Rapid installation device and method for aircraft interior trim parts

Abstract

The invention belongs to the technical field of airplane interior trim part installation, and discloses an airplane interior trim part rapid installation device and method.The airplane interior trim part rapid installation device comprises a bearing base and a vertical groove body located on the upper side of the bearing base, a lifting base is arranged on the upper side of the vertical groove body, a rotating block is arranged on the inner side of the lifting base, and a connecting frame body is fixedly connected to the rotating block; a mounting disc is arranged above the connecting frame body, a fixed shaft rod is fixedly connected to the middle position of the upper side of the mounting disc, and the fixed shaft rod is sleeved with a movable block; the side face of the movable block is fixedly connected with four sets of outer groove bodies, the inner sides of the four sets of outer groove bodies are fixedly connected with first limiting sliding rods in a clamped mode, the four sets of first limiting sliding rods are sleeved with first sliding blocks, the upper sides of the four sets of first sliding blocks are fixedly connected with movable groove bodies, and the inner sides of the four sets of movable groove bodies are fixedly connected with second limiting sliding rods in a clamped mode. And second sliding blocks are connected to the four sets of second limiting sliding rods in a sleeving mode correspondingly, limiting clamping plates are fixedly connected to the upper sides of the four sets of second sliding blocks correspondingly, and the technical problems that when an existing mounting clamp is used, only aircraft interior trim parts of a small number of specifications can be clamped, the clamping range is small, and using limitation is large are solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft interior decoration component installation, and in particular relates to a device and method for quickly installing aircraft interior decoration components. Background Art

[0002] Aircraft interiors refer to the various functional, decorative, and structural components installed within an aircraft's cabin and cockpit, including seats, luggage racks, sidewall panels, ceilings, and floor coverings. They not only provide a comfortable environment for passengers and crew, but also fulfill important functions such as safety, sound insulation, heat insulation, and fire protection. The design and manufacture of interior components must meet strict aviation standards to ensure their reliability and durability during flight. Aircraft interior mounting fixtures are tools specifically used for the installation and positioning of aircraft interior components, designed to ensure precise installation of interior components within the aircraft. These fixtures are typically made of high-strength, lightweight materials to ensure durability and portability.

[0003] Patent publication number CN208930720U discloses a fixture for stably clamping interior trim. By installing a cylinder on the outside of a baffle to clamp the trim, the fixture is quickly and accurately secured, resolving the time-consuming issue of securing trim in existing technologies. To clamp the trim, the trim is placed within the area where the baffle is located, and then the cylinder is activated. The cylinder's telescopic rod gradually approaches the trim, pushing it into position and tightening it, achieving the desired effect of quickly and accurately securing the trim. However, existing mounting fixtures still have certain drawbacks. They can typically only clamp a few specifications of aircraft interior trim, have a relatively small clamping range, and are subject to significant limitations. Therefore, there is an urgent need for a rapid aircraft interior fixture installation fixture to address the shortcomings of existing fixtures and improve the installation safety of aircraft interior trim. Summary of the Invention

[0004] In response to the shortcomings of the existing technology, the present invention provides a quick installation fixture for aircraft interior parts, which solves the technical problems that the existing installation fixtures proposed in the above background technology still have certain defects when used. They can usually only clamp aircraft interior parts of a few specifications, have a relatively small clamping range, and have large usage limitations.

[0005] To achieve the above object, the present invention provides the following technical solutions: A quick installation fixture for aircraft interior parts includes a load-bearing base and a vertical trough located on the upper side of the load-bearing base. A lifting seat is provided on the upper side of the vertical trough, a rotating block is provided on the inner side of the lifting seat, a connecting frame is fixedly connected to the rotating block, a mounting plate is provided above the connecting frame, a fixed shaft is fixedly connected to the middle position of the upper side of the mounting plate, and a movable block is sleeved on the fixed shaft. Four groups of outer trough bodies are fixedly connected to the side surfaces of the movable block, the inner sides of the four groups of outer trough bodies are fixedly connected with the first limiting slide rods, the four groups of the first limiting slide rods are sleeved with the first sliding block, the upper sides of the four groups of the first sliding blocks are fixedly connected to the movable trough bodies, the inner sides of the four groups of the movable trough bodies are fixedly connected with the second limiting slide rods, the four groups of the second limiting slide rods are sleeved with the second sliding block, and the upper sides of the four groups of the second sliding blocks are fixedly connected with the limiting splints.

