Aircraft fuselage rapid docking device with locking mechanism and method

Abstract

The invention provides an airplane fuselage rapid butt joint device with a locking mechanism and a method, the airplane fuselage rapid butt joint device comprises a bearing base and further comprises a double-shaft driving motor arranged in the middle of the bearing base, and the two output ends of the double-shaft driving motor are fixedly connected with transverse threaded shafts; the two sets of transverse threaded shafts are sleeved with a first moving block and a second moving block correspondingly, the upper side of the first moving block and the upper side of the second moving block are fixedly connected with a first bearing plate and a second bearing plate correspondingly, and the two sides of the lower surface of the first bearing plate and the two sides of the lower surface of the second bearing plate are fixedly connected with side supporting sliding plates correspondingly. Two first limiting vertical plates are arranged on the upper side of the second bearing plate, frame openings are formed in the first limiting vertical plates in a penetrating mode, a plurality of shaft clamping rods are clamped to the inner sides of the frame openings, side elastic rollers movably sleeve the shaft clamping rods, and fixing plates are fixedly connected to the positions, close to the two sides, of the upper surface of the second bearing plate; and a rotating motor is fixedly clamped and mounted on the outer side of the fixed plate.

Description

Technical Field

[0001] This invention relates to the field of aircraft fuselage docking technology, specifically to an aircraft fuselage quick docking device and method with a locking mechanism. Background Technology

[0002] The main components of an aircraft include the fuselage, wings, tail, and landing gear. The fuselage is the primary load-bearing structure, housing passengers, cargo, fuel, avionics, and connecting other critical components such as the wings, tail, and landing gear. The fuselage docking assembly is a specialized device used during aircraft manufacturing, maintenance, or assembly to precisely position, adjust, and securely connect two or more fuselage sections. Its core function is to ensure that the docking accuracy between fuselage sections meets the stringent aerodynamic and structural requirements of the aviation industry, while improving assembly efficiency and safety. It is primarily used for segmented docking on the final assembly line, fuselage replacement during major overhauls, and prototype assembly during the research and development phase. In existing technologies, before fuselage docking, the main body of the docking frame is fixedly connected to one end of the fuselage to be docked. Then, the other fuselage is pushed by a slide rail on a tooling fixture, causing it to embed into the interface formed by the docking flange. The docking flange fits against the fuselage skin of the other fuselage. Finally, the docking flange is fixed to the fuselage skin using methods such as adhesive riveting, thus completing the docking of the two fuselages. Only one docking frame is needed to dock two fuselages, simplifying the fuselage docking structure, reducing weight, and improving the convenience of fuselage assembly. In addition, it can reduce the overall weight of the aircraft, which is beneficial to the lightweight design of the aircraft. However, in the use of existing aircraft fuselage docking devices, the two fuselage sections are prone to docking failure due to misalignment of axes or misalignment. Moreover, the operation of the docking process is difficult, which leads to a decrease in the docking efficiency of the aircraft fuselage. Therefore, a quick docking device for aircraft fuselages with a locking mechanism is proposed. Summary of the Invention

[0003] To address the shortcomings of existing technologies, this invention provides a quick docking device for aircraft fuselages with a locking mechanism. This solves the technical problems mentioned in the background section, such as the failure of docking between the two fuselage sections due to misalignment or misalignment of axes, and the high operational difficulty of the docking process, which leads to reduced docking efficiency of the aircraft fuselage.

[0004] To achieve the above objectives, the present invention provides the following technical solution: In a first aspect, this application provides a quick docking device for aircraft fuselage with a locking mechanism, including a support base and a dual-axis drive motor disposed in the middle of the support base. Both output ends of the dual-axis drive motor are fixedly connected to a horizontal threaded shaft. A first moving block and a second moving block are respectively sleeved on the two sets of horizontal threaded shafts. A first support plate and a second support plate are fixedly connected to the upper side of the first moving block and the second moving block, respectively. Side support slides are fixedly connected to both sides of the lower surface of the first support plate and the second support plate. The upper side of the second bearing plate is provided with two sets of first limiting vertical plates. The first limiting vertical plates are provided with a frame opening. Several sets of clamping rods are clamped on the inner side of the frame opening. Side elastic rollers are movably sleeved on the clamping rods. Fixed plates are fixedly connected to the upper surface of the second bearing plate near both sides. A rotary motor is fixedly installed on the outer side of the fixed plate. The output end of the rotary motor is fixedly connected to a long rotating shaft that passes through the fixed plate. A bottom elastic roller is fixedly sleeved on the long rotating shaft. The first vertical plate is fixedly connected to a first vertical groove body on one side. A first vertical screw shaft is provided through the first vertical groove body. A lifting rod is sleeved on the first vertical screw shaft. A fixed shaft is fixedly connected to the end of the lifting rod. An auxiliary elastic roller is movably sleeved on the fixed shaft. A third side groove is fixedly connected to one side of the first bearing plate. A second adjusting screw is provided through the third side groove. A second lifting column is sleeved on the second adjusting screw. A lifting plate is fixedly connected to the upper end of the second lifting column. A lifting carrier plate is fixedly connected to one side of the lifting plate. Limit blocks are fixedly connected to both sides of the lifting carrier plate.

[0005] Specifically, the support base has a main through-hole in the middle, and the dual-axis drive motor is fixedly installed inside the main through-hole. The external threads of the two sets of transverse threaded shafts are symmetrically arranged, and the first moving block and the second moving block are respectively threadedly connected to the two sets of transverse threaded shafts. The support base has two sets of docking sliding mouths through, and the first moving block and the second moving block are respectively slidably connected to the support base through the docking sliding mouths. Side sliding grooves are opened on both sides of the support base, and the lower end of the side support slide plate is located inside the side sliding groove.

[0006] Specifically, several sets of side elastic rollers are evenly distributed on the inner side of the frame opening, the bottom elastic roller is located between two sets of fixed plates, the bottom end of the first vertical groove is fixedly installed with a first lifting motor, and the first vertical screw shaft is fixedly connected to the output end of the first lifting motor. The lifting rod is threadedly connected to the first vertical screw shaft, and one end of the lifting rod is located on the inner side of the first vertical groove. The two sets of auxiliary elastic rollers are symmetrically arranged about the bottom elastic roller.

