Unmanned aerial vehicle impact vibration test system with adaptive adjustment

Abstract

The invention relates to the technical field of detection, in particular to an unmanned aerial vehicle impact vibration test system with a self-adaptive adjustment function. According to the technical scheme, the device comprises an unmanned aerial vehicle placing part, the unmanned aerial vehicle placing part comprises a bottom plate fixedly mounted at the top of a spring telescopic rod, a guide rod internally provided with a spring is fixedly mounted at the top of the bottom plate, and a top plate is fixedly mounted at the top of the guide rod; the interior of the top plate is rotationally connected with a gravity center deflection plate for placing the unmanned aerial vehicle with the gravity center deviating front and back through a rotating shaft. The gravity center deflection plate is matched with the torque spring, the inclination angle of the unmanned aerial vehicle is adjusted according to the gravity center of the unmanned aerial vehicle, gravitational torque generated by gravity center shift is made to be matched with the inclination angle of the vibration plate, and therefore the unbalance problem is accurately exposed, and the real working condition is simulated; the top plate moves downwards, the push rod and the linkage rod are used for changing the position of the sliding switch, the vibration frequency is changed, and vibration detection is conducted by self-adaption to the gravity of the unmanned aerial vehicle.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of detection, in particular to a UAV impact vibration test system with adaptive adjustment. BACKGROUND

[0002] A UAV is a pilotless aircraft controlled by radio remote control equipment or autonomous program, which has the ability of vertical take-off and landing, flexible flight, and carrying load. The vibration detection of the UAV is a key link to ensure its flight safety, performance stability, and equipment life. During factory inspection, ground idle speed vibration test is performed on each UAV to eliminate unqualified products with unbalanced propellers and abnormal motor noises.

[0003] In the patent document with publication number CN118254962B, a UAV mechanical vibration test device is proposed. The UAV is placed on the top of the rotating seat, the hand wheel is rotated, the double-headed screw rod is driven to rotate, the two fixed boxes are brought closer to each other, and the UAV is clamped. Then, the tightening bolts are loosened, the top clamping plate freely falls and abuts against the top of the UAV, and the tightening bolts are tightened to fix the top clamping plate on the fixed box, thereby fixing the UAV. This device can fix the side and top of the UAV, making the fixing effect more accurate, and can fix most models of UAVs.

[0004] There are UAVs with a center of gravity offset. This type of UAV frequently adjusts its attitude during actual flight (such as hovering tilt, turning roll, and climbing pitch). The influence of the center of gravity offset is only highlighted at a "non-horizontal angle". Direct measurement of the UAV will cause the detection data to be distorted and the risk to be increased. SUMMARY

[0005] The present application aims to solve the problems in the background art and proposes a UAV impact vibration test system with adaptive adjustment.

[0006] The technical solution of the present application is a UAV impact vibration test system with adaptive adjustment, which includes a vibration work cabinet, a vibration device for generating vibration is fixedly installed on the side of the vibration work cabinet, a vibration plate connected with the vibration device is arranged on the top of the vibration work cabinet, a spring telescopic rod is fixedly installed on the top of the vibration plate, and the system further includes: The unmanned aerial vehicle placing part comprises a bottom plate fixedly installed at the top of the spring telescopic rod, a guide rod with a spring inside fixedly installed at the top of the bottom plate, a top plate fixedly installed at the top of the guide rod, a center of gravity deflection plate for placing the center of gravity of the unmanned aerial vehicle before and after the center of gravity is offset rotatably connected with the top plate through a rotating shaft, a torque spring elastically connected at the rotating connection between the center of gravity deflection plate and the top plate, a magnetic positioning piece arranged at the rotating shaft inside the top plate, a push rod fixedly installed at the bottom of the top plate, a linkage rod hingedly connected at the bottom end of the push rod, and a sliding switch for controlling the vibration frequency of the vibration device sliding at the bottom of the bottom plate. A stable part for positioning the push rod is arranged at the top of the bottom plate.