[0006] As a further solution of the present invention, a rotating shaft hole is provided through the middle position of the movable block, and the movable block is movably connected to the fixed shaft rod through the rotating shaft hole, the four groups of outer troughs are evenly spaced on the periphery of the movable block, the four groups of the first sliding blocks are all provided with a first sliding hole, and the first sliding block is movably connected to the first limiting sliding rod through the first sliding hole, the four groups of the first limiting sliding rods are all provided with a first compression spring, and the four groups of first compression springs and the four groups of first sliding blocks are respectively located inside the four groups of outer troughs.

[0007] As a further solution of the present invention, the four groups of second sliding blocks are all provided with a second sliding hole, and the second sliding blocks are movably connected to the second limiting sliding rod through the second sliding hole. The four groups of second limiting sliding rods are all provided with a second compression spring. The four groups of second compression springs and the four groups of second sliding blocks are respectively located inside the four groups of movable grooves. The vertical cross-section of the four groups of limiting splints are all L-shaped, and the upper end of the limiting splint is arc-shaped.

[0008] As a further solution of the present invention, a rotating motor is fixedly embedded in the middle position of the bottom of the supporting base, and the output end of the rotating motor is fixedly connected to the first rotating shaft that passes through the supporting base, and the bottom of the vertical trough body is fixedly connected to four groups of rotating connecting plates, and the lower sides of the four groups of rotating connecting plates are fixedly connected to the sliding plates. The edge position of the supporting base is provided with an annular groove, and the bottom of the vertical trough body is penetrated by a notch, and a lifting motor is fixedly installed inside the notch, and the output end of the lifting motor is fixedly connected to a vertical screw shaft that passes through the vertical trough body, and a lifting column is sleeved on the vertical screw shaft, and a tilting motor is fixedly installed on the outer side of the lifting seat, and the output end of the tilting motor is fixedly connected to the second rotating shaft that passes through the lifting seat.

[0009] As a further solution of the present invention, the first rotating shaft is fixedly connected to the vertical trough body, the four groups of rotating connecting plates are respectively located around the vertical trough body, the four groups of sliding plates are all located inside the annular groove, the four sides of the vertical trough body are fixedly connected with support plates, the bottoms of the four groups of support plates are provided with limiting grooves, the supporting base is fixedly sleeved with limiting rings, and the four groups of support plates are respectively connected to the limiting rings through the limiting grooves.

[0010] As a further solution of the present invention, the lifting seat is fixedly connected to the lifting column, and the cross-section of the lifting seat is U-shaped. The vertical screw shaft is threadedly connected to the lifting column, and the lifting column is located inside the vertical trough.

[0011] As a further solution of the present invention, the rotating block is fixedly sleeved on the second rotating shaft, and the rotating block is located inside the lifting seat. The inner side of the connecting frame is fixedly connected to a hydraulic cylinder, and the output end of the hydraulic cylinder is fixedly connected to a telescopic rod, and the telescopic rod is fixedly connected to the mounting plate.

[0012] As a further solution of the present invention, an annular block is fixedly sleeved in the middle position of the vertical trough body, and the annular block is hinged to four groups of rotating long plates through four groups of connecting hinges. The ends of the four groups of rotating long plates are fixedly connected with a clamping block, the upper side of the annular block is fixedly connected with an elastic net, and the upper end of the elastic net is fixedly connected with an elastic rope. The bottoms of the four groups of rotating long plates are penetrated by fastening bolts, and threaded slots are penetrated around the annular block.

[0013] As a further solution of the present invention, the annular block is shaped like a U-shape, and the four groups of rotating long plates are respectively located around the vertical trough body. The rotation range of the rotating long plates through the connecting hinges is 0-90°, and the elastic net is located on the periphery of the vertical trough body. The elastic rope is connected to the four groups of clamping blocks, and the fastening bolt passes through the rotating long plate and cooperates with the threaded clamping groove to be threadedly connected to the annular block.

