Assembly tool and assembly method for aircraft fuselage

Abstract

The invention discloses an aircraft fuselage assembly tool and method, the aircraft fuselage assembly tool comprises a tool base, a front spar positioning frame and a plurality of frameworks, the front spar positioning frame is fixedly mounted on the tool base, and the plurality of frameworks are vertically arranged on the front side of the tool base. A first motor is started to drive a worm to rotate, a worm gear is driven to rotate, then a rotating rod is driven to rotate, then a plurality of connecting blocks are driven to rotate, and then a plurality of rotating plates are driven to rotate, so that when the rotating plates are horizontally placed, a framework is conveniently installed, and after the rotating plates are rotated by 90 degrees, the framework is fixed. At the moment, the fixing block is inserted into the fixing base, the front rotating base and the rear rotating base, then the limiting mechanism is used for limiting the fixing block, and after the rotating plate is laid flat, the stability is better, the operation space is larger, workers can conveniently conduct accurate screw fixing operation, the workers can more easily adjust the position and the angle of the screw, and firm fixing is ensured.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft manufacturing, and particularly relates to an assembly tooling and an assembly method for an aircraft fuselage. Background Art

[0002] During the assembly process of a small aircraft fuselage, assembly tooling is widely used in the following steps: using the tooling to accurately position and clamp the various parts of the fuselage skeleton together to form a stable fuselage structure; tightly fitting the skin onto the fuselage skeleton through the tooling and using a clamping mechanism to fix it to ensure the flatness and tightness of the skin; using the tooling to accurately install various components at the designated positions on the fuselage and conduct necessary debugging and testing.

[0003] Some aircraft fuselage assembly toolings in the prior art are usually designed to fit the aircraft fuselage. After the main frame of the aircraft fuselage is installed, the skin is installed. After part of the fuselage skin is installed, the entire aircraft fuselage needs to be vertically lifted, and multiple skeletons for supporting the fuselage are disassembled. Then, the two ends of the fuselage are continuously fixed on the front and rear positioning beams, and the fuselage skin is continued to be installed. The fuselage is relatively heavy, and it takes a relatively long time to lift the fuselage. Moreover, multiple debuggings are required to prevent errors. Also, when assembling the next aircraft fuselage, multiple skeletons need to be reinstalled. The skeletons are installed vertically, and when using bolts or riveting, the staff needs to overcome the influence of gravity, and the operating space is limited, which may lead to insecure fixation or position deviation. Therefore, an assembly tooling and an assembly method for an aircraft fuselage are proposed to solve the above problems. Summary of the Invention

[0004] To solve the technical problems in the background art, the present invention proposes an assembly tooling and an assembly method for an aircraft fuselage. By setting a rotating assembly and a limiting mechanism, the rotating plate can be laid flat, which is convenient for installing the skeleton and improves the stability during installation.

[0005] The present invention provides an assembly tooling and an assembly method for an aircraft fuselage, including a tooling base, a front spar positioning frame and a plurality of skeletons. The front spar positioning frame is fixedly installed on the tooling base, and the plurality of skeletons are vertically arranged on the front side of the tooling base. The assembly tooling further includes a plurality of rotating plates, and the plurality of skeletons are respectively arranged on the plurality of rotating plates. Fixed blocks are connected to the rear sides of the plurality of rotating plates. The tooling base includes a fixed seat, a front rotating seat and a rear rotating seat. The front rotating seat and the rear rotating seat are respectively hinged to the front and rear ends of the fixed seat. Fixed components are arranged between the front rotating seat and the rear rotating seat and the fixed seat. After the tooling base is unfolded, it is fixed. Rotating components for driving the plurality of rotating plates to rotate are arranged in the fixed seat, the front rotating seat and the rear rotating seat. Limiting mechanisms for fixing the plurality of fixed blocks are arranged in the fixed seat, the front rotating seat and the rear rotating seat.

[0006] Preferably, the fixed component includes a fixed piece, a first threaded rod and a knob. The fixed piece is fixedly connected to the rear side of the front rotating seat. The first threaded rod is connected to the rear side of the fixed seat. The knob is threadedly connected to the first threaded rod. A U-shaped groove is formed in the fixed piece, and the size of the U-shaped groove is adapted to the size of the first threaded rod.

[0007] Preferably, casters are arranged at the bottom ends of the fixed seat, the front rotating seat and the rear rotating seat.

