Aircraft body scribing device and method suitable for inner space of aircraft

Abstract

The invention relates to the technical field of aircraft manufacturing and assembling, and discloses an aircraft body lineation device and method suitable for an inner layer space of an aircraft, and the device comprises a fixing mechanism, a driving device and a lineation assembly; the fixing mechanism comprises a fixing block assembly installed on an aircraft shell and a movable plate assembly arranged on the fixing block assembly. The driving device comprises a translation assembly which is assembled on the moving plate assembly and can move in the length direction of the moving plate assembly, a driving mechanism fixed to the translation assembly and a guiding mechanism. The scribing assembly comprises a moving shaft assembly assembled on the guide mechanism in a sliding mode, a connecting piece assembly connected with the driving mechanism and the moving shaft assembly, and a scribing head module arranged on the moving shaft assembly. The driving mechanism drives the connecting piece assembly to drive the moving shaft assembly to move, so that the scribing head module abuts against the aircraft shell, and the translation assembly drives the scribing head module to complete scribing when moving. The position and the walking distance of the marking head in the inner layer space of the airplane can be visually observed, accurate marking data can be obtained, and the marking precision is remarkably improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft manufacturing and assembly technology, and more specifically to a fuselage marking device and method suitable for the internal space of an aircraft. Background Technology

[0002] When assembling aircraft structures by riveting or bolting, workers need to mark lines on the aircraft fuselage to determine the mounting hole positions. After the positioning holes are set, holes are drilled using a drilling device, and finally, rivets or bolts are riveted or bolted.

[0003] Existing aircraft fuselage scribing devices are mostly caliper-like, capable of precisely scribing lines on exposed, relatively open areas of the aircraft fuselage. However, when encountering confined spaces, the scribing device must be fully inserted into the narrow space, making it impossible for operators to observe the overall structure of the equipment, the position of the scribing head, or the distance it has traveled. As a result, scribing often relies on the operator's years of experience, significantly impacting accuracy. Summary of the Invention

[0004] To address the shortcomings and deficiencies of existing technologies, this invention proposes a scribing device and method suitable for the inner space of an aircraft. The scribing head of the scribing device can extend into the inner space of the aircraft, while the remaining part is on the outside of the aircraft. During scribing, the position and distance traveled of the scribing head in the inner space of the aircraft can be directly observed, thereby obtaining accurate scribing data and significantly improving the scribing accuracy of the aircraft body. To achieve the above-mentioned objectives, the technical solution of the present invention is as follows: This invention discloses a fuselage marking device suitable for the interior space of an aircraft, the technical solution of which is as follows: the aircraft fuselage marking device consists of the following components: The fixing mechanism includes a fixing block assembly mounted on the aircraft shell and a movable plate assembly mounted on the fixing block assembly on the side away from the aircraft shell; A driving device, the driving device comprising a translation component mounted on a movable plate assembly and movable along the length direction of the movable plate assembly, a driving mechanism fixed on the translation component, and a guiding mechanism mounted on the translation component; A scribing assembly, comprising a movable shaft assembly slidably mounted on the guide mechanism, a connecting piece assembly mounted on the end face of the movable shaft assembly and connected to the drive mechanism, and a scribing head module mounted on the other end of the movable shaft assembly; wherein... The drive mechanism drives the connecting plate assembly to move in a direction perpendicular to the moving plate assembly, causing the moving shaft assembly to move synchronously in the same direction on the guide mechanism, so that the scribing head module on the moving shaft assembly comes into contact with the scribing position of the aircraft body in the inner space of the aircraft. Then, when the translation component moves along the length direction of the moving plate assembly, it drives the drive mechanism, the moving shaft assembly and the scribing head module to move synchronously, and the scribing head module completes the scribing on the aircraft body. During the scribing process, the cameras distributed next to the scribing head module capture images of the aircraft inner space near the scribing head module in real time and transmit them to the external mobile device.

[0005] Preferably, the fixing block assembly includes a fixing block and a vacuum suction cup assembly mounted on the fixing block for adsorbing the aircraft shell; the vacuum suction cup assembly includes a hollow box and a suction cup, an exhaust port and an air inlet disposed on the hollow box and communicating with the inner cavity of the hollow box, the air inlet being threadedly connected to a sealing cap; the hollow box is mounted on the fixing block.