[0014] The present invention provides a device and method for quickly installing aircraft interior parts, comprising a supporting base and a vertical trough located above the supporting base, a lifting seat provided on the upper side of the vertical trough, a rotating block provided inside the lifting seat, a connecting frame fixedly connected to the rotating block, a mounting plate provided above the connecting frame, and a fixed shaft fixedly connected to the middle position of the upper side of the mounting plate. The present invention can quickly clamp a variety of plate-shaped aircraft interior parts of different specifications and sizes, significantly increasing the installation and clamping range of aircraft interior parts, having fewer limitations on use, and being able to adjust the position of the mounting fixture according to the installation position of the aircraft interior part, having a high degree of automation and reducing the labor intensity of the installer. It can also prevent the aircraft interior part and its components from being damaged by falling during the installation process, significantly improving the installation safety of the aircraft interior part. BRIEF DESCRIPTION OF THE DRAWINGS In order to more clearly illustrate the embodiments of the present invention and the technical solutions in the prior art, the following briefly describes the drawings required for use in the embodiments: Figure 1 It is a schematic diagram of the overall structure of the present invention; Figure 2 Schematic diagram of the connection structure of the movable block in the present invention; Figure 3 Schematic diagram of the connection structure between the outer tank body and the movable tank body in the present invention; Figure 4 Schematic diagram of the connection structure of the support base in the present invention; Figure 5 Schematic diagram of the connection structure of the vertical trough body in the present invention; Figure 6 Schematic diagram of the connection structure of the connecting frame in the present invention; Figure 7 Schematic diagram of the connection structure of the elastic net in the present invention; Figure 8 Schematic diagram of the connection structure of the ring blocks in the present invention.

[0015] Figure: 1, bearing base; 2, vertical trough; 3, lifting seat; 4, rotating block; 5, connecting frame; 6, mounting plate; 7, fixed shaft; 8, movable block; 9, rotating shaft hole; 10, outer trough; 11, first limiting slide; 12, first sliding block; 13, first sliding hole; 14, first compression spring; 15, movable trough; 16, second limiting slide; 17, second sliding block; 18, second sliding hole; 19, second compression spring; 20, limiting clamp; 22, rotating motor; 2 3. First rotating shaft; 24. Rotating connecting plate; 25. Sliding plate; 26. Annular groove; 27. Support plate; 28. Limiting groove; 29. ​​Limiting ring; 30. Notch; 31. Lifting motor; 32. Vertical screw shaft; 33. Lifting column; 34. Tilt motor; 35. Second rotating shaft; 36. Hydraulic cylinder; 37. Telescopic rod; 38. Annular block; 39. Elastic net; 40. Elastic rope; 41. Rotating long board; 42. Connecting hinge; 43. Block; 44. Fastening bolt; 45. Threaded slot. DETAILED DESCRIPTION

[0016] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0017] See also Figures 1 to 8The present invention provides a rapid installation device for aircraft interior parts, comprising a bearing base 1, a vertical trough body 2 located on the upper side of the bearing base 1, a lifting seat 3 being provided on the upper side of the vertical trough body 2, a rotating block 4 being provided on the inner side of the lifting seat 3, a connecting frame 5 being fixedly connected to the rotating block 4, a mounting plate 6 being provided above the connecting frame 5, a fixed shaft 7 being fixedly connected to the middle position of the upper side of the mounting plate 6, a movable block 8 being sleeved on the fixed shaft 7, and a side of the movable block 8 being fixedly connected to the connecting frame 5. There are four groups of outer trough bodies 10, the inner sides of the four groups of outer trough bodies 10 are all fixedly connected with the first limiting slide rod 11, the four groups of first limiting slide rods 11 are all sleeved with the first sliding block 12, the upper sides of the four groups of first sliding blocks 12 are all fixedly connected with the movable trough body 15, the inner sides of the four groups of movable trough bodies 15 are all fixedly connected with the second limiting slide rod 16, the four groups of second limiting slide rods 16 are all sleeved with the second sliding block 17, and the upper sides of the four groups of second sliding blocks 17 are all fixedly connected with the limiting splint 20.

[0018] A rotating shaft hole 9 is provided through the middle position of the movable block 8, and the movable block 8 is movably connected to the fixed shaft rod 7 through the rotating shaft hole 9. The four groups of outer troughs 10 are evenly spaced on the periphery of the movable block 8. The four groups of first sliding blocks 12 are all provided with first sliding holes 13, and the first sliding blocks 12 are movably connected to the first limiting slide rod 11 through the first sliding holes 13. The four groups of first limiting slide rods 11 are all provided with first compression springs 14, and the four groups of first compression springs 14 and the four groups of first sliding blocks 12 are respectively located inside the four groups of outer troughs 10.

