An inspection device for the strength of a carbon fiber shell of a drone and its usage method

Abstract

The present invention relates to the field of UAV detection, and particularly to a UAV carbon fiber shell strength inspection device and its usage method, including a base, a lifting platform, a mounting plate, a moving component, a fixed rod, a pressing head, a first electric push rod, a sliding disk, etc.; the base is fixedly connected with the lifting platform; the telescopic part of the lifting platform is fixedly connected with the mounting plate; the mounting plate is connected with the moving component; the moving component is connected with the fixed rod, and the moving component is used to drive the fixed rod to move; the fixed rod is fixedly connected with the pressing head; several first electric push rods are fixedly connected to the fixed rod; the telescopic parts of all the first electric push rods are commonly fixedly connected with a sliding disk. By alternately using the pressing head and the ejector rod, the overall strength of the UAV carbon fiber shell and the structural strength of each part are detected. The overall detection is more stable and accurate. Moreover, through automated detection, no manual operation is required, and compared with manual detection, the detection efficiency is higher.

Description

Technical Field

[0001] The present invention relates to the field of UAV detection, and particularly relates to a strength inspection device for a UAV carbon fiber shell and a using method thereof. Background Art

[0002] The UAV carbon fiber shell is usually assembled by two upper and lower half shells. When it is produced, it is usually necessary to inspect its strength to ensure the production quality of the UAV carbon fiber shell. The existing detection methods often simply use a stamping device to press the whole shell to detect its strength. However, the UAV carbon fiber shell is usually integrally formed. During the manufacturing process, due to uneven distribution of the injected resin or insufficient exhaust, etc., there is too little resin in some local areas, or small pores are formed, resulting in lower strength in some local areas of the UAV carbon fiber shell. The existing methods can only detect the strength of the whole UAV carbon fiber shell and cannot detect the strength of its local areas, making the strength detection result inaccurate. And the integrally formed UAV carbon fiber shell generally consists of a fuselage and multiple wings, and its structural shape is not a regular shape. During actual detection, it is difficult to stably detect each part of the UAV carbon fiber shell, and the operation is inconvenient. When manually detecting, the detection efficiency of the UAV carbon fiber shell is low, which is not conducive to actual use. Summary of the Invention

[0003] In order to overcome the defect that the existing methods can only detect the strength of the whole UAV carbon fiber shell and cannot detect the strength of its local areas, resulting in inaccurate strength detection results, the present invention provides a strength inspection device for a UAV carbon fiber shell and a using method thereof.

[0004] Technical Solution: A strength inspection device for a UAV carbon fiber shell includes a base, a lifting table, a mounting plate, a moving component, a fixed rod, and a pressing head; the base is fixedly connected with the lifting table; the telescopic part of the lifting table is fixedly connected with the mounting plate; the mounting plate is connected with the moving component; the moving component is connected with the fixed rod, and the moving component is used to drive the fixed rod to move; the fixed rod is fixedly connected with the pressing head; it further includes a first electric push rod, a sliding disk, a top rod, a laser detector, and a placement system; the fixed rod is fixedly connected with several first electric push rods; the telescopic parts of all the first electric push rods are commonly fixedly connected with a sliding disk, and the sliding disk is slidably connected with the pressing head; the sliding disk is fixedly connected with the top rod; the sliding disk is fixedly connected with two laser detectors for detecting damage to the UAV shell, and both the top rod and the laser detectors are slidably connected within the pressing head; the base is connected with a placement system for placing and fixing the UAV shell.

[0005] Furthermore, particularly preferably, the bottom of the top rod is lower than the bottom of the laser detector.

[0006] In addition, it is particularly preferred that the placement system includes mounting columns, a placement tray, support airbags, support rods, fixing airbags, and electric splints; the base is fixedly connected with mounting columns; the mounting columns are rotatably connected with a placement tray through spherical gears, and a driving motor for driving the rotation of the spherical gears is arranged inside the mounting columns; a support airbag is fixedly connected to the middle of the placement tray; a number of support rods are fixedly connected to the placement tray, and the support rods are arranged as telescopic rods; a number of fixing airbags are fixedly connected to each support rod; and a number of electric splints are arranged on the placement tray.

