An unmanned aerial vehicle target aircraft defect detection apparatus and method

Abstract

The application discloses a kind of unmanned vehicle target aircraft defect detection equipment and method, including machine table, the top of the machine table is detachably installed lower mould, lower mould is opened in with the appearance of target aircraft tail body lower half portion matched recessed cavity;Lifting assembly is installed at the rear position of the top of the machine table, upper die is connected on the output end of the lifting assembly, and the bottom wall of the upper die has the pressing surface matched with the appearance of target aircraft tail body upper half portion;Vertical plate is fixed on the left and right sides of the top of the machine table respectively, and visual detection component one and visual detection component two are installed in vertical direction with interval in vertical plate.The application is fixed by profiling pressing, and the flexibility of fuselage is retained, bilateral synchronous loading bending torque transmission and visual subarea detection separation bending, to solve the defect that traditional single-side independent normal loading cannot simulate V-shaped tail wing stress coupling state.

Description

Technical Field

[0001] This invention relates to the field of target drone testing technology, specifically to a defect detection device and method for unmanned aerial vehicle (UAV) target drones. Background Technology

[0002] Unmanned aerial vehicle (UAV) target drones are specialized UAVs designed to simulate enemy aerial targets and provide live-fire training and performance testing for air defense weapon systems. By replicating radar reflection signals, infrared radiation characteristics, and maneuvers, and even simulating complex scenarios such as electronic jamming and formation flight, they meet diverse training and testing needs. Many adopt low-cost, expendable designs to adapt to high-intensity live-fire training scenarios. The V-shaped tail fin is a key structural component that requires compressive strength testing to verify structural strength and connection reliability. During testing, the tail fin is fixed to the test fixture in its actual assembly state, with its root secured to the fuselage connection section using a special clamp to ensure no additional stress interference. Then, a load simulating aerodynamic pressure is applied to the tail fin surface using a loading device, with the load applied in stages according to the design load until the specified limit load is reached. Simultaneously, the deformation, stress changes, and connection status of the tail fin are monitored to check for permanent deformation, cracks, delamination, or connection failure. For example, the target drone production wing compression testing device disclosed in authorization announcement number CN121113668B includes a testing platform, a testing mechanism, and a bearing mechanism. The testing mechanism and the bearing mechanism are installed on the testing platform, and the bearing mechanism is located in the middle of the testing mechanism. The bearing mechanism includes a bearing platform, a bearing frame, and a bearing shell. The bearing platform is installed on the surface of the testing platform, the bearing frame is installed on the bearing platform through a support column, and the bearing shell is disposed on the surface of the bearing frame. The bearing frame and the bearing shell form a cavity to provide movement space for the iron cores. The above solution can automatically adjust the extension distance of each iron core according to the wing curvature through the independent extension and retraction movement of multiple iron cores and the meshing mechanism of the linkage disk and the long gear to achieve fitting and positioning. However, the above solution independently loads one side of the wing surface or only applies the normal load perpendicular to the wing surface, ignoring the torque transmission generated by the load through the tail section of the fuselage. It is difficult to apply to the two tail wings arranged and connected in a V-shape at the tail end of the UAV target drone, and it is difficult to judge the deformation of the wing root and the tail end fuselage when the wingtips of the two tail wings are subjected to force. Summary of the Invention