[0019] The four groups of second sliding blocks 17 are all penetrated by a second sliding hole 18, and the second sliding blocks 17 are movably connected to the second limiting slide rod 16 through the second sliding hole 18. The four groups of second limiting slide rods 16 are all sleeved with a second compression spring 19. The four groups of second compression springs 19 and the four groups of second sliding blocks 17 are respectively located inside the four groups of moving grooves 15. The vertical cross-section of the four groups of limiting splints 20 are all L-shaped, and the upper ends of the limiting splints 20 are arc-shaped.

[0020] Specifically, when the plate-shaped aircraft interior decoration component is small, the four groups of second sliding blocks 17 are moved relatively along the four groups of movable grooves 15 respectively through the active connection between the second sliding block 17 and the second limiting slide bar 16, so that the four groups of limiting clamps 20 are moved relatively, and the four groups of second compression springs 19 are used to make the four groups of limiting clamps 20 fit tightly with the plate-shaped aircraft interior decoration component. When the plate-shaped aircraft interior decoration component is large, on the basis of the above steps, the four groups of first sliding blocks 12 are moved relatively along the four groups of outer grooves 10 respectively through the active connection between the first sliding block 12 and the first limiting slide bar 11, thereby driving the four groups of movable grooves 15 to move relatively, and the four groups of limiting clamps 20 are fit tightly with the plate-shaped aircraft interior decoration component through the four groups of first compression springs 14, which can quickly clamp plate-shaped aircraft interior decoration components of various sizes and specifications, significantly improving the installation and clamping range of aircraft interior decoration components, and having fewer limitations on use.

[0021] A rotating motor 22 is fixedly embedded in the middle position of the bottom of the supporting base 1, and the output end of the rotating motor 22 is fixedly connected to the first rotating shaft 23 that passes through the supporting base 1. Four groups of rotating connecting plates 24 are fixedly connected to the bottom of the vertical trough body 2, and the lower sides of the four groups of rotating connecting plates 24 are fixedly connected to sliding plates 25. An annular groove 26 is provided at the edge of the supporting base 1, and a notch 30 is provided through the bottom of the vertical trough body 2. A lifting motor 31 is fixedly installed inside the notch 30, and the output end of the lifting motor 31 is fixedly connected to a vertical screw shaft 32 that passes through the vertical trough body 2. A lifting column 33 is sleeved on the vertical screw shaft 32. A tilting motor 34 is fixedly installed on the outside of the lifting seat 3, and the output end of the tilting motor 34 is fixedly connected to the second rotating shaft 35 that passes through the lifting seat 3.

[0022] The first rotating shaft 23 is fixedly connected to the vertical trough body 2, the four groups of rotating connecting plates 24 are respectively located around the vertical trough body 2, the four groups of sliding plates 25 are all located inside the annular groove 26, and the four sides of the vertical trough body 2 are fixedly connected with support plates 27. The bottoms of the four groups of support plates 27 are all provided with limiting grooves 28. A limiting ring 29 is fixedly sleeved on the supporting base 1, and the four groups of support plates 27 are respectively connected to the limiting ring 29 through the limiting grooves 28.

[0023] The lifting seat 3 is fixedly connected to the lifting column 33 , and the cross-section of the lifting seat 3 is U-shaped. The vertical screw shaft 32 is threadedly connected to the lifting column 33 , and the lifting column 33 is located inside the vertical trough body 2 .

[0024] The rotating block 4 is fixedly sleeved on the second rotating shaft 35, and the rotating block 4 is located inside the lifting seat 3. The inner side of the connecting frame 5 is fixedly connected to the hydraulic cylinder 36, and the output end of the hydraulic cylinder 36 is fixedly connected to the telescopic rod 37, which is fixedly connected to the mounting plate 6.