[0007] Specifically, a first side groove and a second side groove are fixedly connected to one side of the second bearing plate. A first adjusting screw is provided through the first side groove. A limiting vertical rod is fixedly connected to the inner side of the second side groove. A limiting plate is provided above the first side groove and the second side groove. Two sets of first lifting columns are fixedly connected to the limiting plate. One set of first lifting columns is threadedly connected to the first adjusting screw, and the other set of first lifting columns is slidably connected to the limiting vertical rod.

[0008] Specifically, the second lifting column is threadedly connected to the second adjusting screw, and the second lifting column is located inside the third side groove. Two sets of second limiting vertical plates are provided on the upper side of the first bearing plate. The bottom of the second limiting vertical plate is provided with a limiting slot, and the limiting block is located inside the limiting slot.

[0009] Specifically, a first through-hole is provided in the middle of the second bearing plate, a first dual-axis motor is fixedly installed inside the first through-hole, and a first horizontal lead screw shaft is fixedly connected to both output ends of the first dual-axis motor. A first moving rod is sleeved on the first horizontal lead screw shaft. The first bearing plate has a second through opening in the middle. A second dual-axis motor is fixedly installed inside the second through opening. Both output ends of the second dual-axis motor are fixedly connected to a second horizontal lead screw shaft. A second moving rod is sleeved on the second horizontal lead screw shaft.

[0010] Specifically, the external threads of the two sets of first horizontal lead screw shafts are symmetrically arranged, and the first moving rod is threadedly connected to the first horizontal lead screw shaft. The first moving rod is movably connected to the second bearing plate. The first limiting vertical plate is engaged with the first moving rod. The two sets of first limiting vertical plates are symmetrically arranged about the first opening. The external threads of the two sets of second horizontal lead screw shafts are symmetrically arranged, and the second moving rod is threadedly connected to the second horizontal lead screw shaft. The second moving rod is movably connected to the first bearing plate. The second limiting vertical plate is engaged with the second moving rod. The two sets of second limiting vertical plates are symmetrically arranged about the second opening.

[0011] Specifically, a central groove is fixedly connected to the upper middle of the support base. A third through-hole is provided in the middle of the central groove, and a third dual-axis motor is fixedly installed inside the third through-hole. Both output ends of the third dual-axis motor are fixedly connected to a third horizontal lead screw shaft. A third moving rod is sleeved on the third horizontal lead screw shaft. A second vertical groove is fixedly connected to the outer end of the third moving rod. A second vertical lead screw shaft is provided through the second vertical groove. A lifting block is sleeved on the second vertical lead screw shaft. A locking plate is fixedly connected to the end of the lifting block. An elastic anti-slip plate is fixedly connected to the locking plate.

[0012] Specifically, the external threads of the two sets of third horizontal lead screw shafts are symmetrically arranged. The third moving rod is threadedly connected to the third horizontal lead screw shaft and is movably connected to the intermediate groove. The bottom end of the second vertical groove is fixedly installed with a second lifting motor, and the second vertical lead screw shaft is fixedly connected to the output end of the second lifting motor. The second vertical lead screw shaft is threadedly connected to the lifting block, and the lifting block is located inside the second vertical groove. The vertical cross-sectional shape of the locking plate and the elastic anti-slip plate is arc-shaped.