[0007] Optionally, the top plate adopts a box-like structure without a cover, there is a spacing between the bottom of the center of gravity deflection plate and the top plate, the center of gravity offset direction of the unmanned aerial vehicle is perpendicular to the rotating shaft direction outside the center of gravity deflection plate, and there is a spacing between the bottom end of the push rod and the vibration plate.

[0008] Optionally, the magnetic positioning piece comprises a butt joint block, the butt joint block adopts an end tooth-like structure, the butt joint block slides on the rotating shaft outside the center of gravity deflection plate, a first return spring is elastically connected between the end of the butt joint block and the center of gravity deflection plate, a butt joint hole is arranged in the inner wall of the top plate, and the butt joint block is inserted into the butt joint hole.

[0009] Optionally, a plurality of butt joint holes are arranged and are distributed in a ring shape at equal angles around the rotating shaft outside the center of gravity deflection plate, a triangular block-shaped transition is fixedly installed between two adjacent butt joint holes, the number of the butt joint holes is the same as the number of the end teeth of the butt joint block, and the same ring-shaped electromagnet is fixedly installed inside the top plate and inside the plurality of butt joint holes.

[0010] Optionally, a groove is arranged on the rotating shaft inside the top plate, a convex strip is fixedly installed at the inner arc surface of the butt joint block, and the convex strip slides along the groove.

[0011] Optionally, the stable part comprises two stable boxes symmetrically arranged with respect to the push rod, a sliding block is slidingly connected inside the stable box, a magnetic attraction piece is fixedly installed at the side of the sliding block, the end of the magnetic attraction piece extends out of the inside of the stable box, a strip-shaped electromagnet is fixedly installed at the top of the bottom plate and between the two stable boxes, an intermediate block is fixedly installed at the middle of the sliding block and on the side facing the push rod, and a clamping block is fixedly installed at the end of the intermediate block.

[0012] Optionally, the clamping block adopts an arc-shaped structure, the inner arc surface of the clamping block has the same arc degree as the arc surface of the push rod, a plurality of clamping grooves are arranged at equal intervals in the direction of the axis of the push rod and in the outer wall of the push rod, an arc-shaped convex strip is arranged in the inner arc surface of the clamping block, and the arc-shaped convex strip is clamped with the clamping groove.

[0013] Optionally, the slider is made of wear-resistant plastic material, and a second reset spring is elastically connected between the side, away from the magnetic attracting element, of the slider and the stabilizing box; and the magnetic attracting element is made of one of an iron block, a cobalt block and a nickel block.

[0014] Optionally, the top of the gravity center deflection plate is provided with a clamp, the clamp comprises two lateral sliding plates symmetrically arranged on the top of the gravity center deflection plate, the two lateral sliding plates slide left and right on the top of the gravity center deflection plate, the side, facing each other, of the two lateral sliding plates is slidably connected with a longitudinal moving block, the side of the longitudinal moving block is fixedly connected with a fixed elastic arc piece, the outer wall of the fixed elastic arc piece is fixedly connected with a fixed block, and the end of the fixed elastic arc piece is fixedly connected with a movable elastic arc piece penetrating through the fixed block.

[0015] Optionally, the inside of the fixed block is slidably connected with a pressing plate, the side of the movable elastic arc piece is provided with a plurality of equidistantly distributed pressing grooves, the pressing plate is in meshing connection with the pressing grooves, and the side, away from the pressing grooves, of the pressing plate is rotatably connected with a screw rod in screw connection with the fixed block.

[0016] To sum up, the present application has at least one of the following beneficial technical effects: 1. The gravity center deflection plate and the torsion spring are matched to adjust the inclination angle of the unmanned aerial vehicle according to the gravity center of the unmanned aerial vehicle, the gravity center offset of the unmanned aerial vehicle is self-adapted, the gravity moment generated by the gravity center offset is adapted to the inclination angle of the vibration plate, the imbalance problem is accurately exposed, the real working condition is simulated, the top plate and the guide rod are matched, the top plate is lowered under the action of the gravity of the unmanned aerial vehicle, the position of the sliding switch is changed by using the push rod and the linkage rod, the vibration frequency of the vibration device is changed, and the vibration detection is self-adapted to the gravity of the unmanned aerial vehicle.