[0003] The purpose of this invention is to provide a defect detection device and method for unmanned aerial vehicle (UAV) target drones. The connecting section between the tail fuselage and the V-shaped tail wings is placed in the cavity of the lower mold, which fits snugly against the tail fuselage. Then, the lifting assembly drives the upper pressure mold to move downward to cooperate with the lower mold to fix the tail fuselage of the UAV target drone. The two-stage force-adding bending assemblies on the left and right sides are activated by the central control box to work synchronously. Each of the two-stage force-adding bending assemblies applies force to one tail wingtip. The visual inspection assembly one and visual inspection assembly two respectively detect the upper and lower edges of the tail wing root, thereby determining the deformation of the wing root and the fuselage under the force applied to the tail wingtip, so as to solve the problems mentioned in the background art.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a defect detection device for unmanned aerial vehicle (UAV) target drones, comprising: The machine platform has a lower mold detachably installed on its top, and the lower mold has a cavity that matches the shape of the lower half of the target machine's tail section. The lifting assembly installed at the rear of the top of the machine tool is connected to the upper pressure mold on the output end of the lifting assembly. The bottom wall of the upper pressure mold has a pressing surface that matches the shape of the upper half of the tail section of the target machine. The vertical plates are fixed to the left and right sides of the top of the machine tool respectively. Visual inspection component one and visual inspection component two are installed at intervals along the vertical direction on the vertical plates. The tail fin on the corresponding side passes through the space between visual inspection component one and visual inspection component two. The two-stage force-adding bending assembly is installed at the upper position of the surface of the vertical plate. The driving end of the two-stage force-adding bending assembly abuts against the wingtip of the corresponding side tail fin and applies thrust. The central control box is installed on the outer wall of one side of the machine tool. The central control box is electrically connected to the lifting assembly, vision inspection assembly one, vision inspection assembly two, and the two-stage force-applying bending assembly.

[0005] Preferably, the lifting assembly includes a rear mast fixed at the rear of the top of the machine platform, an H-shaped island fixed on the rear mast, and a servo electric cylinder installed at the center of the top of the H-shaped island. The piston rod of the servo electric cylinder passes downward through the H-shaped island and is fixed to an upper mold base. The upper mold and the upper mold base are detachably connected.

[0006] Preferably, the left and right inner walls of the upper mold base are provided with rectangular grooves extending along the Y-axis, and the left and right outer walls of the upper die are integrally formed with protrusions for sliding cooperation with the rectangular grooves, and the protrusions are bolted to the upper mold base.

[0007] Preferably, the visual inspection component includes a fixed platform plate fixed at an upper position on the surface of the upright plate, a movable platform plate disposed diagonally above the fixed platform plate, and a hinge seat installed on the back of the movable platform plate and connected to the fixed platform plate. At least one CCD visual camera is installed on the outer wall of the movable platform plate.

[0008] Preferably, the two-stage force-applying bending assembly includes an outer inclined platform fixedly connected to a fixed platform plate, a rotating shaft rotatably mounted in the outer inclined platform along the Y-axis direction via bearings, an L-shaped long arm fixed to the end of the rotating shaft, and a double-cylinder pneumatic bending mechanism fixed to the L-shaped long arm. A rotary drive mechanism is installed on the outer wall of the outer inclined platform on the side away from the L-shaped long arm, and the output shaft of the rotary drive mechanism is fixedly connected to the other end of the rotating shaft via a coupling.

[0009] Preferably, guide columns extending upward through the H-shaped island platform are fixed on both the left and right sides of the top of the upper mold base.

[0010] Preferably, the dual-cylinder pneumatic bending mechanism includes a U-shaped frame fixed to the bottom of the L-shaped long arm, two cylinders hinged to the L-shaped long arm, and a final shaft rotatably mounted on the left and right inner walls of the U-shaped frame. One end of the final shaft is fixed with an upper rocker arm, the upper end of which connects with the piston rod end of the cylinder, and the other end of the final shaft is fixed with a connecting rod bracket.

[0011] Preferably, the top ends of the two connecting rod supports are fixed with rubber seats.

[0012] Preferably, the lower surface of the upper mold and the inner wall of the cavity of the lifting assembly are both lined with a flexible material layer.

