the display 18;

[0041] Then, the second electric slide rail 23 is controlled to drive the slide plate 12 to move, so that the second test box 14 is opposite to the first test box 10; at this time, the hydraulic cylinder 21 is controlled to extend to drive the motor under test and the propeller blade to rise; the height of the clamp arm 36 is adjusted by flipping the docking arm 35 on the flip seat 32 in the docking structure 3, so that the clamp arm 36 can be clamped on the propeller blade, and because the propeller blade is in an inclined state, the flip clamp arm 36 is adjusted to a corresponding tilt angle on the flip arm, and then tightened by rotating the clamping bolt 37; the three clamp arms 36 on the shaft frame 31 are respectively connected to the propeller blade; the installation position of the clamp arm 36 can be moved and adjusted on the slide 6 by the flip seat 32, and after the flip seat 32 moves, it is fixed on the slide 6 by tightening the first bolt 34 with the help of the clamp 33 to apply force;

[0042] After the docking structure 3 is connected to the propeller, the motor to be tested can be driven again to drive the shaft frame 31 to rotate synchronously with the bearing 15, and then the infrared speed meter 20 and one end of the shaft frame 31 can detect the rotation speed relative to each other, and finally multiple data tests can be achieved.

[0043] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A power test device for a hydrogen-powered UAV, characterized in that: It comprises a detection structure (1), a fixing structure (2) and a docking structure (3), wherein the fixing structure (2) is fixedly arranged in the detection structure (1), and the docking structure (3) is movably inserted into a bearing (15) in the detection mechanism; The detection structure (1) comprises a first test box (10), a pair of first electric slide rails (11), a slide plate (12), a pair of transfer claws (13), a second test box (14), a bearing (15), an air duct (16), a wind force detector (17), a display (18), a control keyboard (19), and an infrared speed meter (20); The first test box (10) is a rectangular box without an upper wall and a front side wall, and the lower wall of the first test box (10) is provided with mounting grooves near the four corners. A slide groove (4) is provided along the middle of the upper wall of the left and right side walls of the first test box (10). A pair of the first electric slide rails (11) are symmetrically arranged on the left and right side walls of the first test box (10) and are located below the slide groove (4). The slide plate (12) is rectangular and has a track symmetrically arranged on the lower wall that matches the slide groove (4). The slide plate (12) is movably arranged on the first test box (10) and the track on the lower wall of the slide plate (12) is inserted into the slide groove (4). An air outlet is arranged in the middle of the rear end of the slide plate (12), and the air outlet is located in the middle of the upper wall of the first test box (10). A docking interface that matches the upper wall of the first test box (10) is arranged in the middle of the front end of the slide plate (12). , one end of a pair of transfer claws (13) is respectively fixedly arranged on the first electric slide rail (11) and the other end of the transfer claws (13) is fixedly connected to the left and right side walls of the slide plate (12); the second test box (14) is a rectangular box without a lower wall and a left side wall; the second test box (14) is fixedly arranged on the front upper wall of the slide plate (12), and the second test box (14) is matched with the first test box (10); the bearing (15) is fixedly embedded in the middle of the upper wall of the second test box (14); the air duct (16) is detachably arranged in the middle of the rear upper wall of the slide plate (12); the wind force detector (17) is fixedly arranged on the inner wall of the air duct (16); the display (18) is fixedly arranged on the front side wall of the second test box (14); and the control keyboard (19) is fixedly arranged on the front side wall of the second test box and is located on the right side of the display (18).

2. A power test device for a hydrogen-powered UAV according to claim 1, characterized in that: The fixing structure (2) comprises a hydraulic cylinder (21), a support plate (22), a second electric slide rail (23), a pair of clamping seats (24), a first support rod (25) and a second support rod (26); One end of the hydraulic cylinder (21) is fixedly arranged at the middle of the lower wall of the first test box (10); the support plate (22) is fixedly arranged on the telescopic end of the hydraulic cylinder (21), and the support plate (22) is movably embedded in the first test box (10); the second electric slide rail (23) is fixedly arranged at the middle of the upper wall of the support plate (22), and a pair of second slide seats that move relatively are arranged on the second electric slide rail (23); one end of a pair of clamp seats (24) are symmetrically arranged on the second electric slide rail (23), and the other ends of the pair of clamp seats (24) are both arc-shaped structures, and one of the clamp seats (24) is A rectangular socket (5) is provided in the middle of the clamping seat (24), the first support rod (25) is concave, the first support rod (25) is fixedly arranged in the middle of one of the clamping seats (24), the two ends of the first support rod (25) are respectively located at the front and rear sides of the middle of the other clamping seat (24), one end of the second support rod (26) is detachably arranged in the middle of the left side wall of the other clamping seat (24), and the other end of the second support rod (26) is movably inserted into the socket (5) of one of the clamping seats (24), and the upper wall of the second support rod (26) and the upper walls of the two ends of the first support rod (25) are on the same horizontal plane.

3. A power test device for a hydrogen-powered UAV according to claim 2, characterized in that: The docking structure (3) comprises an axle frame (31), three turning seats (32), three clamping pieces (33), three first bolts (34), three docking arms (35), three clamping arms (36) and three clamping bolts (37); One end of the shaft frame (31) is fixedly passed through the middle of the bearing (15), and one end of the shaft frame (31) is opposite to the infrared speed meter (20). Three slides (6) are equidistantly arranged on the side wall of the other end of the shaft frame (31). One end of the three flip seats (32) are respectively movably passed through the middle of the slides (6). The three clips (33) are respectively movably arranged on the slides (6) and opposite to the flip seats (32). The three first bolts (34) are respectively movably passed through the middle of the clips (33) and are screwed to the flip seats (32). One end of the docking arm (35) is movably connected to the other end of the flip seat (32), and the docking arm (35) can flip left and right. One end of the three clamping arms (36) is movably connected to the other end of the docking arm (35), and the clamping arm (36) can flip forward and backward. The other ends of the three clamping arms (36) are all concave. The three clamping bolts (37) are movably screwed to the side wall of the other end of the docking arm (35), and a circular top plate is arranged on one end of the clamping bolt (37), and the top plate is located inside the other end of the clamping arm (36).

4. A power test device for a hydrogen-powered UAV according to claim 3, characterized in that: A pressure detector (7) can also be installed between the left and right ends of the support plate (22) and the second electric slide rail (23).

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