[0008] Preferably, the rotating component includes a first motor, a worm, a rotating rod, a worm gear and a plurality of connecting blocks. The first motor is arranged on the rear side wall of the fixed seat. One end of the worm is coaxially connected to the output shaft of the first motor, and the other end is rotatably connected to the rear side wall of the fixed seat. The rotating rod is rotatably connected between the left and right side walls of the fixed seat. The worm gear is coaxially fixedly sleeved on the rotating rod and meshes with the worm. The plurality of connecting blocks are coaxially fixedly sleeved on the rotating rod and are respectively connected to the plurality of rotating plates.

[0009] Preferably, a plurality of sliding windows are formed in the fixed seat, the front rotating seat and the rear rotating seat, and the sizes of the sliding windows are respectively adapted to the sizes of the plurality of connecting blocks.

[0010] Preferably, the limiting mechanism includes a second motor, a fixing plate, a limiting plate, a second threaded rod, a moving plate and a plurality of fixing members. The fixing plate is connected inside the fixing seat. The fixing plate is arranged on the left side of the second motor. One end of the second threaded rod is coaxially connected to the output shaft of the second motor, and the other end is rotatably connected to the right side wall of the fixing seat. The limiting plate is fixedly connected to the rear side wall of the fixing seat. The moving plate is threadedly connected to the second threaded rod and slidably connected to the limiting plate. The plurality of fixing members are connected to the front side of the moving plate.

[0011] Preferably, S1, after pushing the tooling base into the site, spread the front rotating seat and the rear rotating seat towards the opposite side, so that they form a straight line with the fixing seat, and fix them to the fixing seat by using the fixing components. S2, when the rotating plate is in contact with the top of the tooling base, use bolts to install the plurality of skeletons on the plurality of rotating plates respectively. Start the first motor to drive the worm to rotate, drive the worm wheel to rotate, drive the rotating rod to rotate, so that the plurality of connecting blocks drive the plurality of rotating plates to rotate, and make the rotating plate fit with the front side of the tooling base. At this time, use the limiting mechanism to fix the plurality of fixing blocks, support and fix the plurality of skeletons, make the plurality of skeletons perpendicular to the top of the tooling base, and facilitate subsequent assembly of the fuselage.

[0012] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. By bending the fixing seat, the front rotating seat and the rear rotating seat in a hinged manner, the overall length is shortened, making it easier to move and facilitating entry and exit from the site.

[0013] 2. By starting the first motor to drive the worm to rotate, driving the worm wheel to rotate, then driving the rotating rod to rotate, and then driving the plurality of connecting blocks to rotate, and then driving the plurality of rotating plates to rotate. In this way, when the rotating plate is laid flat, it is convenient to install the skeleton. After rotating 90 degrees, at this time, the fixing block is inserted into the fixing seat, the front rotating seat and the rear rotating seat, and then the limiting mechanism is used to limit it. After the rotating plate is laid flat, its stability is better, the operating space is larger, which is convenient for workers to perform precise screw fixing operations. Workers can more easily adjust the position and angle of the screws to ensure firm fixation. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The drawings are used to provide a further understanding of the present invention, and constitute a part of the specification. They are used together with the embodiments of the present invention to explain the present invention, and do not constitute a limitation to the present invention.

[0015] In the drawings: Figure 1 is a schematic diagram of an assembly tool for an aircraft fuselage proposed by the present invention; Figure 2Schematic diagram of the rear side of an assembly tooling for an aircraft fuselage proposed by the present invention; Figure 3 Partial cross-sectional view of an assembly tooling for an aircraft fuselage proposed by the present invention; Figure 4 Schematic diagram of a rotating plate in an assembly tooling for an aircraft fuselage proposed by the present invention; Figure 5 Cross-sectional view of an assembly tooling for an aircraft fuselage proposed by the present invention; 1. Tooling base; 11. Fixed seat; 12. Front rotating seat; 121. Caster; 13. Rear rotating seat; 2. Front wing beam positioning frame; 3. Skeleton; 4. Rotating plate; 41. Fixed block; 51. First motor; 52. Worm; 53. Rotating rod; 54. Worm gear; 55. Connecting block; 61. Second motor; 62. Fixed plate; 63. Limiting plate; 64. Second threaded rod; 65. Moving plate; 66. Fixing part; 71. Fixed piece; 72. First threaded rod; 73. Knob. Detailed implementation manners

[0016] The following describes the preferred embodiments of the present invention with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are only for the purpose of illustration and explanation of the present invention, and are not used to limit the present invention.