[0007] In addition, it is particularly preferred that it further includes an electric push rod II, a limit frame, and a bending assembly; the mounting column is fixedly connected with the electric push rod II; the telescopic part of the electric push rod II is fixedly connected with a limit frame for placing the wing of the drone housing; and the limit frame is connected with a bending assembly for bending the wing of the drone housing.

[0008] In addition, it is particularly preferred that it further includes telescopic springs, clamping rods, sliding plates, and elastic telescopic rods; a number of telescopic springs are fixedly connected to both sides of each limit frame; a number of clamping rods are slidably connected to each limit frame, and the clamping rods are fixedly connected with the telescopic springs; a sliding plate is slidably connected to both sides of each limit frame; and two elastic telescopic rods are fixedly connected to each sliding plate, and the elastic telescopic rods are fixedly connected with the limit frame.

[0009] In addition, it is particularly preferred that the limit frame is provided with a first rubber cushion block.

[0010] In addition, it is particularly preferred that the bending assembly includes a motor and a rotating plate; two motors are fixedly connected to each limit frame; two rotating plates for bending the wing of the drone housing are rotatably connected to each limit frame, and the output shaft of the motor is fixedly connected with the rotating plate.

[0011] In addition, it is particularly preferred that it further includes a baffle; a baffle is fixedly connected to each rotating plate.

[0012] In addition, it is particularly preferred that the rotating plate is provided with a second rubber cushion block.

[0013] In addition, it is particularly preferred that a method for using an inspection device for the strength of a carbon fiber housing of a drone includes the following steps: Step 1: First, manually place the carbon fiber housing of the drone on the mounting column and fix it, and then control the lower pressing head to move downward to press and detect the strength of the overall structure of the housing body.

[0014] Step 2: Then control the ejector rod to extend, detect the strength of the local area of the housing body through the ejector rod, and during the detection process, control the driving motor in the mounting column to drive the spherical gear to rotate, and the spherical gear drives the placement tray and the fixed drone housing to rotate, so that the local area to be detected can always be vertically aligned with the ejector rod, thereby making the detection result of the local area strength more accurate, and detecting the strength of the wing structure of the carbon fiber housing of the drone through the ejector rod.

[0015] Step 3: By controlling the rotation of the rotating plate, the bending resistance of the wing of the carbon fiber shell of the drone is detected.

[0016] Compared with the prior art, the present invention has the following advantages:

[0017] By alternately using the pressing head and the ejector rod, the overall strength of the carbon fiber shell of the drone and the structural strength of each part are detected. The overall detection is more stable and accurate. Moreover, through automatic detection, manual operation is not required, and the detection efficiency is higher compared with manual detection.

[0018] The electric push rod II drives the limiting frame to move, causing the placement plate to rotate around the mounting column, and then making the entire drone shell rotate into an inclined state, that is, making the local edge of the fuselage of the drone shell to be pressed and detected rotate perpendicular to the ejector rod. At this time, control the ejector rod to move downward to press and detect it, making the strength detection of the local area of the drone shell fuselage accurate; and through the movement of the clamping rod and the limiting of the limiting frame, the two sides of the wing of the drone detection shell are limited and fixed, so that when the ejector rod can accurately move downward to press the wing of the drone detection shell later, all the pressing forces can be applied to the wing to detect its structural strength and reduce the error of the detection result.

[0019] By controlling the motor to drive the rotating plate to rotate, the rotating plate rotates to bend the wing of the drone detection shell, causing the wing of the drone detection shell to be bent by its own force, thereby detecting its bending resistance strength. Description of the Drawings

[0020] Figure 1 It is a schematic structural diagram disclosed by the strength inspection device for the carbon fiber shell of the drone of the present invention;

[0021] Figure 2 It is a schematic structural diagram of the moving component disclosed by the strength inspection device for the carbon fiber shell of the drone of the present invention;

[0022] Figure 3 It is a cross-sectional view of the pressing head disclosed by the strength inspection device for the carbon fiber shell of the drone of the present invention;

[0023] Figure 4 It is a state diagram of the movement of the sliding plate, the ejector rod, and the laser detector disclosed by the strength inspection device for the carbon fiber shell of the drone of the present invention;