[0013] This invention also provides a defect detection method for unmanned aerial vehicle (UAV) target drones, using the aforementioned equipment, comprising the following steps: S1: The tail section of the target drone, along with the assembled V-shaped tail fins, is hoisted onto the platform. The drone's attitude is slowly adjusted so that the fuselage falls horizontally into the cavity of the lower mold. When the tail section is fully seated in the cavity and can no longer sink, the positioning is complete. The camera of visual inspection component one faces the upper edge of the tail fin root on that side, and the camera of visual inspection component two faces the lower edge of the tail fin root. The focal length, aperture, and shooting angle of each camera are adjusted to ensure that the image clearly captures the specific marking points or natural texture features of the upper and lower edges of the tail fin root. When the tail fin tilts upward, its fin root is exactly located in the intersection of the lines of sight of the two cameras. S2: The command is issued through the central control box to start the lifting component and drive the upper pressure mold to move vertically downward until the lower surface of the upper pressure mold is in close contact with the upper contour of the tail body of the target machine, and together with the lower mold, they form a ring-shaped wrapping and pressing on the tail body. S3: According to the testing requirements, the staff set the loading force value and holding time of the two-stage force-adding bending components on the left and right sides. Then, the two-stage force-adding bending components on the left and right sides are started to work synchronously. The force-applying end of each two-stage force-adding bending component abuts against its corresponding tail wing tip and gradually increases the thrust at a preset rate. During the loading process, the displacement of the upper and lower edges of the wing root is observed in real time through the screen of the central control box to see if it is stable and to check for any abnormal noises or sudden deformation until the specified limit load is reached. S4: After reaching the ultimate load and completing the load maintenance, continue recording by visual inspection component one and visual inspection component two. After unloading, compare the initial zero point with the residual displacement after unloading by playing back the image. If there is still a significant positive or negative offset at the upper or lower edge of the wing root, it indicates that permanent deformation has occurred. Check whether there are gaps, delamination or cracks on the wing root and fuselage contact surface. Finally, the staff raises the upper pressure mold and removes the target machine from the cavity. Use a portable ultrasound or endoscope to perform a non-destructive re-inspection of the wing root to confirm whether there is any hidden damage.

[0014] Compared with the prior art, the beneficial effects of the present invention are: the defect detection equipment and method for unmanned aerial vehicle target drones, by setting up a structure in which a lower mold, a lifting component, an upper pressure mold, a vision inspection component one, a vision inspection component two, and a two-stage force-adding bending component cooperate with each other, solves the defect that traditional single-sided independent normal loading cannot simulate the force of V-tail wing. The cavity of the lower mold fits perfectly with the tail section of the target drone. Combined with the vertical clamping of the upper mold driven by the lifting assembly, contour positioning and uniform clamping are achieved. The two-stage force-adding bending components on the left and right sides are controlled by the central control box to work synchronously, each applying force to the tip of a tail wing, replicating the spatial force state of the V-tail wing under symmetrical maneuvering. This ensures that the bending moment, shear force, and torque transmission path of the left and right wing roots remain consistent. Finally, in the inspection stage, visual inspection is arranged on the upper and lower edges of both wing roots to obtain the deformation state of both sides at the same time and determine the symmetry of the entire tail structure. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the main structure of the present invention; Figure 2 This is a schematic diagram of the three-dimensional structure of the present invention. Figure 1 ; Figure 3 This is a schematic diagram of the three-dimensional structure of the present invention. Figure 2 ; Figure 4 This is a side cross-sectional view of the present invention. Figure 5 This is a three-dimensional cross-sectional structural diagram of the present invention; Figure 6 This is a three-dimensional structural diagram of the lifting component of the present invention in the assembled state with the above-mentioned pressure mold; Figure 7 This is a schematic diagram of the three-dimensional structure of the two-stage force-applying bending assembly of the present invention. Figure 1 ; Figure 8 For the present invention Figure 2 Enlarged structural diagram at point A in the middle; Figure 9 This is a schematic diagram of the three-dimensional structure of the two-stage force-applying bending assembly of the present invention.Figure 2 .