[0017] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention; the terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance; in addition, unless otherwise clearly defined and limited, the terms "installed", "connected", "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0018] As Figures 1-5As shown in the figure, an assembly tooling for an aircraft fuselage proposed by the present invention includes a tooling base 1, a front spar positioning frame 2 and a plurality of skeletons 3. The front spar positioning frame 2 is fixedly installed on the tooling base 1, and the plurality of skeletons 3 are vertically arranged on the front side of the tooling base 1. It is characterized in that it further includes a plurality of rotating plates 4. The plurality of skeletons 3 are respectively arranged on the plurality of rotating plates 4. Fixed blocks 41 are connected to the rear sides of the plurality of rotating plates 4. The tooling base 1 includes a fixed seat 11, a front rotating seat 12 and a rear rotating seat 13. The front rotating seat 12 and the rear rotating seat 13 are respectively hinged to the front and rear ends of the fixed seat 11. Fixed components are arranged between the front rotating seat 12 and the rear rotating seat 13 and the fixed seat 11. After the tooling base 1 is unfolded, it is fixed. Rotating components for driving the plurality of rotating plates 4 to rotate are arranged in the fixed seat 11, the front rotating seat 12 and the rear rotating seat 13. Limiting mechanisms for fixing the plurality of fixed blocks 41 are arranged in the fixed seat 11, the front rotating seat 12 and the rear rotating seat 13.

[0019] In the present invention, a nose cone positioning shaft of the aircraft head is connected to the front rotating seat 12, and a rear spar positioning frame is installed on the rear rotating seat 13. The shape of the tooling base 1 is a regular prism, and the four corners are arc-shaped. The tooling base 1 is divided into: a fixed seat 11, a front rotating seat 12 and a rear rotating seat 13. The three are bent by means of hinge, so that its overall length becomes shorter, making it easier to move and convenient to enter and exit the site. Then, it is fixed by using the fixed component for the subsequent assembly of the aircraft fuselage. First, the plurality of rotating plates 4 are installed with the plurality of skeletons 3, and then the rotating component is used to rotate the rotating plates 4 by 90 degrees. When the rotating plates 4 and the skeletons 3 are laid flat, it is more convenient for workers to fix the two by riveting or bolts. Then, the limiting mechanism is used to limit the plurality of fixed blocks 41. A plurality of insertion holes adapted to the size of the fixed blocks 41 are opened on the front side of the tooling base 1. At this time, the fixed blocks 41 enter the tooling base 1 through the insertion holes. Cushion blocks matching the respective positions of the fuselage are arranged on the skeletons 3 for fixing the aircraft fuselage. After the front half of the aircraft fuselage skin is covered, the skeletons 3 need to be disassembled, and then the right half of the aircraft fuselage is skinned. When disassembling and installing the vertically arranged skeletons 3, workers need to bear the weight of the skeletons 3 themselves for disassembly. Laying the skeletons 3 flat for disassembly and installation will improve efficiency and does not require lifting the aircraft fuselage.

[0020] In an optional embodiment, the fixed component includes a fixed piece 71, a first threaded rod 72 and a knob 73. The fixed piece 71 is fixedly connected to the rear side of the front rotating seat 12. The first threaded rod 72 is connected to the rear side of the fixed seat 11. The knob 73 is threadedly connected to the first threaded rod 72. A U-shaped groove is opened on the fixed piece 71, and the size of the U-shaped groove is adapted to the size of the first threaded rod 72.

[0021] It should be noted that before fixation, first turn the knob 73 to the end of the first threaded rod 72, and then rotate the front rotating seat 12 and the rear rotating seat 13. At this time, the first threaded rod 72 is inserted into the U-shaped groove. When the fixing piece 71 is attached to the rear side of the fixing seat 11, turn the knob 73 to fix the fixing piece 71, and then complete the fixation of the fixing seat 11, the front rotating seat 12 and the rear rotating seat 13.

[0022] In an alternative embodiment, casters 121 are provided at the bottom ends of the fixing seat 11, the front rotating seat 12 and the rear rotating seat 13.

[0023] It should be noted that adjustable-height support legs are provided at the bottom ends of the fixing seat 11 and the front wing beam positioning bracket 2, which facilitates fixing the tooling base 1 in the site after fixation. By providing the casters 121, it is convenient for the fixing seat 11, the front rotating seat 12 and the rear rotating seat 13 to rotate.