[0013] Secondly, this application provides a method for quick docking of an aircraft fuselage with a locking mechanism, characterized in that it is implemented using the aforementioned quick docking device for an aircraft fuselage, and the method includes: Step 1: By starting the first dual-axis motor 13 inside the first port 12, the two sets of first horizontal lead screw shafts 14 are rotated together, thereby driving the two sets of first moving rods 15 to move relative to each other along the second bearing plate 8 under the cooperation of symmetrical external threads, and then driving the two sets of first limiting vertical plates 16 to move relative to each other until the side elastic roller 19 is in contact with a section of the machine body. Step 2: Start the second dual-axis motor 43 inside the second port 42 to drive the two sets of second horizontal lead screw shafts 44 to rotate together, thereby driving the two sets of second moving rods 45 to move relative to each other along the first bearing plate 7 under the cooperation of symmetrical external threads, and then driving the two sets of second limiting vertical plates 46 to move relative to each other until the two sets of second limiting vertical plates 46 are in contact with the other section of the machine body. Step 3: When a section of the machine body is located between the two sets of first limiting vertical plates 16, the machine body is driven by the first dual-axis motor 13 to make it fit with the side elastic roller 19. At this time, the machine body is placed on the upper side of the bottom elastic roller 23. At the same time, the first lifting motor 25 at the bottom of the first vertical groove 24 is started to drive the first vertical screw shaft 26 to rotate. Thus, through the threaded connection between the first vertical screw shaft 26 and the lifting rod 27, the fixed shaft 28 is driven to move upward until the auxiliary elastic roller 29 fits with the machine body to provide auxiliary support for the rolling of the machine body. Step 4: Rotate the second adjusting screw 37 on the third side groove 36 to drive the second lifting column 38 to move upward along the third side groove 36, thereby driving the lifting plate 39 to move upward. Then, with the cooperation of the limiting block 41 and the limiting slot 47, the lifting carrier plate 40 is driven to move upward until the height of the lifting carrier plate 40 corresponds to the bottom height of the machine body. Fix the position of the second adjusting screw 37. Then place the other section of the machine body between the two sets of second limiting vertical plates 46, and drive the second dual-axis motor 43 to make the machine body fit with the second limiting vertical plates 46. Step 5: Start the rotary motor 21 on the outside of the fixed plate 20 to drive the rotating long shaft 22 and the bottom elastic roller 23 to rotate together, thereby driving the fuselage to rotate between the two sets of first limit vertical plates 16 with the cooperation of the side elastic roller 19 and the auxiliary elastic roller 29, until the two sections of the aircraft fuselage are aligned. Step 6: Rotate the first adjusting screw 32 on the first side groove 30 to drive the limiting plate 35 to move upward under the threaded connection between the first adjusting screw 32 and the first lifting column 34, and with the cooperation of the limiting vertical rod 33 in the second side groove 31, make the limiting plate 35 fit tightly with the machine body and fix the position of the first adjusting screw 32. Step 7: During fuselage docking, start the dual-axis drive motor 3 inside the main port 2 to drive the two sets of transverse threaded shafts 4 to rotate together. Under the cooperation of the symmetrical external threads, the first moving block 5 and the second moving block 6 move relative to each other along the two sets of docking slides 9. Then, under the cooperation of the side support slide plate 10 and the side sliding groove 11, the first bearing plate 7 and the second bearing plate 8 move relative to each other above the bearing base 1 until the two sections of the aircraft fuselage dock together. Step 8: After the two sections of the aircraft fuselage are docked and in contact, the second lifting motor 54 at the bottom of the second vertical groove 53 is started to drive the second vertical screw shaft 55 to rotate. This causes the locking plate 57 to move up and down through the threaded connection between the second vertical screw shaft 55 and the lifting block 56 until the locking plate 57 is at the target height position. Step 9: Start the third dual-axis motor 50 inside the third port 49 to drive the two sets of third horizontal lead screw shafts 51 to rotate together. This, in turn, drives the two sets of third moving rods 52 to move relative to each other along the middle groove 48 under the cooperation of symmetrical external threads. This, in turn, drives the two sets of second vertical grooves 53 to move relative to each other until the elastic anti-slip plates 58 on the two sets of locking plates 57 are tightly fitted to the two sections of the machine body.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. When a section of the machine body is positioned between two sets of first limiting vertical plates, the machine body is brought into contact with the side elastic rollers by the drive of the first dual-axis motor. At this time, the machine body is placed on the upper side of the bottom elastic roller. Simultaneously, the first lifting motor at the bottom of the first vertical groove is activated to drive the first vertical screw shaft to rotate. This, through the threaded connection between the first vertical screw shaft and the lifting rod, drives the fixed shaft to move upward until the auxiliary elastic roller is in contact with the machine body, providing auxiliary support for the rolling of the machine body. Then, the second adjusting screw on the third side groove is rotated to drive the second lifting column to move upward along the third side groove, thereby driving the lifting plate to move upward. Subsequently, with the cooperation of the limiting block and the limiting groove, the lifting carrier plate is moved upward. The process involves moving the lifting platform until its height corresponds to the bottom height of the fuselage, and then fixing the position of the second adjusting screw. Next, the other fuselage section is placed between the two sets of second limiting vertical plates, and driven by the second dual-axis motor, the fuselage is brought into contact with the second limiting vertical plates to ensure the axes of the two fuselage sections are aligned. Then, the rotating motor on the outside of the fixing plate is activated to drive the rotating long shaft and the bottom elastic roller to rotate together. This, in conjunction with the side elastic roller and auxiliary elastic roller, causes the fuselage to rotate between the two sets of first limiting vertical plates until the two fuselage sections are aligned. This achieves the direct docking function for the two fuselage sections, reduces the difficulty of docking the fuselage, and significantly improves the docking efficiency.

[0015] 2. By activating the first dual-axis motor in the middle of the second bearing plate, the two sets of first horizontal lead screw shafts are rotated together. Under the cooperation of symmetrical external threads, the two sets of first moving rods move relative to each other along the second bearing plate, thereby driving the two sets of first limiting vertical plates to move relative to each other until the side elastic rollers are in contact with one section of the fuselage. Then, the second dual-axis motor in the middle of the first bearing plate is activated, the two sets of second horizontal lead screw shafts are rotated together. Under the cooperation of symmetrical external threads, the two sets of second moving rods move relative to each other along the first bearing plate, thereby driving the two sets of second limiting vertical plates to move relative to each other until both sets of second limiting vertical plates are in contact with the other section of the fuselage. This method can provide auxiliary limiting for two sections of aircraft fuselage of various sizes, significantly improving the applicability of the docking device.

[0016] 3. After the two aircraft fuselage sections are docked and contacted, the second lifting motor at the bottom of the second vertical groove is activated to drive the second vertical lead screw shaft to rotate. This, through the threaded connection between the second vertical lead screw shaft and the lifting block, causes the locking plate to move up and down until the locking plate is at the target height. Then, the third dual-axis motor inside the third port is activated to drive the two sets of third horizontal lead screw shafts to rotate together. This, with the cooperation of symmetrical external threads, causes the two sets of third moving rods to move relative to each other along the middle groove, thereby causing the two sets of second vertical grooves to move relative to each other until the elastic anti-slip plates on both sets of locking plates are tightly fitted to the two fuselage sections. This allows for docking and locking of the two aircraft fuselage sections according to their actual specifications, preventing gaps from appearing at the connection point due to external forces and ensuring the stability of subsequent connection work. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the connection structure of the support base in this invention; Figure 3 This is a schematic diagram of the connection structure of the second bearing plate in this invention; Figure 4 This is a schematic diagram of the distribution structure of the first limiting vertical plate in this invention; Figure 5 This is a schematic diagram of the connection structure of the first vertical groove in this invention; Figure 6 This is a schematic diagram of the connection structure of the limiting plate in this invention; Figure 7 This is a schematic diagram of the connection structure of the first bearing plate in this invention; Figure 8 This is a schematic diagram of the distribution structure of the second limiting plate in this invention; Figure 9 This is a schematic diagram of the connection structure of the lifting platform in this invention; Figure 10 This is a schematic diagram of the connection structure of the intermediate groove in this invention; Figure 11 This is a front view schematic diagram of the present invention.