[0006] Preferably, the movable plate assembly includes a movable plate disposed on the side of the fixed block away from the vacuum suction cup assembly, and the movable plate has a strip-shaped opening through the center along its long side.

[0007] Preferably, the fixed block is provided with a first sliding groove, and the movable plate is provided with a first slider that is slidably inserted into the first sliding groove. The end face of the first slider is also provided with a first threaded hole that penetrates the first slider.

[0008] Preferably, the translation component includes a translation plate and a connecting block inserted into the strip opening. The connecting block has second sliders on both sides, and the opening has second grooves on both sides. The second sliders are slidably installed in the second grooves, and the connecting block can slide within the strip opening.

[0009] Preferably, the drive mechanism includes a second motor mounted on a translation plate and a second lead screw fixed on the output shaft of the second motor.

[0010] Preferably, the guiding mechanism includes a guide shaft disposed on the translation plate and parallel to the second lead screw, and the end face of the guide shaft is provided with a guide hole along the axial direction.

[0011] Preferably, the movable shaft assembly includes a movable shaft and a mounting groove formed on the end face of the movable shaft. The movable shaft is slidably inserted into a guide hole, and a pressure sensor and a spring abutting against the pressure sensor are provided in the mounting groove.

[0012] Preferably, the connecting piece assembly includes a first connecting piece mounted on the movable shaft at the end away from the mounting groove. The first connecting piece has a second threaded hole, and a second lead screw is screwed into the second threaded hole.

[0013] Preferably, the marking head module includes a second connecting piece inserted into the mounting groove and abutting against a spring, and a straight cylinder fixed on the second connecting piece. The end of the straight cylinder has a cone head located outside the mounting groove.

[0014] Preferably, the marking assembly further includes an end cap module, which includes an end cap fixed to the opening of the mounting groove and a connecting hole opened on the end face of the end cap. The straight cylinder passes through the connecting hole, and the end cap is also equipped with a camera.

[0015] Preferably, the outer wall of the guide shaft is also provided with a finger groove. Preferably, the fixing mechanism further includes a transmission assembly, which includes a first motor mounted on the side of the fixing block and a first lead screw connected to the output end of the first motor, with the other end of the first lead screw screwed into the first threaded hole of the first slider.

[0016] Preferably, the camera is surrounded by LED beads.

[0017] Based on the same inventive concept, another aspect of the present invention discloses a method for marking lines on the fuselage of an aircraft, applicable to the interior space of an aircraft. This method is implemented using the aforementioned aircraft fuselage marking device and includes the following steps: Step S1. Assemble the scribing device onto the aircraft fuselage shell to be scribed using the fixed block assembly. Adjust the position of the drive mechanism and guide mechanism by sliding the translation component on the sliding plate assembly, so that the scribing head module installed on the guide mechanism is aligned with the scribing position on the fuselage in the inner space of the aircraft. Step S2. Start the drive mechanism, which drives the moving shaft assembly to move on the guide mechanism, so that the scribing head module on the moving shaft assembly extends into the inner space of the aircraft and contacts and abuts against the scribing position on the fuselage. Step S3. The handheld guide mechanism drives the translation component to move on the moving plate component, and simultaneously drives the moving axis component and the scribing head module to move. The scribing head module scribes lines on the surface of the aircraft. During the scribing process, the camera next to the scribing head module captures images of the inner space of the aircraft body and transmits the images to the mobile terminal via the network for the operator to observe. At the same time, the lighting beads distributed around the camera provide supplementary lighting during the shooting process to obtain a clearer image of the inner space.

[0018] The beneficial effects of this invention are: 1. The scribing head of the scribing device of this invention can extend into the inner space of the aircraft, while the remaining components are fixed to the outside of the aircraft. A camera is integrated beside the scribing head module. During the scribing process, the camera can capture and transmit images of the inner space in real time to an external mobile device, allowing operators outside the aircraft to clearly and intuitively observe the precise position of the scribing head. This invention achieves visualization and precision in scribing operations within confined spaces, completely eliminating the previous reliance on personal experience, significantly improving scribing accuracy, and ultimately significantly improving aircraft assembly quality.