[0017] 2. The bar-shaped electromagnet is electrified to attract the magnetic attracting element, the magnetic attracting element moves the clamping blocks by using the slider, the two clamping blocks clamp the push rod, the clamping force of the clamping blocks on the push rod is increased by using the cooperation between the arc convex strips and the clamping grooves, the lowering height of the gravity center deflection plate is positioned, the height of the gravity center deflection plate is prevented from changing during vibration, and the unmanned aerial vehicle vibration detection is affected.

[0018] 3. The stretching length of the movable elastic arc piece is adjusted by rotating the screw rod clockwise to move the pressing plate away from the pressing grooves, the stretching length of the movable elastic arc piece is fixed by rotating the screw rod counterclockwise to move the pressing plate towards the pressing grooves, the pressing plate is in engagement with the pressing grooves, the stretching length of the movable elastic arc piece from the fixed block is adjusted, the size of the circle around the fixed elastic arc piece and the movable elastic arc piece is changed, the unmanned aerial vehicle landing gear of different volumes is adapted, and the larger the volume of the unmanned aerial vehicle is, the thicker the diameter of the landing gear is. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 The overall structure of the present application is shown in the schematic diagram. Figure 2 Give the top plate structure schematic diagram; Figure 3 Give the push rod structure schematic diagram; Figure 4 Give the center of gravity deflection plate structure separation state schematic diagram; Figure 5 For Figure 4 A portion of the docking block structure schematic diagram; Figure 6 Give the stable box structure cross section schematic diagram; Figure 7 Give the fixed elastic arc piece structure schematic diagram; Figure 8 Give the fixed block structure half cut schematic diagram; Figure 9 For Figure 8 B portion of the press plate structure enlarged schematic diagram.

[0020] The figure mark: 1, vibration work cabinet; 2, vibration device; 3, vibration plate; 4, spring telescopic rod; 5, unmanned aerial vehicle placement part; 51, bottom plate; 52, guide rod; 53, top plate; 54, center of gravity deflection plate; 55, push rod; 56, linkage rod; 57, sliding switch; 58, torque spring; 59, docking block; 510, first reset spring; 511, docking hole; 512, ring-shaped electromagnet; 6, stabilizing part; 61, stable box; 62, sliding block; 63, second reset spring; 64, magnetic element; 65, bar-shaped electromagnet; 66, intermediate block; 67, occlusion block; 68, occlusion groove; 7, clamp; 71, transverse sliding plate; 72, longitudinal displacement block; 73, fixed elastic arc piece; 74, movable elastic arc piece; 75, fixed block; 76, press plate; 77, screw rod; 78, press groove. DETAILED DESCRIPTION

[0021] The technical solutions of the present application will be further described in detail below in combination with the drawings and specific embodiments.

[0022] The components of the embodiments of the present application generally described and shown in the accompanying drawings can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but only represents selected embodiments of the present application.

[0023] Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative efforts fall within the scope of protection of the present application.

[0024] In the description of the present application, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "two ends", "one end", "the other end" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second" are only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0025] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0026] As shown in Figure 1 , the unmanned aerial vehicle impact vibration test system with self-adaptive adjustment provided by the present application, as shown in Figure 1 , comprises a vibration work cabinet 1, a vibration device 2 for generating vibration is fixedly installed on the side of the vibration work cabinet 1, a vibration plate 3 connected with the vibration device 2 is arranged on the top of the vibration work cabinet 1, and a spring telescopic rod 4 is fixedly installed on the top of the vibration plate 3. The vibration device 2 drives the vibration plate 3 to move.