[0024] Figure 5 It is a schematic structural diagram of the placement system disclosed by the strength inspection device for the carbon fiber shell of the drone of the present invention;

[0025] Figure 6Schematic diagram of the combined structure of the limit frame, telescopic spring, clamping rod, sliding plate and elastic telescopic rod disclosed in the drone carbon fiber shell strength inspection device of the present invention;

[0026] Figure 7 Schematic diagram of the bending component structure disclosed in the drone carbon fiber shell strength inspection device of the present invention;

[0027] Figure 8 Schematic diagram of the structure of the object to be processed disclosed in the drone carbon fiber shell strength inspection device of the present invention.

[0028] The markings of each component in the drawings are as follows: 1 - base, 2 - lifting platform, 3 - mounting plate, 4 - fixed rod, 5 - pressing head, 6 - electric push rod 1, 7 - sliding disk, 8 - ejector rod, 9 - laser detector, 101 - electric guide rail 1, 102 - moving block 1, 103 - electric guide rail 2, 104 - moving block 2, 111 - mounting column, 112 - placing plate, 11201 - support airbag, 11202 - support rod, 11203 - fixed airbag, 113 - electric clamp, 114 - electric push rod 2, 115 - limit frame, 116 - telescopic spring, 117 - clamping rod, 118 - sliding plate, 119 - elastic telescopic rod, 201 - motor, 202 - rotating plate, 203 - baffle, 01 - rubber cushion block 1, 02 - rubber cushion block 2, 100 - drone shell. Detailed implementation manners

[0029] To make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the drawings. It is hereby declared that the orientation terms such as up, down, left, right, front, back, inside and outside that appear or will appear in the present invention are only based on the drawings of the present invention, and they do not specifically limit the present invention.

[0030] Embodiment 1

[0031] A drone carbon fiber shell strength inspection device, as Figures 1-6 and Figure 8 shown, includes a base 1, a lifting platform 2, a mounting plate 3, a moving component, a fixed rod 4 and a pressing head 5; the base 1 is fixedly connected to the lifting platform 2; the telescopic part of the lifting platform 2 is fixedly connected to the mounting plate 3; the mounting plate 3 is connected to the moving component; the moving component is connected to the fixed rod 4, and the moving component is used to drive the fixed rod 4 to move; the fixed rod 4 is fixedly connected to the pressing head 5;

[0032] It also includes an electric push rod 1-6, a sliding disc 7, a push rod 8, a laser detector 9 and a placement system; two electric push rods 1-6 are fixedly connected to the fixed rod 4; the telescopic parts of all the electric push rods 1-6 are jointly fixedly connected with a sliding disc 7, and the sliding disc 7 is slidably connected with the lower pressing head 5; the sliding disc 7 is fixedly connected with a push rod 8; two laser detectors 9 are fixedly connected to the sliding disc 7, and the push rod 8 and the laser detector 9 are both slidably connected within the lower pressing head 5; the base 1 is connected with a placement system.

[0033] The bottom of the push rod 8 is lower than the bottom of the laser detector 9. When the push rod 8 and the laser detector 9 extend out together and the push rod 8 contacts the drone housing 100, the laser detector 9 is located above it to detect the pressing situation and prevent the laser detector 9 from being knocked and damaged.

[0034] The placement system includes a mounting column 111, a placement disc 112, a support airbag 11201, a support rod 11202, a fixed airbag 11203 and an electric clamping plate 113; the mounting column 111 is fixedly connected to the base 1; the mounting column 111 is rotatably connected with the placement disc 112 through a spherical gear, and a drive motor 201 for driving the spherical gear to rotate is arranged inside the mounting column 111; a support airbag 11201 is fixedly connected to the middle of the placement disc 112; several support rods 11202 are fixedly connected to the placement disc 112, and the support rods 11202 are set as telescopic rods; several fixed airbags 11203 are fixedly connected to each support rod 11202; several electric clamping plates 113 are arranged on the placement disc 112.

[0035] It also includes an electric push rod 2-114, a limiting frame 115 and a bending assembly; the electric push rod 2-114 is fixedly connected to the mounting column 111; the telescopic part of the electric push rod 2-114 is fixedly connected with a limiting frame 115; the limiting frame 115 is connected with a bending assembly.