[0019] 2. This invention employs a vacuum suction cup assembly as the fixing mechanism for the entire scribing device, enabling it to quickly and firmly adhere the entire device to the aircraft outer shell (skin). Vacuum suction not only avoids surface damage or deformation caused by clamping or binding, but also provides a stable foundation for subsequent longitudinal movement of the translational components and vertical feed of the drive mechanism. This ensures the uniformity and stability of the entire process from external operation to internal scribing, thereby guaranteeing high-precision scribing results.

[0020] 3. This invention incorporates a pressure sensor and a spring within the mounting slot of the moving shaft assembly, forming an intelligent buffer and feedback mechanism. When the conical tip of the scribing head module abuts against the machine body surface, the spring compresses, and the pressure sensor detects the pressure value in real time, maintaining a constant, optimal scribing pressure. This structure effectively adapts to minor unevenness on the machine body surface, ensuring uniform pressure during scribing. This results in consistent, clear, and continuous lines, avoiding workpiece damage caused by pressure fluctuations during manual operation, such as scribing that is too shallow, discontinuous, or too deep.

[0021] 4. This invention employs a transmission assembly consisting of a first motor and a first lead screw for fine-tuning the position of the scribing head, and a drive mechanism consisting of a second motor and a second lead screw for controlling the vertical feed of the scribing head. Throughout the scribing process, the operator can achieve precise positioning mainly by observing the screen on the mobile device and controlling the motor, reducing reliance on the operator's personal experience. Furthermore, the entire device is located in an open space outside the aircraft fuselage, making operation more convenient and labor-saving.

[0022] 5. The present invention has illumination lamps arranged around the camera to ensure the imaging quality of the camera in the dim inner space, thereby ensuring the high accuracy of the line drawing results. Attached Figure Description

[0023] The foregoing and hereinafter detailed description of the invention becomes clearer when read in conjunction with the following drawings, in which: Figure 1 This is a schematic diagram of the marking device of the present invention; Figure 2This is a schematic diagram of the fixed block assembly structure of the present invention; Figure 3 This is a schematic diagram of the mobile board assembly structure of the present invention; Figure 4 This is a schematic diagram of the transmission component structure of the present invention; Figure 5 This is a schematic diagram of the drive device structure of the present invention; Figure 6 This is a schematic diagram of the scribing component structure of the present invention; Figure 7 This is a cross-sectional schematic diagram of the movable shaft assembly of the present invention; Figure 8 This is a schematic diagram of the marking head module structure of the present invention; Figure 9 This is a schematic diagram of the end cap module structure of the present invention; Figure 10 This is a schematic diagram of the vacuum suction cup assembly structure of the present invention.

[0024] In the picture: 100. Fixing mechanism; 110. Fixing block assembly; 111. Fixing block; 112. Vacuum suction cup assembly; 112a. Hollow box; 112b. Suction cup; 112c. Exhaust port; 112d. Air inlet; 113. First slide rail; 120. Moving plate assembly; 121. Moving plate; 122. Second slide rail; 123. First slider; 124. First threaded hole; 130. Transmission assembly; 131. First motor; 132. First lead screw; 200. Drive device; 210. Translation assembly; 211. Translation plate; 212. Connecting block; 213. Second slider; 214. Motor mounting plate ; 220, Drive mechanism; 221, Second motor; 222, Second lead screw; 230, Guide mechanism; 231, Guide shaft; 232, Finger groove; 233, Guide hole; 300, Marking assembly; 310, Moving shaft assembly; 311, Moving shaft; 312, Mounting groove; 313, Pressure sensor; 320, Connecting piece assembly; 321, First connecting piece; 322, Second threaded hole; 330, Spring; 340, Marking head module; 341, Second connecting piece; 342, Straight cylinder; 343, Conical head; 350, End cap module; 351, End cap; 352, Connecting hole; 353, Camera. Detailed Implementation