[0027] It is worth noting that the present application is used for the unmanned aerial vehicle with front and rear gravity center offset, as shown in Figures 2 to 5 , the top of the spring telescopic rod 4 is provided with an unmanned aerial vehicle placing part 5, the unmanned aerial vehicle placing part 5 comprises a bottom plate 51 fixedly installed on the top of the spring telescopic rod 4, a guide rod 52 with a spring inside is fixedly installed on the top of the bottom plate 51, a top plate 53 is fixedly installed on the top of the guide rod 52, a gravity center deflection plate 54 for placing the unmanned aerial vehicle with front and rear gravity center offset is rotatably connected with the top plate 53 through a rotating shaft, the gravity center deflection plate 54 is fixedly connected with the rotating shaft, and the rotating shaft is rotatably connected with the top plate 53. The vibration device 2, the vibration plate 3, the spring telescopic rod 4 and the top plate 53 cooperate to generate vibration to detect the unmanned aerial vehicle.

[0028] Further, the rotating connection between the center of gravity deflection plate 54 and the top plate 53 is elastically connected with a torque spring 58, the top plate 53 adopts a box-shaped structure without cover, and there is a gap between the bottom of the center of gravity deflection plate 54 and the top plate 53. The center of gravity shift direction of the unmanned aerial vehicle is perpendicular to the external rotating shaft direction of the center of gravity deflection plate 54. Since there is a gap between the bottom of the center of gravity deflection plate 54 and the top plate 53, when the unmanned aerial vehicle is placed in the center of the center of gravity deflection plate 54, the unmanned aerial vehicle will rotate the center of gravity deflection plate 54 and compress the torque spring 58 due to the center of gravity shift, thereby adjusting the angle of the unmanned aerial vehicle. The purpose of adjusting the angle of the vibrating unmanned aerial vehicle is to adapt the gravitational moment generated by the center of gravity shift to the inclination angle of the vibrating plate, so as to accurately expose the imbalance problem, simulate the real working condition or calibrate the detection reference, and accurately position the influence of the center of gravity shift on the structural strength, vibration response and flight stability of the unmanned aerial vehicle.

[0029] A magnetic positioning member is arranged at the rotating shaft inside the top plate 53, the magnetic positioning member includes a butt joint block 59, the butt joint block 59 adopts an end tooth structure, the butt joint block 59 slides on the external rotating shaft of the center of gravity deflection plate 54, and the end of the butt joint block 59 is elastically connected with a first reset spring 510 between the center of gravity deflection plate 54. A butt joint hole 511 is formed in the inner wall of the top plate 53, and the butt joint block 59 is inserted into the butt joint hole 511. The butt joint hole 511 is provided with a plurality of butt joint holes, which are distributed in a ring shape at equal angles around the external rotating shaft of the center of gravity deflection plate 54. A triangular block-shaped transition is fixedly installed between two adjacent butt joint holes 511. The number of butt joint holes 511 is the same as the number of end teeth of the butt joint block 59. An annular electromagnet 512 is fixedly installed inside the top plate 53 and inside the plurality of butt joint holes 511.

[0030] After the center of gravity deflection plate 54 and the torque spring 58 are rotated under the influence of the gravity of the unmanned aerial vehicle, the center of gravity deflection plate 54 is stabilized and then the vibration detection step is started. The vibration device 2 is powered on first. The current passes through the annular electromagnet 512 to generate a magnetic force to attract the butt joint block 59. The annular electromagnet 512 attracts the butt joint block 59 into the butt joint hole 511. The butt joint block 59 stretches the first reset spring 510. Since a triangular block-shaped transition is fixedly installed between two adjacent butt joint holes 511, and the butt joint block 59 adopts an end tooth structure, the triangular block and the end tooth cooperate to enable the butt joint block 59 to always enter the butt joint hole 511, thereby fixing the angle of the center of gravity deflection plate 54 and avoiding the rotation of the center of gravity deflection plate 54 caused by vibration.

[0031] A groove is formed in the rotating shaft inside the top plate 53, and a convex strip is fixedly installed at the inner arc surface of the butt joint block 59. The convex strip slides along the groove. The groove and the convex strip cooperate to enable the butt joint block 59 and the rotating shaft to rotate.