[0016] In the diagram: 1. Machine base; 2. Lower mold; 3. Rear gate; 4. Lifting assembly; 41. H-shaped island platform; 42. Servo electric cylinder; 43. Upper mold base; 44. Rectangular groove; 5. Upper pressure mold; 6. Vertical plate; 7. Vision inspection assembly one; 71. Fixed platform; 72. Hinge seat; 73. Movable platform; 74. CCD vision camera; 8. Vision inspection assembly two; 9. Two-stage force-applying bending assembly; 91. Outer inclined platform; 92. L-shaped long arm; 93. U-shaped frame; 94. Rotary drive mechanism; 95. Rotating shaft; 96. Cylinder; 97. End shaft; 98. Upper rocker arm; 99. Connecting rod bracket; 910. Rubber seat; 10. Central control box; 11. Cavity. Detailed Implementation

[0017] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0018] Example 1, by Figures 1 to 3 The present invention includes a machine base 1, and a lower mold 2 is detachably installed on the top of the machine base 1. The lower mold 2 has a cavity 11 that matches the shape of the lower half of the tail section of the target machine. The lifting assembly 4 is installed at the rear of the top of the machine tool 1. The upper pressure mold 5 is connected to the output end of the lifting assembly 4. The bottom wall of the upper pressure mold 5 has a pressing surface that matches the shape of the upper half of the tail section of the target machine. The lower surface of the upper pressure mold 5 and the inner wall of the cavity 11 of the lifting assembly 4 are lined with a flexible material layer. The lower mold 2 fits into the upper mold 5 through the contoured cavity 11 and is vertically pressed, so as to achieve non-destructive, uniform and repeatable clamping of the composite material thin-walled fuselage. This simulates the boundary constraints between the tail section of the fuselage and the internal support structure during flight, while retaining the degree of freedom to bend and twist when the fuselage is under stress. The vertical plates 6 are fixed to the left and right sides of the top of the machine base 1 respectively. Visual inspection component 1 7 and visual inspection component 2 8 are installed at intervals along the vertical direction on the vertical plates 6. The tail fin on the corresponding side passes through the visual inspection component 1 7 and visual inspection component 2 8. The secondary force-adding bending assembly 9 is installed at the upper position on the surface of the vertical plate 6. The driving end of the secondary force-adding bending assembly 9 abuts against the wingtip of the corresponding side tail fin and applies thrust. The central control box 10 is installed on the outer wall of one side of the machine tool 1. The central control box 10 is electrically connected to the lifting assembly 4, vision inspection assembly 1 7, vision inspection assembly 2 8, and two-stage force-applying bending assembly 9 respectively. The central control box 10 integrates a programmable logic controller, a multi-channel force value acquisition card, a vision image processing module, and a human-machine interaction touch screen. It includes servo valves and motor drivers that drive the left and right two-stage force-applying bending assemblies 9, as well as relays that control the lifting assembly 4.

[0019] This embodiment of a defect detection method for a drone target drone, using the aforementioned equipment, includes the following steps: S1: The tail section of the target drone, along with the assembled V-shaped tail fins, is hoisted onto the platform. The drone's attitude is slowly adjusted so that the fuselage falls horizontally into the cavity of the lower mold. When the tail section is fully seated in the cavity and can no longer sink, the positioning is complete. The camera of visual inspection component one faces the upper edge of the tail fin root on that side, and the camera of visual inspection component two faces the lower edge of the tail fin root. The focal length, aperture, and shooting angle of each camera are adjusted to ensure that the image clearly captures the specific marking points or natural texture features of the upper and lower edges of the tail fin root. When the tail fin tilts upward, its fin root is exactly located in the intersection of the lines of sight of the two cameras. S2: The command is issued through the central control box to start the lifting component and drive the upper pressure mold to move vertically downward until the lower surface of the upper pressure mold is in close contact with the upper contour of the tail body of the target machine, and together with the lower mold, they form a ring-shaped wrapping and pressing on the tail body. S3: According to the testing requirements, the staff set the loading force value and holding time of the two-stage force-adding bending components on the left and right sides. Then, the two-stage force-adding bending components on the left and right sides are started to work synchronously. The force-applying end of each two-stage force-adding bending component abuts against its corresponding tail wing tip and gradually increases the thrust at a preset rate. During the loading process, the displacement of the upper and lower edges of the wing root is observed in real time through the screen of the central control box to see if it is stable and to check for any abnormal noises or sudden deformation until the specified limit load is reached. S4: After reaching the ultimate load and completing the load maintenance, continue recording by visual inspection component one and visual inspection component two. After unloading, compare the initial zero point with the residual displacement after unloading by playing back the image. If there is still a significant positive or negative offset at the upper or lower edge of the wing root, it indicates that permanent deformation has occurred. Check whether there are gaps, delamination or cracks on the wing root and fuselage contact surface. Finally, the staff raises the upper pressure mold and removes the target machine from the cavity. Use a portable ultrasound or endoscope to perform a non-destructive re-inspection of the wing root to confirm whether there is any hidden damage.