[0025] To enable those skilled in the art to better understand the technical solutions of this invention, specific embodiments will be used to further illustrate the technical solutions for achieving the objectives of this invention. It should be noted that the technical solutions claimed by this invention include, but are not limited to, the following embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without inventive effort should fall within the scope of protection of this invention. The present invention first discloses a fuselage marking device suitable for the interior space of an aircraft. Figure 1 This is a schematic diagram of the marking device, such as... Figure 1 As shown, the aircraft fuselage marking device includes: A fixing mechanism 100 for supporting and fixing the marking device during marking, the fixing mechanism 100 includes a fixing block assembly 110 mounted on the aircraft shell and a movable plate assembly 120 mounted on the fixing block assembly 110 on the side away from the aircraft shell. The driving device 200 includes a translation component 210 mounted on the movable plate assembly 120 and capable of moving up and down along the movable plate assembly 120, a driving mechanism 220 fixed on the translation component 210, and a guide mechanism 230 mounted on the translation component 210 and parallel to the driving mechanism 220. The marking assembly 300 includes a movable shaft assembly 310 slidably mounted on the guide mechanism 230, a connecting piece assembly 320 mounted at one end of the movable shaft assembly 310, and a marking head module 340 mounted at the other end of the movable shaft assembly 310. The connecting piece assembly 320 is also connected to a drive mechanism 220. The drive mechanism 200 drives the movable shaft assembly 310 to reciprocate on the guide mechanism 230 through the connecting piece assembly 320, so that the marking head module 340 located at the end of the movable shaft assembly 310 abuts against or moves away from the marking position on the aircraft body.

[0026] Specifically, the above-mentioned marking device has the following working principle and process: The drive mechanism 220 drives the connecting piece assembly 320 to move in a direction perpendicular to the moving plate assembly 120, thereby causing the moving shaft assembly 310 to move synchronously in the same direction on the guide mechanism 230. This causes the scribing head module 340 on the moving shaft assembly 310 to come into contact with the scribing position on the fuselage in the inner space of the aircraft. Then, when the translation assembly 210 moves up and down along the moving plate assembly 120, it drives the drive mechanism 220, the moving shaft assembly 310, and the scribing head module 340 to move synchronously, and the scribing head module 340 completes the scribing on the outer shell of the aircraft fuselage.

[0027] Figure 2 Please refer to the schematic diagram of the fixed block assembly structure of the present invention. Figure 2The fixing block assembly 110 consists of a fixing block 111 and a vacuum suction cup assembly 112 mounted on the fixing block 111 near the side of the aircraft shell. The vacuum suction cup assembly 112 includes a hollow box 112a, suction cups 112b evenly arranged on one side of the hollow box 112a and communicating with the inner cavity of the hollow box 112a, an exhaust port 112c arranged at the bottom of the hollow box 112a and communicating with the inner cavity of the hollow box 112a, and an air inlet 112d arranged at the bottom edge of the hollow box 112a and communicating with the inner cavity of the hollow box 112a. A sealing cap is threadedly connected to the air inlet 112d to seal the air inlet 112d.

[0028] In practical use, the vacuum pump is installed on the exhaust port 112c, and the suction cup 112b is attached to the aircraft fuselage. The power supply of the vacuum pump is turned on, and a vacuum is created at the connection between the hollow box 112a, the suction cup 112b, and the aircraft fuselage. The negative pressure is used to adsorb the hollow box 112a onto the fuselage, and the vacuum suction cup assembly 112 is energized and adsorbed onto the aircraft fuselage. The fixing block 111 connected to it is also fixed to the aircraft fuselage. The fixing block 111 serves as a component supporting the drive device 200 and the marking assembly 300. During use, the above two structures are fixed to the aircraft fuselage. When removing the marking device, simply unscrew the sealing cap at the air inlet 112d. External air enters the inner cavity of the hollow box 112a through the air inlet 112d, eliminating the negative pressure in the inner cavity of the hollow box 112a, allowing the hollow box 112a along with the entire marking device to be removed from the aircraft fuselage.