[0036] It also includes a telescopic spring 116, a clamping rod 117, a sliding plate 118 and an elastic telescopic rod 119; several telescopic springs 116 are fixedly connected to both sides of each limiting frame 115; several clamping rods 117 are slidably connected to each limiting frame 115, and the clamping rods 117 are fixedly connected with the telescopic springs 116; a sliding plate 118 is slidably connected to both sides of each limiting frame 115; two elastic telescopic rods 119 are fixedly connected to each sliding plate 118, and the elastic telescopic rods 119 are fixedly connected with the limiting frame 115.

[0037] The limiting frame 115 is provided with a rubber pad 1-01, which can protect the wing part and reduce the damage to the wing of the drone housing 100 during detection.

[0038] The moving component includes an electric guide rail 101, a moving block 102, an electric guide rail 103 and a moving block 104; two electric guide rails 101 are fixedly connected to the mounting plate 3; each electric guide rail 101 is slidably connected to a moving block 102; the two moving blocks 102 are jointly fixedly connected to an electric guide rail 103; the electric guide rail 103 is slidably connected to a moving block 104, and the moving block 104 is fixedly connected to the fixed rod 4.

[0039] The working steps of the above embodiment are as follows: First, manually place the fuselage of the drone housing 100 on the placement plate 112, as Figure 3 and Figure 5 shown, and place the four wings of the drone housing 100 on the support rods 11202 respectively. The support rods 11202 are telescopic rods, and the operator can adjust the length of the support rods 11202 according to the wing length of the drone housing 100. Then, control the movement of the electric clamp 113 to fix the fuselage of the drone housing 100, control the inflation of the support airbag 11201 to support the inside of the fuselage of the drone housing 100, and control the inflation of the fixing airbag 11203 to fix the wings of the drone housing 100. Then, control the moving block 102 to drive the electric guide rail 103 and other connected parts to move forward or backward along the electric guide rail 101, and control the moving block 104 to drive the fixed rod 4 and the pressing head 5, and other connected parts to move left or right along the electric guide rail 103. By the mutual movement of the moving block 102 and the moving block 104, drive the fixed rod 4 and the pressing head 5 to move directly above the fuselage of the drone housing 100. Then, control the lifting platform 2 to drive the mounting plate 3, the fixed rod 4 and the pressing head 5 to move downward, so that the pressing head 5 moves downward to press the fuselage of the drone housing 100, and by controlling the magnitude of the pressure applied by the pressing head 5, the strength of the fuselage of the drone housing 100 can be inspected.

[0040] However, during the detection, it can only detect the overall strength of the fuselage of the drone housing 100 and cannot detect the strength of its local area, resulting in inaccurate strength detection results. Therefore, after the pressing head 5 moves downward to complete the pressing inspection, control the lifting platform 2 to drive the pressing head 5 to move upward and reset. Then, control the first electric push rod 6 to drive the sliding disk 7, the ejector rod 8 and the laser detector 9 to move downward, so that the sliding disk 7 moves into contact with the pressing head 5. At this time, the ejector rod 8 and the laser detector 9 extend out of the pressing head 5, as Figure 4As shown, then control the lifting platform 2 to drive the pressing head 5 and the ejector rod 8 to move downward, and control the cooperation between the first moving block 102 and the second moving block 104 to drive the ejector rod 8 to move, so as to press each part of the fuselage of the UAV shell 100. By moving the ejector rod 8 to press a local area of the fuselage of the UAV shell 100, the strength of its local area is detected, making the strength detection result of the UAV shell 100 more accurate; at the same time, in order to reduce wind resistance, the fuselage of the UAV carbon fiber shell is usually set to be streamlined, and the overall shell surface is arc-shaped. When the ejector rod 8 moves downward to press, the ejector rod 8 cannot vertically press each local area of the fuselage of the UAV shell 100, and the applied pressing force cannot all act on the surface of the fuselage of the UAV shell 100, making the local area strength detection inaccurate; therefore, when controlling the ejector rod 8 to move downward to press the edge of the fuselage of the UAV shell 100, first control the drive motor 201 in the mounting column 111 to drive the ball gear to rotate, and the ball gear drives the placement disk 112 and the fixed UAV shell 100 to rotate, so that the overall UAV shell 100 rotates to an inclined state, that is, the local edge of the fuselage of the UAV shell 100 to be pressed and detected rotates to be perpendicular to the ejector rod 8. At this time, control the ejector rod 8 to move downward to press and detect it. With the support of the support airbag 11201, the strength detection of the local area of the fuselage of the UAV shell 100 is accurate. And perform the same operation, control the drive motor 201 in the mounting column 111 to drive the UAV shell 100 to rotate at various angles, and press and detect each arc-shaped surface; and during the detection process, control the laser detector 9 to work in real time to monitor the surface of the UAV shell 100 and monitor the damage that occurs during the strength inspection process, so as to check which part of the UAV shell 100 has poor strength.