[0018] In the diagram: 1. Support base; 2. Main port; 3. Dual-axis drive motor; 4. Horizontal threaded shaft; 5. First moving block; 6. Second moving block; 7. First support plate; 8. Second support plate; 9. Connecting slide; 10. Side support slide plate; 11. Side sliding groove; 12. First port; 13. First dual-axis motor; 14. First horizontal lead screw shaft; 15. First moving rod; 16. First limiting vertical plate; 17. Frame opening; 18. Shaft locking rod; 19. Side elastic roller; 20. Fixed plate; 21. Rotary motor; 22. Rotating long shaft; 23. Bottom elastic roller; 24. First vertical groove body; 25. First lifting motor; 26. First vertical lead screw shaft; 27. Lifting rod; 28. Fixed shaft rod; 29. ​​Auxiliary elastic roller; 30. First side groove 31. Second side groove; 32. First adjusting screw; 33. Limiting vertical rod; 34. First lifting column; 35. Limiting plate; 36. Third side groove; 37. Second adjusting screw; 38. Second lifting column; 39. Lifting plate; 40. Lifting carrier plate; 41. Limiting block; 42. Second opening; 43. Second dual-axis motor; 44. Second horizontal lead screw shaft; 45. Second moving rod; 46. Second limiting vertical plate; 47. Limiting slot; 48. Middle groove; 49. Third opening; 50. Third dual-axis motor; 51. Third horizontal lead screw shaft; 52. Third moving rod; 53. Second vertical groove; 54. Second lifting motor; 55. Second vertical lead screw shaft; 56. Lifting block; 57. Locking plate; 58. Elastic anti-slip plate. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] To better understand the above technical solution, the following will refer to the appendix to the instruction manual. Figure 1 ~Appendix Figure 11 The specific implementation methods are described in detail below for the above technical solutions.

[0021] Example 1 Please see Figure 1This invention provides a quick docking device for aircraft fuselage with a locking mechanism, including a support base 1 and a dual-axis drive motor 3 disposed in the middle of the support base 1. Both output ends of the dual-axis drive motor 3 are fixedly connected to transverse threaded shafts 4. A first moving block 5 and a second moving block 6 are respectively sleeved on the two sets of transverse threaded shafts 4. A first support plate 7 and a second support plate 8 are fixedly connected to the upper sides of the first moving block 5 and the second moving block 6, respectively. Side support slide plates 10 are fixedly connected to both sides of the lower surfaces of the first support plate 7 and the second support plate 8. like Figure 3 , Figure 4 , Figure 5 As shown, two sets of first limiting vertical plates 16 are provided on the upper side of the second bearing plate 8. A frame opening 17 is provided through the first limiting vertical plate 16. Several sets of clamping rods 18 are clamped inside the frame opening 17. Side elastic rollers 19 are movably sleeved on the clamping rods 18. Fixed plates 20 are fixedly connected to both sides of the upper surface of the second bearing plate 8. A rotary motor 21 is fixedly installed on the outer side of the fixed plate 20. A rotating long shaft 22 passing through the fixed plate 20 is fixedly connected to the output end of the rotary motor 21. A bottom elastic roller 23 is clamped and sleeved on the rotating long shaft 22. A first vertical groove 24 is fixedly connected to one side of the first limiting vertical plate 16. A first vertical screw shaft 26 is provided through the first vertical groove 24. A lifting rod 27 is sleeved on the first vertical screw shaft 26. A fixed shaft 28 is fixedly connected to the end of the lifting rod 27. An auxiliary elastic roller 29 is movably sleeved on the fixed shaft 28. like Figure 9 As shown, a third side groove 36 is fixedly connected to the middle of one side of the first bearing plate 7. A second adjusting screw 37 is provided through the third side groove 36. A second lifting column 38 is sleeved on the second adjusting screw 37. A lifting plate 39 is fixedly connected to the upper end of the second lifting column 38. A lifting carrier plate 40 is fixedly connected to one side of the lifting plate 39. Limiting blocks 41 are fixedly connected to both sides of the lifting carrier plate 40.

[0022] like Figure 2 As shown, a main opening 2 is provided through the middle of the support base 1, and a dual-axis drive motor 3 is fixedly installed inside the main opening 2. The external threads of the two sets of transverse threaded shafts 4 are symmetrically arranged, and the first moving block 5 and the second moving block 6 are respectively threadedly connected to the two sets of transverse threaded shafts 4. Two sets of docking sliding mouths 9 are provided through the support base 1, and the first moving block 5 and the second moving block 6 are respectively slidably connected to the support base 1 through the docking sliding mouths 9. Side sliding grooves 11 are provided on both sides of the support base 1, and the lower end of the side support slide plate 10 is located inside the side sliding groove 11.

[0023] Several sets of side elastic rollers 19 are evenly distributed on the inner side of the frame opening 17. The bottom elastic roller 23 is located between two sets of fixed plates 20. The bottom end of the first vertical groove 24 is fixedly installed with a first lifting motor 25, and the first vertical screw shaft 26 is fixedly connected to the output end of the first lifting motor 25. The lifting rod 27 is threadedly connected to the first vertical screw shaft 26, and one end of the lifting rod 27 is located on the inner side of the first vertical groove 24. Two sets of auxiliary elastic rollers 29 are symmetrically arranged about the bottom elastic roller 23.

[0024] like Figure 6 As shown, a first side groove 30 and a second side groove 31 are fixedly connected to one side of the second bearing plate 8. A first adjusting screw 32 is provided through the first side groove 30. A limiting vertical rod 33 is fixedly connected to the inner side of the second side groove 31. A limiting plate 35 is provided above the first side groove 30 and the second side groove 31. Two sets of first lifting columns 34 are fixedly connected to the limiting plate 35. One set of first lifting columns 34 is threadedly connected to the first adjusting screw 32, and the other set of first lifting columns 34 is slidably connected to the limiting vertical rod 33.

[0025] like Figure 7 As shown, the second lifting column 38 is threadedly connected to the second adjusting screw 37, and the second lifting column 38 is located inside the third side groove 36. Two sets of second limiting vertical plates 46 are provided on the upper side of the first bearing plate 7. The bottom of the second limiting vertical plate 46 is provided with a limiting slot 47, and the limiting block 41 is located inside the limiting slot 47.