[0029] Figure 3 Please refer to the schematic diagram of the mobile board assembly structure of the present invention. Figure 3 The movable plate assembly 120 includes a movable plate 121 disposed on the fixed block 111 on the side away from the vacuum suction cup assembly 112. The movable plate 121 has a through-elongated opening at its center along its length. The translation component 210 is slidably fitted into the elongated opening and can move within it. The movable plate 121 is also provided with a first slider 123. A first groove 113 is provided on one side of the fixed block 111. The first slider 123 is slidably fitted into the first groove 113. The movable plate 121 can move relative to the fixed block 121 along the direction of the first groove 113. The fixed block assembly 110, consisting of the fixed block 111 and the vacuum suction cup assembly 112, is symmetrically arranged in two sets at both ends of the movable plate 121. The two ends of the movable plate 121 are respectively provided with a first slider 123, which is fitted into the first groove 113 of the fixed block 111 at the corresponding position.

[0030] Furthermore, to better control the sliding displacement of the moving plate 121 relative to the fixed block 111, the first slider 123 is provided with a first threaded hole 124 penetrating both end faces along the axial direction, and a transmission mechanism 130 for controlling the sliding of the moving plate 121 relative to the fixed block 111 is installed in the first threaded hole 124; Figure 4 As shown, the transmission mechanism 130 includes a first motor 131 mounted on the side of the fixed block 111 and corresponding to the first slide groove 113, and a first lead screw 132 located on the output shaft of the first motor 131 and mounted on the inner side of the first slide groove 133 via bearings and connected to the first threaded hole 124. When the first motor 131 is started, the first motor 131 drives the first lead screw 132 to rotate, which in turn drives the movable plate 121, which is threadedly connected to the first lead screw 132 via the first threaded hole 124, to move relative to the fixed block 111 along the direction of the first slide groove 113, so as to adjust the position of the scribing assembly 300 mounted on the movable plate 121 and avoid wires or pipes in the inner space of the aircraft.

[0031] Figure 5 Please refer to the schematic diagram of the driving device structure of the present invention. Figure 5 The driving device 200 includes a translation assembly 210 mounted on a moving plate 121, a driving mechanism 220 mounted on the translation assembly 210, and a guide mechanism 230 mounted on the translation assembly 210 and parallel to the driving mechanism 220. Specifically, the translation assembly 210 includes a translation plate 211 and a connecting block 212 mounted on the translation plate 211. The translation plate 211 is also equipped with a motor mounting plate 214 for supporting the driving mechanism. The connecting block 212 of 11 is installed in the elongated opening of the movable plate 121, and the connecting block 212 is provided with second sliders 213 on both sides. The elongated opening of the movable plate 121 is provided with second sliding grooves 122 that are adapted to the second sliders 213. The second sliders 213 are slidably assembled in the second sliding grooves 122. Based on the above assembly relationship, the connecting block 212 can slide in the elongated opening of the movable plate 121, thereby driving the translation plate 211 to move along the length direction of the movable plate 121.

[0032] The drive mechanism 220 includes a second motor 221 mounted on a motor mounting plate 214 and a second lead screw 222 mounted on the output shaft of the second motor 221.

[0033] The guiding mechanism 230 includes a guide shaft 231, which is fixed on the translation plate 211 and parallel to the second lead screw 222. The guide shaft 231 is provided with guide holes 233 through its two end faces along the axial direction, and the translation plate 211 is also provided with a through hole coaxial with the guide hole 233. The scribing assembly 300 passes through the guide hole 233 and the through hole of the translation plate 211 and is connected to the driving mechanism 220. Under the driving action of the driving mechanism 220, the scribing assembly 300 can slide in the guide hole 233 to adjust the distance of its end scribing head module relative to the scribing position of the aircraft body. The moving direction of the scribing assembly 300 in the guide hole 233 is perpendicular to the translation plate 211 and the moving plate 121.

[0034] In addition, a finger groove 232 is provided on the outer circumferential wall of the guide shaft 231. When using the scribing device, hold the guide shaft 231 with your fingers in the finger groove 232 for easy gripping, and then manually push the translation plate 211 to slide along its length on the moving plate 121 to adjust the position of the scribing assembly 300 so that the scribing assembly 300 is aligned with the scribing position on the aircraft body.