[0020] Example 2, based on Example 1, is... Figure 4 , Figure 5 and Figure 6The lifting assembly 4 includes a rear door frame 3 fixed at the rear of the top of the machine base 1, an H-shaped island platform 41 fixed on the rear door frame 3, and a servo electric cylinder 42 installed at the center of the top of the H-shaped island platform 41. The piston rod of the servo electric cylinder 42 passes downward through the H-shaped island platform 41 and is fixed with an upper mold base 43. The left and right sides of the top of the upper mold base 43 are fixed with guide columns that pass upward through the H-shaped island platform 41. The upper mold 5 is detachably connected to the upper mold base 43. The tail of the target machine is placed into the cavity 11 of the lower mold 2. The depth and contour of the cavity 11 ensure that the machine body is automatically aligned. Then, the servo cylinder 42 is activated through the central control box 10 to work. The servo cylinder 42 drives the upper mold base 43 and the upper pressure mold 5 to move down until the upper pressure mold 5 is pressed on the tail of the target machine to prevent the machine body from sliding during subsequent loading. The upper mold base 43 has rectangular grooves 44 extending along the Y-axis on both the left and right inner walls. The upper mold 5 has protrusions integrally formed on both the left and right outer walls for sliding cooperation with the rectangular grooves 44. The protrusions are bolted to the upper mold base 43. Since the protrusions are integrally formed on the side walls of the upper mold 5, the protrusions slide into the rectangular grooves 44 of the upper mold base 43. The upper mold base 43 and the protrusions are locked with bolts. The lifting assembly 4 and the upper mold 5 can be replaced to adapt to the tail shape of different target models. The tail fin passes between two cameras, with the upper and lower cameras facing the upper and lower edges of the wing root, respectively, to obtain high-resolution local images. The vision inspection component 7 includes a fixed platform 71 fixed to the upper part of the surface of the vertical plate 6, a movable platform 73 set diagonally above the fixed platform 71, and a hinge seat 72 installed on the back of the movable platform 73 and connected to the fixed platform 71. At least one CCD vision camera 74 is installed on the outer wall of the movable platform 73. Taking the vision inspection component 7 as an example, the hinge seat 72 adjusts the angle of the movable platform 73 and the CCD vision camera 74 on the movable platform 73. The CCD vision camera 74 is connected to the image acquisition card in the central control box 10 through a data cable. During the loading process, the image acquisition card in the central control box 10 performs pixel-level positioning of the feature points in each frame of the image and calculates the displacement relative to the initial position. The displacement of the upper edge measuring point mainly reflects the combined effect of wing root bending and fuselage torsion, while the displacement of the lower edge measuring point provides the opposite torsional information.