[0032] The bottom of the top plate 53 is fixedly provided with a push rod 55, the bottom end of the push rod 55 is hingedly provided with a linkage rod 56, the end of the linkage rod 56 is hingedly provided with a sliding switch 57 for controlling the vibration frequency of the vibration device 2, which is slidingly arranged on the bottom of the bottom plate 51. The gravity of the unmanned aerial vehicle makes the top plate 53 compress the guide rod 52, the top plate 53 moves downward and pulls the linkage rod 56 through the push rod 55, and the movement of the linkage rod 56 makes the sliding switch 57 slide to change the vibration frequency of the vibration device 2.

[0033] In the present application, the gravity center deflection plate 54 and the torque spring 58 are matched to adjust the inclination angle of the unmanned aerial vehicle according to the gravity center of the unmanned aerial vehicle, and the gravity center offset of the unmanned aerial vehicle is adapted, so that the gravity moment generated by the gravity center offset is matched with the inclination angle of the vibration plate, thereby accurately exposing the imbalance problem and simulating the real working condition. At the same time, the top plate 53 and the guide rod 52 are matched under the action of the gravity of the unmanned aerial vehicle, the top plate 53 moves downward and changes the position of the sliding switch 57 through the push rod 55 and the linkage rod 56, thereby changing the vibration frequency of the vibration device 2 and adaptively vibrating the unmanned aerial vehicle.

[0034] As an embodiment, as shown in Figures 3 to 6 The top of the bottom plate 51 is provided with a stabilizing portion 6 for positioning the push rod 55, the stabilizing portion 6 includes two stabilizing boxes 61 symmetrically arranged with respect to the push rod 55, the inside of the stabilizing box 61 is slidingly connected with a sliding block 62, the side of the sliding block 62 is fixedly provided with a magnetic attracting member 64, the end of the magnetic attracting member 64 extends from the inside of the stabilizing box 61, the top of the bottom plate 51 and between the two stabilizing boxes 61 is fixedly provided with a bar-shaped electromagnet 65, the middle of the sliding block 62 and towards one side of the push rod 55 is fixedly provided with an intermediate block 66, and the end of the intermediate block 66 is fixedly provided with a clamping block 67.

[0035] The sliding block 62 is made of wear-resistant plastic material, the side of the sliding block 62 away from the magnetic attracting member 64 is elastically connected with a second reset spring 63 between the stabilizing box 61, the magnetic attracting member 64 is made of one of iron block, cobalt block or nickel block, before the vibration detection, the bar-shaped electromagnet 65 is electrified, the bar-shaped electromagnet 65 generates magnetic force to attract the magnetic attracting member 64, thereby making the clamping block 67 slide to the push rod 55 to clamp the push rod 55.

[0036] Further, the clamping block 67 adopts an arc-shaped structure, the inner arc surface of the clamping block 67 has the same curvature as the curvature of the push rod 55, the contact area between the clamping block 67 and the push rod 55 is increased, the outer wall of the push rod 55 is provided with a plurality of clamping grooves 68 equidistantly distributed along the axial line of the push rod 55, the inner arc surface of the clamping block 67 is provided with an arc-shaped protruding strip, and the arc-shaped protruding strip is clamped with the clamping groove 68. The arc-shaped protruding strip and the clamping groove 68 are matched to increase the clamping force of the clamping block 67 on the push rod 55.

[0037] The present application attracts the magnetism member 64 by electrifying the bar-shaped electromagnet 65, and the magnetism member 64 drives the occlusion block 67 to move by the sliding block 62, so that the two occlusion blocks 67 clamp the push rod 55, and the occlusion force of the occlusion block 67 on the push rod 55 is increased by the cooperation of the arc convex strip and the occlusion groove 68, so as to position the moving height of the gravity center deflection plate 54, avoid the height change of the gravity center deflection plate 54 when vibrating, and affect the unmanned aerial vehicle vibration detection.

[0038] As an embodiment, as shown in Figures 7 to 9 The top of the gravity center deflection plate 54 is provided with a clamp 7, the clamp 7 includes two transverse sliding plates 71 symmetrically arranged on the top of the gravity center deflection plate 54, the transverse sliding plates 71 slide left and right on the top of the gravity center deflection plate 54, the side of the two transverse sliding plates 71 facing each other is slidably connected with a longitudinal moving block 72, the side of the longitudinal moving block 72 is fixedly installed with a fixed elastic arc piece 73, the outer wall of the fixed elastic arc piece 73 is fixedly installed with a fixed block 75, and the end of the fixed elastic arc piece 73 is fixedly installed with a movable elastic arc piece 74 penetrating through the fixed block 75.