[0035] Figure 6 Please refer to the schematic diagram of the scribing component structure of this invention. Figure 6 The scribing assembly 300 includes a movable shaft assembly 310 slidably mounted in the guide hole 233, a connecting piece assembly 320 and a scribing head module 340 mounted at both ends of the movable shaft assembly 310, and the connecting piece assembly 320 is connected to the drive mechanism 200 on the translation plate 211. The movable shaft assembly 310 includes a movable shaft 311, one end of which has an axially formed mounting groove 312. A pressure sensor 313 and a spring 330 are mounted in the mounting groove 312, and one end of the spring 330 abuts against the pressure sensor 313. The connecting piece assembly 320 includes a first connecting piece 321, which is fixed to the end of the movable shaft 311 away from the mounting groove 312 by a connecting bolt. The first connecting piece 321 is provided with a second threaded hole 322, and a second lead screw 222 is sleeved in the second threaded hole 322. The scribing head module 340 is assembled in the mounting groove 312 and includes a second connecting piece 341 and a straight cylinder 342 assembled on the second connecting piece 341. The second connecting piece 341 abuts against the spring 330 in the mounting groove 312. The end of the straight cylinder 342 away from the second connecting piece 341 has a cone head 343 for scribing. The cone head 343 is located outside the mounting groove 312. The scribing head module 340 can reciprocate in the mounting groove 312 along the axial direction.

[0036] The marking assembly 300 further includes an end cap module 350, which consists of an end cap 351, a connecting hole 352 coaxially extending through the end face of the end cap 351, and a camera 353 mounted on the end cap 351. The end cap 351 covers the opening of the mounting groove 312, and is used to enclose the spring 330 and the second connecting piece 341 within the mounting groove 312. The straight cylinder 342 and the conical head 343 pass through the connecting hole 352, and the camera 353 is located on the side of the end cap 351 facing away from the opening of the mounting groove 312. After the end cap module 350 is closed in the opening of the mounting groove 312, the two ends of the second connecting piece 341 abut against the end faces of the spring 330 and the end cap 351, respectively.

[0037] Based on the same inventive concept, this invention also discloses a method for marking lines on the fuselage of an aircraft, applicable to the interior space of an aircraft. The marking method is implemented using the fuselage marking device for the interior space of an aircraft described in the above embodiments. The specific marking process is as follows: Step S1. The scribing device is attached to the aircraft body to be scribed by the vacuum suction cup assembly 112. The translation plate 211 on the sliding moving plate 121 is positioned with the guide mechanism 230 so that the cone 343 of the scribing head module 340 installed on the guide mechanism 230 is aligned with the scribing position of the aircraft body. Step S2. Start the second motor 221. The second motor 221 drives the second lead screw 222 to rotate. The rotation of the second lead screw 222 drives the first connecting piece 321 to translate on the second lead screw 222. The first connecting piece 321 then drives the movable shaft 311 connected to it to move in the guide hole 233, so that the cone 343 of the scribing module 340 enters the inner space that the aircraft can reach and comes into contact with the scribing position of the fuselage in the inner space of the aircraft. Step S3. Then, hold the guide shaft 231 and drive the translation plate 211 along its length direction on the moving plate 121. The movement drives the entire moving axis assembly 310 to move, which in turn drives the scribing head module 340 to move. The cone 343 at the end of the scribing head module 340 scribes lines on the surface of the aircraft body. During the scribing process, the camera 353 on the end cover 351 captures images of the inner space of the aircraft body and transmits the captured images to an external mobile device via wireless network or other means for the operator to observe.

[0038] In the embodiments described in this invention, in order to ensure the clarity of the camera footage, an illumination lamp is also installed on the end cover 351. The illumination lamp is distributed around the camera 353 and is used to provide supplementary lighting during the recording process.

[0039] In the embodiment described in this invention, during the marking process, after the cone 343 contacts the marking position, it continues to move towards the marking position. At this time, the straight cylinder 342 moves into the inner cavity of the mounting groove 312 and compresses the spring 330 through the connecting piece 341 until the straight cylinder 342 contacts the pressure sensor 313. The pressure sensor 313 measures the pressure value of the straight cylinder 342. When the pressure value reaches the set threshold, the power supply of the second motor 221 is cut off. This ensures the marking force, the clarity of the marked line, and also avoids damage to the aircraft body or the marking device.