[0021] Example 3, based on Example 2, by Figure 7 , Figure 8 and Figure 9The two-stage force-applying bending assembly 9 includes an outer inclined platform 91 fixedly connected to a fixed platform plate 71, a rotating shaft 95 rotatably mounted in the outer inclined platform 91 along the Y-axis direction via bearings, an L-shaped long arm 92 fixed to the end of the rotating shaft 95, and a double-cylinder pneumatic bending mechanism fixed to the L-shaped long arm 92. A rotary drive mechanism 94 is installed on the outer wall of the outer inclined platform 91 away from the L-shaped long arm 92. The output shaft of the rotary drive mechanism 94 is fixedly connected to the other end of the rotating shaft 95 via a coupling. The dual-cylinder pneumatic bending mechanism includes a U-shaped frame 93 fixed at the bottom of the L-shaped long arm 92, two cylinders 96 hinged on the L-shaped long arm 92, and a final shaft 97 rotatably mounted on the left and right inner walls of the U-shaped frame 93. One end of the final shaft 97 is fixed with an upper rocker arm 98, the upper end of the upper rocker arm 98 is connected to the piston rod end of the cylinder 96, and the other end of the final shaft 97 is fixed with a connecting rod bracket 99. The top of the two connecting rod brackets 99 is fixed with a rubber seat 910. When the two-stage afterburning bending assembly 9 is working, the piston rod of cylinder 96 gradually extends. During this process, the piston rod of cylinder 96 drives the end shaft 97 to rotate through the upper rocker arm 98. Then, the connecting rod bracket 99 and the rubber seat 910 gradually contact the wingtip under the rotation of the end shaft 97, so as to stimulate the deformation and failure of the wing root and the tail section of the fuselage in the bending state, until the stroke of cylinder 96 is completely finished. When applying the second-stage force, the cylinder 96 remains stationary, and the rotary drive mechanism 94 is activated. The rotary drive mechanism 94 drives the L-shaped long arm 92 to rotate through the rotating shaft 95. At this time, the U-shaped frame 93 and the components mounted on it deflect around the axis of the rotating shaft 95, thereby increasing the thrust until the ultimate load of the tail fin is reached.

[0022] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0023] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A defect detection device for unmanned aerial vehicle (UAV) target drones, characterized in that, include: The machine base (1) has a lower mold (2) detachably installed on its top end. The lower mold (2) has a cavity (11) that matches the shape of the lower half of the target machine's tail section. The lifting assembly (4) is installed at the rear of the top of the machine (1), and the upper pressure mold (5) is connected to the output end of the lifting assembly (4). The bottom wall of the upper pressure mold (5) has a pressing surface that matches the shape of the upper half of the tail section of the target machine. The vertical plates (6) are fixed to the left and right sides of the top of the machine (1). Visual inspection component one (7) and visual inspection component two (8) are installed at intervals along the vertical direction on the vertical plates (6). The tail fin on the corresponding side passes through the visual inspection component one (7) and visual inspection component two (8). The secondary force-adding bending assembly (9) is installed at the upper position on the surface of the vertical plate (6). The driving end of the secondary force-adding bending assembly (9) abuts against the wingtip of the corresponding side tail fin and applies thrust. The central control box (10) is installed on the outer wall of one side of the machine (1). The central control box (10) is electrically connected to the lifting assembly (4), vision inspection assembly one (7), vision inspection assembly two (8), and two-stage force-applying bending assembly (9).

2. The UAV target drone defect detection equipment according to claim 1, characterized in that: The lifting assembly (4) includes a rear mast (3) fixed at the rear end of the machine base (1), an H-shaped island platform (41) fixed on the rear mast (3), and a servo electric cylinder (42) installed at the center of the top of the H-shaped island platform (41). The piston rod of the servo electric cylinder (42) passes downward through the H-shaped island platform (41) and is fixed with an upper mold base (43). The upper mold (5) is detachably connected to the upper mold base (43).

3. The UAV target drone defect detection equipment according to claim 2, characterized in that: The upper mold base (43) is provided with rectangular grooves (44) extending along the Y-axis on both the left and right inner walls. The upper mold (5) is integrally formed with protrusions for sliding cooperation with the rectangular grooves (44) on both the left and right outer walls. The protrusions are bolted to the upper mold base (43).

4. The UAV target drone defect detection device according to claim 1, characterized in that: The visual inspection component 1 (7) includes a fixed platform (71) fixed at an upper position on the surface of the upright plate (6), a movable platform (73) set diagonally above the fixed platform (71), and a hinge seat (72) installed on the back of the movable platform (73) and connected to the fixed platform (71). At least one CCD visual camera (74) is installed on the outer wall of the movable platform (73).