[0025] Specifically, by starting the rotating motor 22 on the supporting base 1 to drive the first rotating shaft 23 to rotate, the vertical slot body 2 is driven to rotate on the upper side of the supporting base 1 by rotating the connecting plate 24 and the sliding plate 25 in conjunction with the annular groove 26, and then the tilting motor 34 outside the lifting seat 3 is started to drive the second rotating shaft 35 to rotate, thereby driving the rotating block 4 to rotate, and then driving the aircraft interior to tilt and rotate until the aircraft interior is in the target position, and then the lifting motor 31 inside the slot 30 is started to drive the vertical screw shaft 32 to rotate, thereby The threaded connection with the lifting column 33 drives the lifting column 33 to move upward along the vertical trough body 2, thereby driving the aircraft interior decoration component to move vertically upward, and then the hydraulic cylinder 36 inside the connecting frame 5 is activated to drive the telescopic rod 37 to extend until the aircraft interior decoration component is pushed to the installation position, and the movable block 8 is driven to rotate by the cooperation of the fixed shaft rod 7 and the rotating shaft hole 9, thereby driving the installation fixture to rotate to ensure the corresponding installation of the aircraft interior decoration component. The position of the installation fixture can be adjusted according to the installation position of the aircraft interior decoration component, which has a high degree of automation and reduces the labor intensity of the installer.

[0026] An annular block 38 is fixedly sleeved in the middle position of the vertical trough body 2, and the annular block 38 is hingedly connected to four groups of rotating long plates 41 through four groups of connecting hinges 42. The ends of the four groups of rotating long plates 41 are fixedly connected with a clamping block 43, and the upper side of the annular block 38 is fixedly connected to an elastic net 39, and the upper end of the elastic net 39 is fixedly connected to an elastic rope 40. The bottom of the four groups of rotating long plates 41 is penetrated by a fastening bolt 44, and the four sides of the annular block 38 are penetrated by a threaded clamping groove 45.

[0027] The annular block 38 is shaped like a U-shaped rectangle, and four groups of rotating long plates 41 are respectively located around the vertical trough body 2. The rotating long plates 41 rotate in a range of 0-90° through the connecting hinges 42. The elastic net 39 is located on the periphery of the vertical trough body 2. The elastic rope 40 is connected to the four groups of clamping blocks 43. The fastening bolt 44 passes through the rotating long plates 41 and cooperates with the threaded clamping groove 45 to be threadedly connected to the annular block 38.

[0028] Specifically, the four sets of rotating long plates 41 are rotated together to a horizontal state through the connecting hinges 42 on the annular block 38, and then the four sets of fastening bolts 44 are respectively passed through the four sets of rotating long plates 41 and threadedly connected to the annular block 38 in cooperation with the threaded slots 45. At this time, the elastic net 39 is extended with the cooperation of the elastic rope 40 and the four sets of blocks 43. When the aircraft interior parts and their installed components fall, they can be received by the elastic net 39, and the four sets of support plates 27 can be used to ensure the stable placement of the vertical trough body 2, which can prevent the aircraft interior parts and their components from being damaged due to falling during the installation process of the aircraft interior parts, thereby significantly improving the installation safety of the aircraft interior parts.