[0040] Furthermore, when there are wires or pipes installed in the internal space, if the camera 353 captures the wires or pipes, the operator can directly observe them on a mobile device such as a mobile phone or tablet. At this time, the first motor 131 is started, which drives the first lead screw 132 to rotate. The rotation of the first lead screw 132 drives the moving plate 121 to move along the trajectory of the first slide groove 113 on the fixed block 111, thereby moving the cone head 343 to avoid the wires or pipes. Then, the second motor 221 is started to align the cone head 343 with the position to be marked until the cone head 343 contacts the marking position, and then the subsequent marking operation is performed.

[0041] To achieve automation, the marking device is also equipped with a PLC controller, which is connected to a camera 353. The camera 353 captures images and transmits them to the PLC controller. Based on the captured image, the transmission mechanism 130 is activated, which drives the marking assembly 300 to move, avoiding wires and pipes in the inner space, making operation more convenient. Furthermore, the PLC controller can also be connected to the drive mechanism 200 to control its operation, thereby adjusting the distance between the marking head module 340 and the marking position on the aircraft body.

[0042] Understandably, in order to control and understand the movement distance and position of the scribe head module driven by the translation plate 211 at 340 degrees, the edge of the translation plate 121 is etched with scale.

[0043] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A fuselage marking device suitable for the interior space of an aircraft, characterized in that, include: The fixing mechanism (100) includes a fixing block assembly (110) mounted on the aircraft shell and a movable plate assembly (120) mounted on the fixing block assembly (110) on the side away from the aircraft shell. The driving device (200) includes a translation component (210) mounted on the movable plate assembly (120) and movable along the length of the movable plate assembly (120), a driving mechanism (220) fixed on the translation component (210), and a guide mechanism (230) mounted on the translation component (210). A marking assembly (300) includes a movable shaft assembly (310) slidably mounted on the guide mechanism (230), a connecting piece assembly (320) mounted on the end face of the movable shaft assembly (310) and connected to the drive mechanism (220), and a marking head module (340) mounted on the other end of the movable shaft assembly (310). The end of the movable shaft assembly (310) is also provided with cameras (353) distributed beside the marking head module (340). The drive mechanism (220) drives the connecting piece assembly (320) to move in a direction perpendicular to the moving plate assembly (120), causing the moving shaft assembly (310) to move synchronously in the same direction on the guide mechanism (230), so that the scribing head module (340) on the moving shaft assembly (310) abuts against the position to be scribed on the aircraft body. When the translation assembly (210) moves along the length direction of the moving plate assembly (120), it drives the drive mechanism (220), the moving shaft assembly (310) and the scribing head module (340) to move synchronously. The scribing head module (340) completes the scribing on the aircraft body. The camera (353) captures images of the aircraft's inner space near the scribing head module (340) in real time during the scribing process.

2. The fuselage marking device suitable for the interior space of an aircraft according to claim 1, characterized in that, The fixing block assembly (110) includes a fixing block (111) and a vacuum suction cup assembly (112) mounted on the fixing block (111) for adsorbing the aircraft shell; the vacuum suction cup assembly (112) includes a hollow box (112a) and a suction cup (112b), an exhaust port (112c) and an air inlet (112d) disposed on the hollow box (112a) and communicating with the inner cavity of the hollow box (112a), the air inlet (112d) being threadedly connected to a sealing cap; the hollow box (112a) is mounted on the fixing block (111).

3. The fuselage marking device suitable for the interior space of an aircraft according to claim 2, characterized in that, The movable plate assembly (120) includes a movable plate (121) disposed on the side of the fixed block (111) away from the vacuum suction cup assembly (112), and the movable plate (121) has a strip-shaped opening through the center along the long side direction.

4. The fuselage marking device suitable for the interior space of an aircraft according to claim 3, characterized in that, The fixed block (111) is provided with a first sliding groove (113), and the movable plate (121) is provided with a first slider (123) that is slidably inserted into the first sliding groove (113). The end face of the first slider (123) is also provided with a first threaded hole (124) that penetrates the first slider (123).

5. The fuselage marking device suitable for the interior space of an aircraft according to claim 3, characterized in that, The translation component (210) includes a translation plate (211) and a connecting block (212) inserted into the strip opening. The connecting block (212) has a second slider (213) on both sides and a second groove (122) on both sides of the strip opening. The second slider (213) is slidably installed in the second groove (122), and the connecting block (212) can slide in the strip opening.