5. The UAV target drone defect detection equipment according to claim 4, characterized in that: The two-stage force-applying bending assembly (9) includes an outer inclined platform (91) fixedly connected to a fixed platform plate (71), a rotating shaft (95) rotatably mounted in the outer inclined platform (91) along the Y-axis direction via bearings, an L-shaped long arm (92) fixed at the end of the rotating shaft (95), and a double-cylinder pneumatic bending mechanism fixed on the L-shaped long arm (92). A rotary drive mechanism (94) is installed on the outer wall of the outer inclined platform (91) away from the L-shaped long arm (92). The output shaft of the rotary drive mechanism (94) is fixedly connected to the other end of the rotating shaft (95) via a coupling.

6. The UAV target drone defect detection device according to claim 3, characterized in that: The upper mold base (43) has guide columns fixed on both the left and right sides of its top end, which extend upward through the H-shaped island platform (41).

7. The UAV target drone defect detection device according to claim 5, characterized in that: The dual-cylinder pneumatic bending mechanism includes a U-shaped frame (93) fixed at the bottom of the L-shaped long arm (92), two cylinders (96) hinged on the L-shaped long arm (92), and a final shaft (97) rotatably mounted on the left and right inner walls of the U-shaped frame (93). One end of the final shaft (97) is fixed with an upper rocker arm (98), the upper end of the upper rocker arm (98) and the piston rod end of the cylinder (96) are connected, and the other end of the final shaft (97) is fixed with a connecting rod bracket (99).

8. The UAV target drone defect detection device according to claim 7, characterized in that: The top ends of the two connecting rod supports (99) are fixed with rubber seats (910).

9. The UAV target drone defect detection equipment according to claim 1, characterized in that: The lower surface of the upper mold (5) and the inner wall of the cavity (11) of the lifting assembly (4) are both lined with a flexible material layer.

10. A method for detecting defects in a drone target drone, using the equipment described in any one of claims 1-9, characterized in that: Includes the following steps: S1: The tail fuselage of the target drone, together with the assembled V-shaped tail wings, is hoisted onto the platform (1). The attitude of the target drone is slowly adjusted so that the fuselage falls horizontally into the cavity (11) of the lower mold (2). When the tail fuselage is completely seated in the cavity (11) and can no longer sink, the positioning is completed. The camera of the visual inspection component 1 (7) faces the upper edge of the tail wing root on this side, and the camera of the visual inspection component 2 (8) faces the lower edge of the wing root. The focal length, aperture and shooting angle of each camera are adjusted to ensure that the image clearly captures the specific marking points or natural texture features of the upper and lower edges of the wing root. When the tail wing tilts upward, its wing root is exactly located in the line-of-sight intersection area of ​​the two cameras. S2: The central control box (10) issues a command to start the lifting assembly (4) and drive the upper pressure mold (5) to move vertically downward until the lower surface of the upper pressure mold (5) is in close contact with the upper contour of the tail body of the target machine, and together with the lower mold, forms a ring-shaped wrapping and pressing on the tail body. S3: According to the testing requirements, the staff set the loading force value and holding time of the two-stage force-adding bending components (9) on the left and right sides, and then started the two-stage force-adding bending components (9) on the left and right sides to work synchronously. The force-applying end of each two-stage force-adding bending component (9) abuts against the corresponding tail wing tip and gradually increases the thrust according to the preset rate. During the loading process, the displacement of the upper and lower edges of the wing root is observed in real time through the screen of the central control box (10) to check whether there are any abnormal noises or sudden deformations until the specified limit load is reached. S4: After reaching the ultimate load and completing the load protection, continue recording by visual inspection component 1 (7) and visual inspection component 2 (8). After unloading, compare the initial zero point with the residual displacement after unloading by playing back the image. If there is still an obvious positive or negative offset on the upper or lower edge of the wing root, it indicates that permanent deformation has occurred. Check whether there are gaps, delamination or cracks on the wing root and fuselage contact surface. Finally, the staff raises the upper pressure mold (5) and takes the target machine out of the cavity (11). Use portable ultrasound or endoscope to perform non-destructive re-inspection of the wing root interior to confirm whether there is any hidden damage.

Images