[0041] After the inspection of the fuselage of the UAV shell 100 is completed, then the strength of the wing of the UAV shell 100 is detected; control the drive motor 201 in the mounting column 111 to drive the placement disk 112 and the fixed UAV shell 100 to rotate horizontally, so that the wing of the UAV shell 100 rotates to directly above the limit frame 115. Then control the second electric push rod 114 to drive the limit frame 115 and other connected parts to move upward, so that the wing of the UAV shell 100 is placed on the limit frame 115, as Figure 5 and Figure 6As shown in the figure, then control the first moving block 102 and the second moving block 104 to cooperate with each other to drive the pressing head 5 to move above the limiting frame 115, so that the ejector rod 8 is directly above the wing of the UAV shell 100 within the limiting frame 115. Then control the lifting platform 2 to drive the pressing head 5 and the ejector rod 8 to move downward. The ejector rod 8 moves downward into the limiting frame 115 to press and detect the wing of the placed UAV shell 100, so as to check the strength of the wing of the UAV shell 100. However, when the ejector rod 8 moves downward to press the wing of the UAV shell 100 within the limiting frame 115, since the wing of the UAV shell 100 is not a solid structure, when it is pressed from top to bottom, the two sides of the wing will extend outward, making it difficult for all the force applied by the pressing of the ejector rod 8 to act on the wing, resulting in easy error in the detection of its structural strength. Therefore, when the lifting platform 2 drives the pressing head 5 and the ejector rod 8 to move downward, the pressing head 5 first contacts the sliding plate 118. As the pressing head 5 moves downward, the pressing head 5 presses the sliding plate 118, causing the sliding plate 118 to move downward and the elastic telescopic rod 119 to contract. The sliding plate 118 moves downward to squeeze the clamping rod 117, causing the telescopic spring 116 to contract and deform. The clamping rod 117 moves toward the wing of the UAV shell 100 within the limiting frame 115. When the clamping rod 117 contacts the two sides of the wing, the pressing head 5 stops moving downward. Then the clamping rod 117 moves to cooperate with the limitation of the limiting frame 115 to limit and fix the two sides of the wing of the UAV shell 100, so that when the ejector rod 8 moves downward to press the wing of the UAV shell 100 later, all the pressing force can be applied to the wing to detect its structural strength and reduce the error of the detection result. And when the pressing of the ejector rod 8 is completed, control the ejector rod 8 to move upward. Then continue to control the pressing head 5 to move downward. The pressing head 5 continues to drive the sliding plate 118 to move downward to squeeze the clamping rod 117, causing the clamping rod 117 to move to apply a squeezing force to the two sides of the wing, so that the two sides of the wing deform toward the middle of the wing and the middle of the wing bulges upward, so as to detect the deformation condition of the wing of the UAV shell 100 under extrusion in different directions and fully detect the structural strength of the wing of the UAV shell 100. And perform the same operation. Control the placing plate 112 to drive the UAV shell 100 to rotate horizontally in turn, place the wing on the limiting frame 115, and perform strength detection. In this way, by alternately using the pressing head 5 and the ejector rod 8, the overall strength of the UAV carbon fiber shell and the structural strength of each part are detected. The overall detection is more stable and accurate. And through automatic detection, no manual operation is required. Compared with manual detection, its detection efficiency is higher.