[0039] By adjusting the length of the movable elastic arc piece 74 extending out of the fixed block 75, the size of the circle surrounded by the fixed elastic arc piece 73 and the movable elastic arc piece 74 can be changed, so as to adapt to unmanned aerial vehicle landing gears of different volumes, and the larger the volume of the unmanned aerial vehicle is, the thicker the diameter of the landing gear is.

[0040] Further, the inside of the fixed block 75 is slidably connected with a pressing plate 76, a plurality of equidistantly distributed pressing grooves 78 are formed in the side of the movable elastic arc piece 74, the pressing plate 76 is meshingly connected with the pressing grooves 78, and the side, away from the pressing grooves 78, of the pressing plate 76 is rotatably connected with a screw rod 77 threadedly connected with the fixed block 75.

[0041] By rotating the screw rod 77 to adjust the connection relationship between the pressing plate 76 and the pressing grooves 78, the size of the circle surrounded by the movable elastic arc piece 74 and the fixed elastic arc piece 73 can be adjusted, and the length of the movable elastic arc piece 74 extending out is positioned by the meshing of the pressing plate 76 and the pressing grooves 78.

[0042] By rotating the screw rod 77 clockwise to make the pressing plate 76 move away from the pressing grooves 78, the length of the movable elastic arc piece 74 extending out can be adjusted, by rotating the screw rod 77 counterclockwise to make the pressing plate 76 move towards the pressing grooves 78, the pressing plate 76 is meshed with the pressing grooves 78, so as to fix the length of the movable elastic arc piece 74 extending out, and by adjusting the length of the movable elastic arc piece 74 extending out of the fixed block 75, the size of the circle surrounded by the fixed elastic arc piece 73 and the movable elastic arc piece 74 can be changed, so as to adapt to unmanned aerial vehicle landing gears of different volumes, and the larger the volume of the unmanned aerial vehicle is, the thicker the diameter of the landing gear is.

[0043] The above specific embodiments are only several optional embodiments of the present application, and based on the technical scheme of the present application and the related inspiration of the above embodiments, the person skilled in the art can make various alternative improvements and combinations on the above specific embodiments.

Claims

1. An adaptively adjustable UAV impact vibration testing system, comprising a vibration cabinet (1), wherein a vibration device (2) for generating vibration is fixedly installed on the side of the vibration cabinet (1), and a vibration plate (3) connected to the vibration device (2) is provided on the top of the vibration cabinet (1), and a spring telescopic rod (4) is fixedly installed on the top of the vibration plate (3), characterized in that, Also includes: The drone placement unit (5) includes a base plate (51) fixedly installed on the top of a spring telescopic rod (4). A guide rod (52) with a spring inside is fixedly installed on the top of the base plate (51). A top plate (53) is fixedly installed on the top of the guide rod (52). A center of gravity deflection plate (54) for placing a drone with a center of gravity shifted forward and backward is rotatably connected to the inside of the top plate (53) via a rotating shaft. A torque spring (58) is elastically connected at the rotational connection between the center of gravity deflection plate (54) and the top plate (53). A magnetic positioning component is provided at the rotating shaft inside the top plate (53). A push rod (55) is fixedly installed on the bottom of the top plate (53). A linkage rod (56) is hinged to the bottom end of the push rod (55). A sliding switch (57) for controlling the vibration frequency of the vibration device (2) that slides on the bottom of the base plate (51) is hinged to the end of the linkage rod (56). The top of the base plate (51) is provided with a stabilizing part (6) for the positioning push rod (55).

2. The UAV impact vibration testing system with adaptive adjustment according to claim 1, characterized in that, The top plate (53) adopts a box-shaped structure without a cover. There is a gap between the bottom of the center of gravity deflection plate (54) and the top plate (53). The center of gravity deflection direction of the UAV is perpendicular to the external rotation axis direction of the center of gravity deflection plate (54). There is a gap between the bottom end of the push rod (55) and the vibration plate (3).