[0029] Working principle: First, the staff places the aircraft interior decoration component on the installation fixture. When the plate-shaped aircraft interior decoration component is small, the four groups of second sliding blocks 17 are movablely connected with the second limiting slide bar 16 to make the four groups of second sliding blocks 17 move relatively along the four groups of moving grooves 15 respectively, thereby making the four groups of limiting splints 20 move relatively, and the four groups of second compression springs 19 make the four groups of limiting splints 20 fit tightly with the plate-shaped aircraft interior decoration component. When the plate-shaped aircraft interior decoration component is large, on the basis of the above steps, the four groups of first sliding blocks 12 are movablely connected with the first limiting slide bar 11 to make the four groups of first sliding blocks 12 move relatively along the four groups of outer grooves 10 respectively, thereby driving the four groups of moving grooves 15 to move relatively, and through the four groups of second compression springs 19 A compression spring 14 makes the four groups of limit clamps 20 fit tightly with the plate-shaped aircraft interior parts, and can quickly clamp a variety of plate-shaped aircraft interior parts of different sizes, significantly improving the installation and clamping range of aircraft interior parts, and having fewer limitations. Secondly, when installing the aircraft interior parts, the rotating motor 22 on the supporting base 1 is started to drive the first rotating shaft 23 to rotate, thereby driving the vertical trough body 2 to rotate on the upper side of the supporting base 1 by rotating the connecting plate 24 and the sliding plate 25 in conjunction with the annular groove 26, and then starting the tilting motor 34 on the outer side of the lifting seat 3 to drive the second rotating shaft 35 to rotate, thereby driving the rotating block 4 to rotate, and then driving the aircraft interior parts to tilt and rotate until the aircraft interior is The part is in the target position, and then the lifting motor 31 inside the slot 30 is started to drive the vertical screw shaft 32 to rotate, thereby driving the lifting column 33 to move upward along the vertical slot body 2 through the threaded connection between the vertical screw shaft 32 and the lifting column 33, thereby driving the aircraft interior decoration part to move vertically upward, and then starting the hydraulic cylinder 36 inside the connecting frame 5 to drive the telescopic rod 37 to extend, thereby driving the installation plate 6 to move until the aircraft interior decoration part is pushed to the installation position, and through the cooperation of the fixed shaft rod 7 and the rotating shaft hole 9 to drive the movable block 8 to rotate, thereby driving the installation fixture to rotate, to ensure the corresponding installation of the aircraft interior decoration part, and the position of the installation fixture can be adjusted according to the installation position of the aircraft interior decoration part, and automatically The degree of automation is high and the labor intensity of the installers is reduced. Finally, the four sets of rotating long plates 41 are rotated together to a horizontal state through the connecting hinges 42 on the annular block 38, and then the four sets of fastening bolts 44 are respectively passed through the four sets of rotating long plates 41 and threadedly connected with the annular block 38 in cooperation with the threaded slots 45. At this time, the elastic net 39 is extended under the cooperation of the elastic rope 40 and the four sets of blocks 43. When the aircraft interior parts and their installed parts fall, they can be taken up by the elastic net 39, and the four sets of support plates 27 can be used to ensure the stable placement of the vertical trough body 2, which can prevent the aircraft interior parts and their components from being damaged due to falling during the installation process of the aircraft interior parts, significantly improve the installation safety of the aircraft interior parts, and complete the operation.

[0030] Compared with the prior art, the present invention has the following beneficial effects: 1. When the plate-shaped aircraft interior decoration component is small, the four groups of second sliding blocks are respectively moved relatively along the four groups of moving grooves through the active connection between the second sliding block and the second limiting sliding rod, so that the four groups of limiting clamps are relatively moved, and the four groups of limiting clamps are all tightly fitted with the plate-shaped aircraft interior decoration component through the four groups of second compression springs. When the plate-shaped aircraft interior decoration component is large, on the basis of the above steps, the four groups of first sliding blocks are respectively moved relatively along the four groups of outer grooves through the active connection between the first sliding block and the first limiting sliding rod, thereby driving the four groups of moving grooves to move relatively, and the four groups of limiting clamps are all tightly fitted with the plate-shaped aircraft interior decoration component through the four groups of first compression springs. It can quickly clamp plate-shaped aircraft interior decoration components of various specifications and sizes, significantly improves the installation and clamping range of aircraft interior decoration components, and has fewer limitations on use.

[0031] 2. By starting the rotating motor on the carrying base, the first rotating shaft is driven to rotate, thereby driving the vertical trough body to rotate on the upper side of the carrying base through the rotating connecting plate and the sliding plate in cooperation with the annular groove, and then starting the tilting motor on the outer side of the lifting seat to drive the second rotating shaft to rotate, thereby driving the rotating block to rotate, and then driving the aircraft interior to tilt and rotate until the aircraft interior is in the target position, and then starting the lifting motor inside the slot to drive the vertical screw shaft to rotate, thereby driving the lifting column to move upward along the vertical trough body through the threaded connection between the vertical screw shaft and the lifting column, thereby driving the aircraft interior to move vertically upward, and then starting the hydraulic cylinder inside the connecting frame to drive the telescopic rod to extend until the aircraft interior is pushed to the installation position, and driving the movable block to rotate through the cooperation of the fixed shaft and the rotating shaft hole, thereby driving the installation fixture to rotate, to ensure the corresponding installation of the aircraft interior, and the position of the installation fixture can be adjusted according to the installation position of the aircraft interior, with a high degree of automation and reduced labor intensity of the installer.