[0026] Specifically, when a section of the machine body is positioned between the two sets of first limiting vertical plates 16, the machine body is brought into contact with the side elastic roller 19 by the drive of the first dual-axis motor 13. At this time, the machine body is placed on the upper side of the bottom elastic roller 23. Simultaneously, the first lifting motor 25 at the bottom of the first vertical groove 24 is activated to drive the first vertical screw shaft 26 to rotate. This, through the threaded connection between the first vertical screw shaft 26 and the lifting rod 27, drives the fixed shaft 28 to move upward until the auxiliary elastic roller 29 is in contact with the machine body to provide auxiliary support for the rolling of the machine body. Then, the second adjusting screw 37 on the third side groove 36 is rotated to drive the second lifting column 38 to move upward along the third side groove 36, thereby driving the lifting plate 39 to move upward. Then, with the cooperation of the limiting block 41 and the limiting slot 47, the lifting plate 39 is driven upward. The lifting plate 40 moves upward until its height corresponds to the bottom height of the fuselage, and the position of the second adjusting screw 37 is fixed. Then, the other fuselage section is placed between the two sets of second limiting vertical plates 46, and the fuselage is brought into contact with the second limiting vertical plates 46 by the drive of the second dual-axis motor 43 to ensure that the axes of the two fuselage sections are aligned. Then, the rotary motor 21 on the outside of the fixing plate 20 is started to drive the rotating long shaft 22 and the bottom elastic roller 23 to rotate together. With the cooperation of the side elastic roller 19 and the auxiliary elastic roller 29, the fuselage is driven to rotate between the two sets of first limiting vertical plates 16 until the two aircraft fuselage sections are aligned. This realizes the function of docking the two aircraft fuselage sections, reduces the docking difficulty of the aircraft fuselage, and significantly improves the docking efficiency of the aircraft fuselage.

[0027] like Figure 8 As shown, a first through-hole 12 is provided through the middle of the second bearing plate 8. A first dual-axis motor 13 is fixedly installed inside the first through-hole 12. A first horizontal lead screw shaft 14 is fixedly connected to both output ends of the first dual-axis motor 13. A first moving rod 15 is sleeved on the first horizontal lead screw shaft 14. A second through-hole 42 is provided through the middle of the first bearing plate 7. A second dual-axis motor 43 is fixedly installed inside the second through-hole 42. A second horizontal lead screw shaft 44 is fixedly connected to both output ends of the second dual-axis motor 43. A second moving rod 45 is sleeved on the second horizontal lead screw shaft 44.

[0028] The external threads of the two sets of first horizontal lead screw shafts 14 are symmetrically arranged, and the first moving rod 15 is threadedly connected to the first horizontal lead screw shaft 14. The first moving rod 15 is movably connected to the second bearing plate 8. The first limiting vertical plate 16 is engaged with the first moving rod 15, and the two sets of first limiting vertical plates 16 are symmetrically arranged about the first through port 12. The external threads of the two sets of second horizontal lead screw shafts 44 are symmetrically arranged, and the second moving rod 45 is threadedly connected to the second horizontal lead screw shaft 44. The second moving rod 45 is movably connected to the first bearing plate 7. The second limiting vertical plate 46 is engaged with the second moving rod 45, and the two sets of second limiting vertical plates 46 are symmetrically arranged about the second through port 42.

[0029] Specifically, by activating the first dual-axis motor 13 in the middle of the second bearing plate 8, the two sets of first horizontal lead screw shafts 14 are rotated together. Under the cooperation of symmetrical external threads, the two sets of first moving rods 15 are moved relative to each other along the second bearing plate 8, thereby causing the two sets of first limiting vertical plates 16 to move relative to each other until the side elastic roller 19 is in contact with one section of the fuselage. Then, the second dual-axis motor 43 in the middle of the first bearing plate 7 is activated, the two sets of second horizontal lead screw shafts 44 are rotated together. Under the cooperation of symmetrical external threads, the two sets of second moving rods 45 are moved relative to each other along the first bearing plate 7, thereby causing the two sets of second limiting vertical plates 46 to move relative to each other until both sets of second limiting vertical plates 46 are in contact with the other section of the fuselage. This can assist in limiting the movement of two sections of aircraft fuselage of various sizes, significantly improving the applicability of the docking device.

[0030] like Figure 10 , Figure 11 As shown, a middle groove 48 is fixedly connected to the upper middle of the support base 1. A third through-hole 49 is provided through the middle of the middle groove 48, and a third dual-axis motor 50 is fixedly installed inside the third through-hole 49. Both output ends of the third dual-axis motor 50 are fixedly connected to a third horizontal lead screw shaft 51. A third moving rod 52 is sleeved on the third horizontal lead screw shaft 51. A second vertical groove 53 is fixedly connected to the outer end of the third moving rod 52. A second vertical lead screw shaft 55 is provided through the second vertical groove 53. A lifting block 56 is sleeved on the second vertical lead screw shaft 55. A locking plate 57 is fixedly connected to the end of the lifting block 56. An elastic anti-slip plate 58 is fixedly connected to the locking plate 57.

[0031] The external threads of the two sets of third horizontal lead screw shafts 51 are symmetrically arranged. The third moving rod 52 is threadedly connected to the third horizontal lead screw shaft 51, and the third moving rod 52 is movably connected to the intermediate groove 48. The bottom end of the second vertical groove 53 is fixedly installed with the second lifting motor 54, and the second vertical lead screw shaft 55 is fixedly connected to the output end of the second lifting motor 54. The second vertical lead screw shaft 55 is threadedly connected to the lifting block 56, and the lifting block 56 is located inside the second vertical groove 53. The vertical cross-sectional shape of the locking plate 57 and the elastic anti-slip plate 58 is arc-shaped.

[0032] Specifically, after the two sections of the aircraft fuselage are docked and contacted, the second lifting motor 54 at the bottom of the second vertical groove 53 is activated to drive the second vertical lead screw shaft 55 to rotate. This, through the threaded connection between the second vertical lead screw shaft 55 and the lifting block 56, drives the locking plate 57 to move up and down until the locking plate 57 is at the target height. Then, the third dual-axis motor 50 inside the third port 49 is activated to drive the two sets of third horizontal lead screw shafts 51 to rotate together. This, with the cooperation of symmetrical external threads, drives the two sets of third moving rods 52 to move relative to each other along the intermediate groove 48, thereby driving the two sets of second vertical grooves 53 to move relative to each other until the elastic anti-slip plates 58 on the two sets of locking plates 57 are tightly fitted with the two sections of the fuselage. This allows for docking and locking of the two sections of the aircraft fuselage according to their actual specifications, preventing gaps from appearing at the connection point due to external forces and ensuring the stability of subsequent connection work.