3. The UAV impact vibration testing system with adaptive adjustment according to claim 2, characterized in that, The magnetic positioning component includes a docking block (59), which has an end tooth structure. The docking block (59) slides on the outer shaft of the center of gravity deflection plate (54). A first reset spring (510) is elastically connected between the end of the docking block (59) and the center of gravity deflection plate (54). The inner wall of the top plate (53) is provided with a docking hole (511), and the docking block (59) is inserted into the docking hole (511).

4. The UAV impact vibration testing system with adaptive adjustment according to claim 3, characterized in that, Multiple docking holes (511) are provided and are distributed in an annular shape at equal angles around the outer axis of the center of gravity deflection plate (54). A triangular block-shaped transition is fixedly installed between two adjacent docking holes (511). The number of docking holes (511) is the same as the number of teeth at the end of the docking block (59). The same annular electromagnet (512) is fixedly installed inside the top plate (53) and inside the multiple docking holes (511).

5. The UAV impact vibration testing system with adaptive adjustment according to claim 4, characterized in that, The top plate (53) has a groove on the rotating shaft inside, and a protrusion is fixedly installed on the inner arc surface of the docking block (59), which slides along the groove.

6. The UAV impact vibration testing system with adaptive adjustment according to claim 5, characterized in that, The stabilizing part (6) includes two stabilizing boxes (61) symmetrically arranged about the push rod (55). A slider (62) is slidably connected inside the stabilizing box (61). A magnet (64) is fixedly installed on the side of the slider (62). The end of the magnet (64) extends out from the inside of the stabilizing box (61). A bar electromagnet (65) is fixedly installed on the top of the base plate (51) and between the two stabilizing boxes (61). A middle block (66) is fixedly installed in the middle of the slider (62) and on the side facing the push rod (55). A biting block (67) is fixedly installed at the end of the middle block (66).

7. The UAV impact vibration testing system with adaptive adjustment according to claim 6, characterized in that, The biting block (67) adopts an arc-shaped structure. The inner arc surface of the biting block (67) has the same arc as the arc surface of the push rod (55). The outer wall of the push rod (55) is provided with a plurality of biting grooves (68) evenly distributed along the axis of the push rod (55). The inner arc surface of the biting block (67) is provided with an arc-shaped protrusion. The arc-shaped protrusion engages with the biting groove (68).

8. The UAV impact vibration testing system with adaptive adjustment according to claim 7, characterized in that, The slider (62) is made of wear-resistant plastic. A second reset spring (63) is elastically connected between the side of the slider (62) away from the magnetizing element (64) and the stabilizing box (61). The magnetizing element (64) is made of one of iron, cobalt or nickel.

9. The UAV impact vibration testing system with adaptive adjustment according to claim 8, characterized in that, The top of the center of gravity deflection plate (54) is provided with a clamp (7), the clamp (7) includes transverse sliding plates (71) symmetrically arranged on the top of the center of gravity deflection plate (54), the transverse sliding plates (71) slide left and right on the top of the center of gravity deflection plate (54), and the two transverse sliding plates (71) are slidably connected to a longitudinal moving block (72) on the opposite side. A fixed elastic arc plate (73) is fixedly installed on the side of the longitudinal moving block (72), a fixed block (75) is fixedly installed on the outer wall of the fixed elastic arc plate (73), and a movable elastic arc plate (74) passing through the fixed block (75) is fixedly installed at the end of the fixed elastic arc plate (73).

10. The UAV impact vibration testing system with adaptive adjustment according to claim 9, characterized in that, The fixed block (75) is internally slidably connected to a pressure plate (76), and the side of the movable elastic arc plate (74) is provided with multiple equally spaced pressure grooves (78). The pressure plate (76) is engaged with the pressure grooves (78), and the side of the pressure plate (76) away from the pressure grooves (78) is rotatably connected to a screw (77) that is threadedly connected to the fixed block (75).

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