[0032] 3. The four sets of rotating long plates are rotated to a horizontal state together through the connecting hinges on the annular block, and then the four sets of fastening bolts are respectively passed through the four sets of rotating long plates and matched with the threaded slots to be threadedly connected to the annular block. At this time, the elastic net is extended under the cooperation of the elastic rope and the four sets of clamping blocks. When the aircraft interior parts and their installed parts fall, they can be received by the elastic net, and the four sets of support plates can ensure the stable placement of the vertical trough body, which can prevent the aircraft interior parts and their components from being damaged due to falling during the installation process of the aircraft interior parts, thereby significantly improving the installation safety of the aircraft interior parts.

Claims

1. A rapid installation device for aircraft interior parts, characterized in that: The device includes a bearing base, and also includes a vertical trough body located on the upper side of the bearing base, a lifting seat is provided on the upper side of the vertical trough body, a rotating block is provided on the inner side of the lifting seat, a connecting frame is fixedly connected to the rotating block, a mounting plate is provided above the connecting frame, a fixed shaft is fixedly connected to the middle position of the upper side of the mounting plate, and a movable block is sleeved on the fixed shaft; Four groups of outer trough bodies are fixedly connected to the side surfaces of the movable block, the inner sides of the four groups of outer trough bodies are fixedly connected with the first limiting slide rods, the four groups of the first limiting slide rods are sleeved with the first sliding block, the upper sides of the four groups of the first sliding blocks are fixedly connected to the movable trough bodies, the inner sides of the four groups of the movable trough bodies are fixedly connected with the second limiting slide rods, the four groups of the second limiting slide rods are sleeved with the second sliding block, and the upper sides of the four groups of the second sliding blocks are fixedly connected with the limiting splints.

2. The rapid installation device for aircraft interior parts according to claim 1, characterized in that: A rotating shaft hole is provided through the middle position of the movable block, and the movable block is movably connected to the fixed shaft rod through the rotating shaft hole. The four groups of outer troughs are evenly spaced on the periphery of the movable block. The four groups of first sliding blocks are all provided with a first sliding hole, and the first sliding block is movably connected to the first limiting sliding rod through the first sliding hole. The four groups of first limiting sliding rods are all provided with a first compression spring, and the four groups of first compression springs and the four groups of first sliding blocks are respectively located inside the four groups of outer troughs.

3. The rapid installation device for aircraft interior parts according to claim 2, characterized in that: The four groups of second sliding blocks are all provided with a second sliding hole, and the second sliding blocks are movably connected to the second limiting sliding rod through the second sliding hole. The four groups of second limiting sliding rods are all provided with a second compression spring. The four groups of second compression springs and the four groups of second sliding blocks are respectively located inside the four groups of moving grooves. The vertical cross-section of the four groups of limiting splints is all L-shaped, and the upper end of the limiting splint is arc-shaped.

4. The rapid installation device for aircraft interior parts according to claim 3, characterized in that: A rotating motor is fixedly embedded in the middle position of the bottom of the carrying base, and an output end of the rotating motor is fixedly connected to the first rotating shaft that passes through the carrying base, and four sets of rotating connecting plates are fixedly connected to the bottom of the vertical trough body, and the lower sides of the four sets of rotating connecting plates are fixedly connected to the sliding plates. An annular groove is provided at the edge position of the carrying base, and a notch is provided through the bottom of the vertical trough body, and a lifting motor is fixedly installed inside the notch, and the output end of the lifting motor is fixedly connected to a vertical screw shaft that passes through the vertical trough body, and a lifting column is sleeved on the vertical screw shaft, and a tilting motor is fixedly installed on the outer side of the lifting seat, and the output end of the tilting motor is fixedly connected to the second rotating shaft that passes through the lifting seat.

5. The rapid installation device for aircraft interior parts according to claim 4, characterized in that: The first rotating shaft is fixedly connected to the vertical trough body, the four groups of rotating connecting plates are respectively located around the vertical trough body, the four groups of sliding plates are all located inside the annular groove, the four sides of the vertical trough body are fixedly connected with support plates, the bottoms of the four groups of support plates are provided with limiting grooves, the supporting base is fixedly sleeved with limiting rings, and the four groups of support plates are respectively connected to the limiting rings through the limiting grooves.

6. The rapid installation device for aircraft interior parts according to claim 5, characterized in that: The lifting seat is fixedly connected to the lifting column, and the cross-section of the lifting seat is U-shaped. The vertical screw shaft is threadedly connected to the lifting column, and the lifting column is located inside the vertical trough.