[0033] Example 2 This invention provides a method for quick docking of aircraft fuselages, which is achieved using a quick docking device for aircraft fuselages with a locking mechanism. The method includes: Step 1: By starting the first dual-axis motor 13 inside the first port 12, the two sets of first horizontal lead screw shafts 14 are rotated together, thereby driving the two sets of first moving rods 15 to move relative to each other along the second bearing plate 8 under the cooperation of symmetrical external threads, and then driving the two sets of first limiting vertical plates 16 to move relative to each other until the side elastic roller 19 is in contact with a section of the machine body. Step 2: Start the second dual-axis motor 43 inside the second port 42 to drive the two sets of second horizontal lead screw shafts 44 to rotate together, thereby driving the two sets of second moving rods 45 to move relative to each other along the first bearing plate 7 under the cooperation of symmetrical external threads, and then driving the two sets of second limiting vertical plates 46 to move relative to each other until the two sets of second limiting vertical plates 46 are in contact with the other section of the machine body. It should be noted that at this time, the opposite ends of the two fuselage sections are aligned with the opposite ends of the first bearing plate 7 and the second bearing plate 8, respectively, which can assist in limiting the two fuselage sections of various sizes and significantly improve the applicability of the docking device.

[0034] Step 3: When a section of the machine body is located between the two sets of first limiting vertical plates 16, the machine body is driven by the first dual-axis motor 13 to make it fit with the side elastic roller 19. At this time, the machine body is placed on the upper side of the bottom elastic roller 23. At the same time, the first lifting motor 25 at the bottom of the first vertical groove 24 is started to drive the first vertical screw shaft 26 to rotate. Thus, through the threaded connection between the first vertical screw shaft 26 and the lifting rod 27, the fixed shaft 28 is driven to move upward until the auxiliary elastic roller 29 fits with the machine body to provide auxiliary support for the rolling of the machine body. Step 4: Rotate the second adjusting screw 37 on the third side groove 36 to drive the second lifting column 38 to move upward along the third side groove 36, thereby driving the lifting plate 39 to move upward. Then, with the cooperation of the limiting block 41 and the limiting slot 47, the lifting carrier plate 40 is driven upward until the height of the lifting carrier plate 40 corresponds to the bottom height of the machine body. Fix the position of the second adjusting screw 37. Then place the other section of the machine body between the two sets of second limiting vertical plates 46, and drive the second dual-axis motor 43 to make the machine body fit with the second limiting vertical plates 46 to ensure that the axes of the two sections of the machine body are aligned. Step 5: Start the rotary motor 21 on the outside of the fixed plate 20 to drive the rotating long shaft 22 and the bottom elastic roller 23 to rotate together, thereby driving the fuselage to rotate between the two sets of first limit vertical plates 16 with the cooperation of the side elastic roller 19 and the auxiliary elastic roller 29, until the two sections of the aircraft fuselage are aligned. Step 6: Rotate the first adjusting screw 32 on the first side groove 30 to drive the limiting plate 35 to move upward under the threaded connection between the first adjusting screw 32 and the first lifting column 34. With the cooperation of the limiting vertical rod 33 in the second side groove 31, the limiting plate 35 is tightly fitted with the fuselage and the position of the first adjusting screw 32 is fixed. This realizes the function of docking the two sections of the aircraft fuselage, reduces the docking difficulty of the aircraft fuselage, and significantly improves the docking efficiency of the aircraft fuselage. Step 7: During fuselage docking, start the dual-axis drive motor 3 inside the main port 2 to drive the two sets of transverse threaded shafts 4 to rotate together. Under the cooperation of the symmetrical external threads, the first moving block 5 and the second moving block 6 move relative to each other along the two sets of docking slides 9. Then, under the cooperation of the side support slide plate 10 and the side sliding groove 11, the first bearing plate 7 and the second bearing plate 8 move relative to each other above the bearing base 1 until the two sections of the aircraft fuselage dock together. Step 8: After the two sections of the aircraft fuselage are docked and in contact, the second lifting motor 54 at the bottom of the second vertical groove 53 is started to drive the second vertical screw shaft 55 to rotate. This causes the locking plate 57 to move up and down through the threaded connection between the second vertical screw shaft 55 and the lifting block 56 until the locking plate 57 is at the target height position. Step 9: Start the third dual-axis motor 50 inside the third port 49 to drive the two sets of third horizontal lead screw shafts 51 to rotate together. Under the cooperation of symmetrical external threads, the two sets of third moving rods 52 move relative to each other along the intermediate groove 48, and then drive the two sets of second vertical grooves 53 to move relative to each other until the elastic anti-slip plates 58 on the two sets of locking plates 57 are tightly fitted with the two fuselage sections. This allows the two fuselage sections to be docked and locked according to the actual specifications of the aircraft fuselage, preventing gaps from appearing at the connection point of the two fuselage sections due to external forces, ensuring the stability of subsequent connection work, and completing the operation.

[0035] In summary, this invention relates to the field of aircraft fuselage docking technology, specifically to a quick docking device for aircraft fuselages with a locking mechanism. The device includes a support base and a dual-axis drive motor disposed in the center of the support base. Both output ends of the dual-axis drive motor are fixedly connected to transverse threaded shafts. A first moving block and a second moving block are respectively sleeved on the two sets of transverse threaded shafts. A first support plate and a second support plate are fixedly connected to the upper sides of the first and second moving blocks, respectively. This invention enables direct docking of two aircraft fuselage sections, reduces the difficulty of aircraft fuselage docking, significantly improves the docking efficiency, and can provide auxiliary positioning for two aircraft fuselage sections of various sizes. This significantly expands the applicability of the docking device and allows for docking and locking of two aircraft fuselage sections according to their actual specifications, preventing gaps from appearing at the joint due to external forces and ensuring the stability of subsequent connection work.