[0042] Embodiment 2

[0043] On the basis of Embodiment 1, as Figures 6-8 shown, the bending assembly includes a motor 201 and a rotating plate 202; two motors 201 are fixedly connected to each limiting frame 115; two rotating plates 202 are rotatably connected to each limiting frame 115, and the output shaft of the motor 201 is fixedly connected to the rotating plate 202.

[0044] It further includes a baffle 203; each rotating plate 202 is fixedly connected with a baffle 203.

[0045] A second rubber cushion block 02 is arranged on the rotating plate 202, which can protect the wing when bending the wing of the UAV shell 100 and reduce the damage to the wing during detection.

[0046] A method for using an inspection device for the strength of a UAV carbon fiber shell includes the following steps:

[0047] Step 1: First, manually place the UAV carbon fiber shell on the mounting post 111 and fix it. Then, control the pressing head 5 to move down to press and detect the strength of the overall structure of the shell body.

[0048] Step 2: Then, control the ejector rod 8 to extend, and detect the strength of the local area of the shell body through the ejector rod 8. During the detection process, control the drive motor 201 in the mounting post 111 to drive the ball gear to rotate. The ball gear drives the placement disk 112 and the fixed UAV shell 100 to rotate, so that the local area to be detected can always be vertically aligned with the ejector rod 8, making the detection result of the local area strength more accurate, and detecting the wing structure strength of the UAV carbon fiber shell through the ejector rod 8.

[0049] Step 3: Control the rotating plate 202 to rotate to detect the anti-bending performance of the wing of the UAV carbon fiber shell.

[0050] On the basis of the above embodiment, when the UAV collides during actual use, the wing part on the outside is more likely to be impacted. Therefore, when detecting the strength of the UAV carbon fiber shell, it is also necessary to detect the anti-bending strength of its wing itself; when the ejector rod 8 completes the detection of the structure strength of the wing of the UAV shell 100, the clamping rod 117 then controls the motor 201 to drive the rotating plate 202 to rotate. The rotating plate 202 rotates to bend the wing of the UAV shell 100, so that the wing of the UAV shell 100 is bent by its own force, thereby detecting its anti-bending strength; and, a baffle 203 is arranged on the rotating plate 202. During detection, the baffle 203 blocks the wing of the UAV shell 100 to prevent the wing from being torsionally bent upward and falling off the rotating plate 202 and the limiting frame 115 when detecting the wing of the UAV shell 100.

[0051] Step 2: Then, control the ejector rod 8 to extend, and detect the strength of the local area of the outer shell fuselage through the ejector rod 8. During the detection process, control the drive motor 201 in the mounting column 111 to drive the ball gear to rotate. The ball gear drives the placement disk 112 and the fixed drone outer shell 100 to rotate, so that the local area to be detected can always be vertically aligned with the ejector rod 8, making the detection result of the local area strength more accurate, and detect the wing structure strength of the carbon fiber outer shell of the drone through the ejector rod 8.

[0052] Step 3: Detect the bending resistance of the wing of the carbon fiber outer shell of the drone by controlling the rotation of the rotating plate 202.

[0053] It should be understood that this embodiment is only used to illustrate the present invention and not to limit the scope of the present invention. In addition, it should be understood that after reading the content taught by the present invention, those skilled in the art can make various changes or modifications to the present invention, and these equivalent forms also fall within the scope defined by the appended claims of this application.