7. The rapid installation device for aircraft interior parts according to claim 6, characterized in that: The rotating block is fixedly sleeved on the second rotating shaft, and the rotating block is located inside the lifting seat. The inner side of the connecting frame is fixedly connected to a hydraulic cylinder, and the output end of the hydraulic cylinder is fixedly connected to a telescopic rod, and the telescopic rod is fixedly connected to the mounting plate.

8. The rapid installation device for aircraft interior parts according to claim 7, characterized in that: An annular block is fixedly sleeved in the middle position of the vertical trough body, and the annular block is hinged to four groups of rotating long plates through four groups of connecting hinges. The ends of the four groups of rotating long plates are fixedly connected with a clamping block, the upper side of the annular block is fixedly connected with an elastic net, and the upper end of the elastic net is fixedly connected with an elastic rope. The bottoms of the four groups of rotating long plates are penetrated by fastening bolts, and threaded slots are penetrated around the annular block.

9. The rapid installation device for aircraft interior parts according to claim 7, characterized in that: The annular block is shaped like a U-shaped rectangle, and the four groups of rotating long plates are respectively located around the vertical trough body. The rotation range of the rotating long plates through the connecting hinges is 0-90°. The elastic net is located on the periphery of the vertical trough body, and the elastic rope is connected to the four groups of clamping blocks. The fastening bolt passes through the rotating long plate and cooperates with the threaded clamping groove to be threadedly connected to the annular block.

10. A method for rapid installation of aircraft interior parts, applied to the device according to any one of claims 1 to 9, characterized in that: The method comprises: First, the aircraft interior component is placed on the mounting fixture. When the plate-shaped aircraft interior component is relatively small, the movable connection between the second sliding block and the second limiting slide rod causes the four sets of second sliding blocks to move relative to each other along the four sets of movable grooves, thereby causing the four sets of limiting clamps to move relative to each other. The four sets of second compression springs ensure that the four sets of limiting clamps are tightly fitted to the plate-shaped aircraft interior component. When the plate-shaped aircraft interior decoration component is large, based on the above steps, the four sets of first sliding blocks are movably connected to the first limiting sliding rod, so that the four sets of first sliding blocks are respectively moved relative to each other along the four sets of outer grooves, thereby driving the four sets of movable grooves to move relative to each other. The four sets of first compression springs are used to ensure that the four sets of limiting clamps are tightly fitted with the plate-shaped aircraft interior decoration component, thereby quickly clamping a variety of plate-shaped aircraft interior decoration components of different specifications and sizes. Secondly, when installing the aircraft interior component, the rotating motor on the supporting base is started to drive the first rotating shaft to rotate, thereby driving the vertical trough body to rotate on the upper side of the supporting base through the cooperation of the rotating connecting plate and the sliding plate with the annular groove, and then the tilting motor on the outer side of the lifting seat is started to drive the second rotating shaft to rotate, thereby driving the rotating block to rotate, and then driving the aircraft interior component to tilt and rotate until the aircraft interior component is in the target position, and then the lifting motor inside the slot is started to drive the vertical screw shaft to rotate, thereby driving the lifting column to move upward along the vertical trough body through the threaded connection between the vertical screw shaft and the lifting column, thereby driving the aircraft interior component to move vertically upward, and then the hydraulic cylinder inside the connecting frame is started to drive the telescopic rod to extend, thereby driving the installation plate to move until the aircraft interior component is pushed to the installation position, and the movable block is driven to rotate through the cooperation of the fixed shaft and the rotating shaft hole, thereby driving the installation fixture to rotate, so as to ensure the corresponding installation of the aircraft interior component, and the position of the installation fixture is adjusted according to the installation position of the aircraft interior component; Finally, the four sets of rotating long plates are rotated to a horizontal state together through the connecting hinges on the annular block, and then the four sets of fastening bolts are respectively passed through the four sets of rotating long plates and threadedly connected to the annular block with the threaded slots. At this time, the elastic net is extended with the cooperation of the elastic rope and the four sets of blocks. When the aircraft interior parts and their installed parts fall, they are received by the elastic net, and the four sets of support plates are used to ensure the stable placement of the vertical trough body.

Images