[0036] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A quick docking device for aircraft fuselage with a locking mechanism, comprising a support base (1), characterized in that, It also includes a dual-axis drive motor (3) set in the middle of the support base (1). Both output ends of the dual-axis drive motor (3) are fixedly connected to a horizontal threaded shaft (4). A first moving block (5) and a second moving block (6) are respectively sleeved on the two sets of horizontal threaded shafts (4). A first support plate (7) and a second support plate (8) are fixedly connected to the upper side of the first moving block (5) and the second moving block (6). Side support slides (10) are fixedly connected to both sides of the lower surface of the first support plate (7) and the second support plate (8). The upper side of the second bearing plate (8) is provided with two sets of first limiting vertical plates (16). The first limiting vertical plates (16) are provided with a frame opening (17). Several sets of clamping rods (18) are clamped on the inner side of the frame opening (17). A side elastic roller (19) is movably sleeved on the clamping rod (18). The upper surface of the second bearing plate (8) is fixedly connected to both sides with a fixing plate (20). A rotary motor (21) is fixedly installed on the outer side of the fixing plate (20). The output end of the rotary motor (21) is fixedly connected to a long rotating shaft (22) that passes through the fixing plate (20). A bottom elastic roller (23) is fixedly sleeved on the long rotating shaft (22). The first vertical plate (16) is fixedly connected to a first vertical groove (24) on one side. A first vertical screw shaft (26) is provided through the first vertical groove (24). A lifting rod (27) is sleeved on the first vertical screw shaft (26). A fixed shaft (28) is fixedly connected to the end of the lifting rod (27). An auxiliary elastic roller (29) is movably sleeved on the fixed shaft (28). A third side groove (36) is fixedly connected to the middle of one side of the second bearing plate (8). A second adjusting screw (37) is provided through the third side groove (36). A second lifting column (38) is sleeved on the second adjusting screw (37). A lifting plate (39) is fixedly connected to the upper end of the second lifting column (38). A lifting carrier plate (40) is fixedly connected to one side of the lifting plate (39). Limit blocks (41) are fixedly connected to both sides of the lifting carrier plate (40).

2. The aircraft fuselage quick docking device with locking mechanism according to claim 1, characterized in that: The bearing base (1) has a main opening (2) through the middle, and the dual-axis drive motor (3) is fixedly installed on the inner side of the main opening (2). The external threads of the two sets of horizontal threaded shafts (4) are symmetrically arranged, and the first moving block (5) and the second moving block (6) are respectively threadedly connected to the two sets of horizontal threaded shafts (4). The bearing base (1) has two sets of docking sliding mouths (9) through the middle, and the first moving block (5) and the second moving block (6) are respectively slidably connected to the bearing base (1) through the docking sliding mouths (9). The bearing base (1) has side sliding grooves (11) on both sides, and the lower end of the side support slide plate (10) is located inside the side sliding groove (11).

3. The aircraft fuselage quick docking device with locking mechanism according to claim 1, characterized in that: Several sets of side elastic rollers (19) are evenly distributed on the inner side of the frame opening (17). The bottom elastic roller (23) is located between two sets of fixed plates (20). The bottom end of the first vertical groove (24) is fixedly installed with a first lifting motor (25), and the first vertical screw shaft (26) is fixedly connected to the output end of the first lifting motor (25). The lifting rod (27) is threadedly connected to the first vertical screw shaft (26), and one end of the lifting rod (27) is located on the inner side of the first vertical groove (24). The two sets of auxiliary elastic rollers (29) are symmetrically arranged about the bottom elastic roller (23).

4. The aircraft fuselage quick docking device with locking mechanism according to claim 1, characterized in that: The second bearing plate (8) is fixedly connected to a first side groove (30) and a second side groove (31) on one side. A first adjusting screw (32) is provided through the first side groove (30). A limiting vertical rod (33) is fixedly connected to the inner side of the second side groove (31). A limiting plate (35) is provided above the first side groove (30) and the second side groove (31). Two sets of first lifting columns (34) are fixedly connected to the limiting plate (35). One set of first lifting columns (34) is threadedly connected to the first adjusting screw (32), and the other set of first lifting columns (34) is slidably connected to the limiting vertical rod (33).

5. The aircraft fuselage quick docking device with locking mechanism according to claim 1, characterized in that: The second lifting column (38) is threadedly connected to the second adjusting screw (37), and the second lifting column (38) is located inside the third side groove (36). Two sets of second limiting vertical plates (46) are provided on the upper side of the first bearing plate (7). The bottom of the second limiting vertical plate (46) is provided with a limiting slot (47), and the limiting block (41) is located inside the limiting slot (47).

6. The aircraft fuselage quick docking device with locking mechanism according to claim 5, characterized in that: The second bearing plate (8) has a first through opening (12) in the middle. A first dual-axis motor (13) is fixedly installed on the inner side of the first through opening (12). The two output ends of the first dual-axis motor (13) are fixedly connected to a first horizontal lead screw shaft (14). A first moving rod (15) is sleeved on the first horizontal lead screw shaft (14). The first bearing plate (7) has a second through opening (42) in the middle. A second dual-axis motor (43) is fixedly installed on the inner side of the second through opening (42). The two output ends of the second dual-axis motor (43) are fixedly connected to a second horizontal lead screw shaft (44). A second moving rod (45) is sleeved on the second horizontal lead screw shaft (44).

7. A quick docking device for aircraft fuselage with a locking mechanism according to claim 6, characterized in that: The external threads of the two sets of first horizontal lead screw shafts (14) are symmetrically arranged, and the first moving rod (15) is threadedly connected to the first horizontal lead screw shaft (14). The first moving rod (15) is movably connected to the second bearing plate (8). The first limiting vertical plate (16) is engaged with the first moving rod (15). The two sets of first limiting vertical plates (16) are symmetrically arranged about the first port (12). The external threads of the two sets of second horizontal lead screw shafts (44) are symmetrically arranged, and the second moving rod (45) is threadedly connected to the second horizontal lead screw shaft (44). The second moving rod (45) is movably connected to the first bearing plate (7). The second limiting vertical plate (46) is engaged with the second moving rod (45). The two sets of second limiting vertical plates (46) are symmetrically arranged about the second port (42).