Claims

1. An inspection device for the strength of a carbon fiber shell of a drone, comprising a base (1), a lifting platform (2), a mounting plate (3), a moving component, a fixing rod (4) and a pressing head (5); the base (1) is fixedly connected with the lifting platform (2); the telescopic part of the lifting platform (2) is fixedly connected with the mounting plate (3); the mounting plate (3) is connected with the moving component; the moving component is connected with the fixing rod (4), and the moving component is used to drive the fixing rod (4) to move; the fixing rod (4) is fixedly connected with the pressing head (5); characterized in that, It also includes an electric push rod 1 (6), a sliding disk (7), a push rod (8), a laser detector (9) and a placement system; the fixed rod (4) is fixedly connected with a plurality of electric push rods 1 (6); the telescopic parts of all the electric push rods 1 (6) are jointly fixedly connected with a sliding disk (7), and the sliding disk (7) is slidably connected with the lower pressing head (5); the sliding disk (7) is fixedly connected with a push rod (8); the sliding disk (7) is fixedly connected with two laser detectors (9) for detecting damage to the outer shell (100) of the drone, and both the push rod (8) and the laser detector (9) are slidably connected within the lower pressing head (5); the base (1) is connected with a placement system for placing and fixing the outer shell (100) of the drone; The bottom of the push rod (8) is lower than the bottom of the laser detector (9); The placement system includes a mounting column (111), a placement disk (112), a support airbag (11201), a support rod (11202), a fixing airbag (11203) and an electric clamp (113); the base (1) is fixedly connected with a mounting column (111); the mounting column (111) is rotatably connected with a placement disk (112) through a spherical gear, and a driving motor (201) for driving the spherical gear to rotate is arranged inside the mounting column (111); a support airbag (11201) is fixedly connected to the middle of the placement disk (112); the placement disk (112) is fixedly connected with a plurality of support rods (11202), and the support rods (11202) are arranged as telescopic rods; each support rod (11202) is fixedly connected with a plurality of fixing airbags (11203); a plurality of electric clamps (113) are arranged on the placement disk (112); It also includes an electric push rod 2 (114), a limit frame (115) and a bending assembly; the mounting column (111) is fixedly connected with an electric push rod 2 (114); the telescopic part of the electric push rod 2 (114) is fixedly connected with a limit frame (115) for placing the wing of the outer shell (100) of the drone; the limit frame (115) is connected with a bending assembly for bending the wing of the outer shell (100) of the drone; It also includes a telescopic spring (116), a clamping rod (117), a sliding plate (118) and an elastic telescopic rod (119); a plurality of telescopic springs (116) are fixedly connected to both sides of each limit frame (115); a plurality of clamping rods (117) are slidably connected to each limit frame (115), and the clamping rods (117) are fixedly connected with the telescopic springs (116); a sliding plate (118) is slidably connected to both sides of each limit frame (115); two elastic telescopic rods (119) are fixedly connected to each sliding plate (118), and the elastic telescopic rods (119) are fixedly connected with the limit frame (115).

2. The strength inspection device for the carbon fiber outer shell of a drone according to claim 1, characterized in that, The limit frame (115) is provided with a rubber cushion block 1 (01).

3. The strength inspection device for the carbon fiber outer shell of an unmanned aerial vehicle according to claim 2, wherein, The bending assembly includes a motor (201) and a rotating plate (202); two motors (201) are fixedly connected to each limit frame (115); two rotating plates (202) for bending the wing of the outer shell (100) of the drone are rotatably connected to each limit frame (115), and the output shaft of the motor (201) is fixedly connected with the rotating plate (202).

4. The strength inspection device for the carbon fiber outer shell of a drone according to claim 3, characterized in that, It further includes a baffle (203); each rotating plate (202) is fixedly connected with a baffle (203).

5. An inspection device for the strength of a carbon fiber outer shell of a drone according to claim 4, characterized in that, Rubber pads II (02) are arranged on the rotating plate (202).

6. An inspection device for the strength of a carbon fiber outer shell of a drone according to claim 5, characterized in that, A method for using an inspection device for the strength of a carbon fiber shell of an unmanned aerial vehicle includes the following steps: Step 1: First, manually place the carbon fiber shell of the unmanned aerial vehicle on the mounting post (111) and fix it. Then, control the lower pressing head (5) to move downward to press and detect the strength of the overall structure of the shell body. Step 2: Then, control the ejector rod (8) to extend, and use the ejector rod (8) to detect the strength of a local area of the shell body. During the detection process, control the drive motor (201) in the mounting post (111) to drive the ball gear to rotate. The ball gear drives the placement disk (112) and the fixed unmanned aerial vehicle shell (100) to rotate, so that the local area to be detected can always be vertically aligned with the ejector rod (8), making the detection result of the local area strength more accurate, and use the ejector rod (8) to detect the strength of the wing structure of the carbon fiber shell of the unmanned aerial vehicle. Step 3: Control the rotating plate (202) to rotate to detect the bending resistance of the wing of the carbon fiber shell of the unmanned aerial vehicle.

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