6. The fuselage marking device suitable for the interior space of an aircraft according to claim 5, characterized in that, The drive mechanism (220) includes a second motor (221) mounted on a translation plate (211) and a second lead screw (222) fixed on the output shaft of the second motor (221).

7. A fuselage marking device suitable for the interior space of an aircraft according to claim 6, characterized in that, The guiding mechanism includes a guide shaft (231) disposed on the translation plate (211) and parallel to the second lead screw (222), and the end face of the guide shaft (231) is provided with a guide hole (233) along the axial direction.

8. A fuselage marking device suitable for the interior space of an aircraft according to claim 7, characterized in that, The movable shaft assembly (310) includes a movable shaft (311) and a mounting groove (312) formed on the end face of the movable shaft (311). The movable shaft (311) is slidably inserted into the guide hole (233). A pressure sensor (313) and a spring (330) abutting against the pressure sensor (313) are provided in the mounting groove (312).

9. A fuselage marking device suitable for the interior space of an aircraft according to claim 8, characterized in that, The connecting piece assembly (320) includes a first connecting piece (321) mounted on a movable shaft (311) at one end away from the mounting groove (312). A second threaded hole (322) is provided on the first connecting piece (321), and a second lead screw (222) is screwed into the second threaded hole (322).

10. A fuselage marking device suitable for the interior space of an aircraft according to claim 9, characterized in that, The marking head module (340) includes a second connecting piece (341) inserted into the mounting groove (312) and abutting against the spring (300) and a straight cylinder (342) fixed on the second connecting piece (341). The end of the straight cylinder has a cone (343) located outside the mounting groove (312).

11. A fuselage marking device suitable for the interior space of an aircraft according to claim 10, characterized in that, The marking assembly also includes an end cap module (350), which includes an end cap (351) fixed at the opening of the mounting groove (312) and a connecting hole (352) opened on the end face of the end cap (351). The straight cylinder (342) passes through the connecting hole (352), and the camera (353) is mounted on the end cap (351).

12. The fuselage marking device suitable for the interior space of an aircraft according to claim 7, characterized in that, The outer wall of the guide shaft (231) is also provided with a finger groove (232).

13. A fuselage marking device suitable for the interior space of an aircraft according to claim 4, characterized in that, The fixing mechanism (100) further includes a transmission assembly (130), which includes a first motor (131) mounted on the side of the fixing block (111) and a first lead screw (132) connected to the output end of the first motor (131). The other end of the first lead screw (132) is screwed into the first threaded hole (124) of the first slider (123).

14. A fuselage marking device suitable for the interior space of an aircraft according to claim 11, characterized in that, Illumination beads are distributed around the camera (353).

15. A method for scribing lines on the fuselage of an aircraft, characterized in that, The aircraft fuselage marking method is implemented using the fuselage marking device suitable for the inner space of an aircraft as described in any one of claims 1-14, and includes the following steps: Step S1. Assemble the scribing device onto the aircraft fuselage shell to be scribed using the fixed block assembly (110), and slide the translation assembly (210) on the sliding plate assembly (120) to adjust the position of the drive mechanism (220) and the guide mechanism (230) so that the scribing head module (340) installed on the guide mechanism (230) is aligned with the scribing position on the aircraft fuselage. Step S2. Start the drive mechanism (220), and drive the moving shaft assembly (310) to move on the guide mechanism (230) so that the scribing head module (340) on the moving shaft assembly (310) extends into the inner space of the aircraft and contacts the scribing position; Step S3. The handheld guide mechanism (230) drives the translation component (210) to move on the moving plate component (120), and simultaneously drives the moving axis component (310) and the scribing head module (340) to move. The scribing head module (340) scribing lines on the surface of the aircraft body. During the scribing process, the camera (353) on the moving axis component (310) takes pictures of the inner space of the aircraft near the scribing head module (340) and transmits the picture to the mobile terminal through the network for the operator to observe. At the same time, the lighting beads distributed around the camera (353) provide supplementary lighting during the shooting process.

Images