8. The aircraft fuselage quick docking device with locking mechanism according to claim 1, characterized in that: The upper middle of the support base (1) is fixedly connected to a middle groove (48). A third through-hole (49) is provided in the middle of the middle groove (48), and a third dual-axis motor (50) is fixedly installed on the inner side of the third through-hole (49). Both output ends of the third dual-axis motor (50) are fixedly connected to a third horizontal lead screw shaft (51). A third moving rod (52) is sleeved on the third horizontal lead screw shaft (51). The outer end of the third moving rod (52) is fixedly connected to a second vertical groove (53). A second vertical lead screw shaft (55) is provided through the second vertical groove (53). A lifting block (56) is sleeved on the second vertical lead screw shaft (55). A locking plate (57) is fixedly connected to the end of the lifting block (56). An elastic anti-slip plate (58) is fixedly connected to the locking plate (57).

9. A quick docking device for aircraft fuselage with a locking mechanism according to claim 8, characterized in that: The external threads of the two sets of third horizontal lead screw shafts (51) are symmetrically arranged. The third moving rod (52) is threadedly connected to the third horizontal lead screw shaft (51) and is movably connected to the intermediate groove (48). The bottom end of the second vertical groove (53) is fixedly installed with a second lifting motor (54) and the second vertical lead screw shaft (55) is fixedly connected to the output end of the second lifting motor (54). The second vertical lead screw shaft (55) is threadedly connected to the lifting block (56) and the lifting block (56) is located inside the second vertical groove (53). The vertical cross-sectional shape of the locking plate (57) and the elastic anti-slip plate (58) is arc-shaped.

10. A method for rapid docking of an aircraft fuselage with a locking mechanism, characterized in that, The method comprises: using the aircraft fuselage quick docking device according to any one of claims 1 to 9, the method comprising: Step 1: Start the first dual-axis motor (13) inside the first port (12) to drive the two sets of first horizontal lead screw shafts (14) to rotate together, thereby driving the two sets of first moving rods (15) to move relative to each other along the second bearing plate (8) under the cooperation of symmetrical external threads, and then driving the two sets of first limiting vertical plates (16) to move relative to each other until the side elastic roller (19) is in contact with a section of the machine body; Step 2: Start the second dual-axis motor (43) inside the second port (42) to drive the two sets of second horizontal lead screw shafts (44) to rotate together, thereby driving the two sets of second moving rods (45) to move relative to each other along the first bearing plate (7) under the cooperation of symmetrical external threads, and then driving the two sets of second limiting vertical plates (46) to move relative to each other until the two sets of second limiting vertical plates (46) are in contact with the other section of the machine body; Step 3: When a section of the machine body is located between the two sets of first limiting vertical plates (16), the machine body is brought into contact with the side elastic roller (19) by the drive of the first dual-axis motor (13). At this time, the machine body is placed on the upper side of the bottom elastic roller (23). At the same time, the first lifting motor (25) at the bottom of the first vertical groove (24) is started to drive the first vertical screw shaft (26) to rotate. Thus, the fixed shaft (28) is driven to move upward through the threaded connection between the first vertical screw shaft (26) and the lifting rod (27) until the auxiliary elastic roller (29) is in contact with the machine body to provide auxiliary support for the rolling of the machine body. Step 4: Rotate the second adjusting screw (37) on the third side groove (36) to drive the second lifting column (38) to move upward along the third side groove (36), thereby driving the lifting plate (39) to move upward, and then, with the cooperation of the limiting block (41) and the limiting slot (47), drive the lifting carrier plate (40) to move upward until the height of the lifting carrier plate (40) corresponds to the bottom height of the machine body, and fix the position of the second adjusting screw (37), and then place the other section of the machine body between the two sets of second limiting vertical plates (46), and drive the second dual-axis motor (43) to make the machine body fit with the second limiting vertical plate (46); Step 5: Start the rotary motor (21) on the outside of the fixed plate (20) to drive the rotating long shaft 22 and the bottom elastic roller (23) to rotate together, thereby driving the fuselage to rotate between the two sets of first limit vertical plates (16) with the cooperation of the side elastic roller (19) and the auxiliary elastic roller (29) until the two sections of the aircraft fuselage are aligned. Step 6: Rotate the first adjusting screw (32) on the first side groove (30) to drive the limiting plate (35) to move upward under the threaded connection between the first adjusting screw (32) and the first lifting column (34), and with the cooperation of the limiting vertical rod (33) in the second side groove (31), make the limiting plate (35) fit tightly against the machine body and fix the position of the first adjusting screw (32); Step 7: When the fuselage is docked, start the dual-axis drive motor (3) inside the main port (2) to drive the two sets of transverse threaded shafts (4) to rotate together. Under the cooperation of the symmetrical external threads, the first moving block (5) and the second moving block (6) move relative to each other along the two sets of docking slides (9). Then, under the cooperation of the side support slide plate (10) and the side sliding groove (11), the first bearing plate (7) and the second bearing plate (8) move relative to each other above the bearing base (1) until the two sections of the aircraft fuselage are docked together. Step 8: After the two sections of the aircraft fuselage are docked and contacted, the second lifting motor (54) at the bottom of the second vertical groove (53) is started to drive the second vertical screw shaft (55) to rotate, thereby driving the locking plate (57) to move up and down through the threaded connection between the second vertical screw shaft (55) and the lifting block (56) until the locking plate (57) is located at the target height position; Step 9: Start the third dual-axis motor (50) inside the third port (49) to drive the two sets of third horizontal lead screw shafts (51) to rotate together, thereby driving the two sets of third moving rods (52) to move relative to each other along the middle groove (48) under the cooperation of symmetrical external threads, and then driving the two sets of second vertical grooves (53) to move relative to each other until the elastic anti-slip plates (58) on the two sets of locking plates (57) are tightly fitted with the two sections of the machine body.

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