[0024] In an alternative embodiment, the rotating assembly includes a first motor 51, a worm 52, a rotating rod 53, a worm gear 54 and a plurality of connecting blocks 55. The first motor 51 is arranged on the rear side wall of the fixing seat 11. One end of the worm 52 is coaxially connected to the output shaft of the first motor 51, and the other end is rotatably connected to the rear side wall of the fixing seat 11. The rotating rod 53 is rotatably connected between the left and right side walls of the fixing seat 11. The worm gear 54 is coaxially and fixedly sleeved on the rotating rod 53 and meshes with the worm 52. A plurality of connecting blocks 55 are coaxially and fixedly sleeved on the rotating rod 53 and are respectively connected to a plurality of rotating plates 4.

[0025] In an alternative embodiment, a plurality of sliding windows are provided on the fixing seat 11, the front rotating seat 12 and the rear rotating seat 13, and are respectively adapted to the sizes of the plurality of connecting blocks 55.

[0026] In an alternative embodiment, the limiting mechanism includes a second motor 61, a fixing plate 62, a limiting plate 63, a second threaded rod 64, a moving plate 65 and a plurality of fixing members 66. The fixing plate 62 is connected inside the fixing seat 11. The fixing plate 62 is arranged on the left side of the second motor 61. One end of the second threaded rod 64 is coaxially connected to the output shaft of the second motor 61, and the other end is rotatably connected to the right side wall of the fixing seat 11. The limiting plate 63 is fixedly connected to the rear side wall of the fixing seat 11. The moving plate 65 is threadedly connected to the second threaded rod 64 and is slidably connected to the limiting plate 63. A plurality of fixing members 66 are connected to the front side of the moving plate 65.

[0027] In an alternative embodiment, fixing holes are provided on a plurality of fixing blocks 41, and the sizes of the plurality of fixing members 66 are respectively adapted to the sizes of the plurality of fixing holes.

[0028] It should be noted that by starting the first motor 51 to drive the worm 52 to rotate, the worm wheel 54 is driven to rotate, and then the rotating rod 53 is driven to rotate, and then a plurality of connecting blocks 55 are driven to rotate, and then a plurality of rotating plates 4 are driven to rotate. In this way, when the rotating plate 4 is placed flat, it is convenient to install the skeleton 3. After rotating 90 degrees, at this time, the fixing block 41 is inserted into the fixing seat 11, the front rotating seat 12 and the rear rotating seat 13, and then the second motor 61 is started to drive the second threaded rod 64 to rotate, driving the moving plate 65 to move along the limiting plate 63, so that a plurality of fixing members 66 are inserted into the fixing holes to complete the fixing of the plurality of rotating plates 4. The connecting block 55 is limited by opening a plurality of sliding windows on the right.

[0029] In an optional embodiment, S1, after pushing the tooling base 1 into the site, the front rotating seat 12 and the rear rotating seat 13 are spread apart towards the opposite side, so that they form a straight line with the fixing seat 11, and they are fixed to the fixing seat 11 by using a fixing component; S2, when the rotating plate 4 is in contact with the top end of the tooling base 1, a plurality of skeletons 3 are respectively installed on the plurality of rotating plates 4 by using bolts. The first motor 51 is started to drive the worm 52 to rotate, driving the worm wheel 54 to rotate, which will drive the rotating rod 53 to rotate, so that a plurality of connecting blocks 55 drive a plurality of rotating plates 4 to rotate, and the rotating plate 4 is in contact with the front side of the tooling base 1. At this time, the plurality of fixing blocks 41 are fixed by using a limiting mechanism to support and fix the plurality of skeletons 3, so that the plurality of skeletons 3 are perpendicular to the top end of the tooling base 1, which is convenient for subsequent assembly of the fuselage.

[0030] Finally, it should be noted that the above are only the preferred embodiments of the present invention and are not used to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, for those skilled in the art, they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An assembly tooling for an aircraft fuselage, comprising a tooling base (1), a front spar positioning frame (2) and a plurality of skeletons (3). The front spar positioning frame (2) is fixedly installed on the tooling base (1), and the plurality of skeletons (3) are vertically arranged on the front side of the tooling base (1), characterized in that, It further includes a plurality of rotating plates (4), a plurality of the skeletons (3) are respectively arranged on the plurality of rotating plates (4), fixing blocks (41) are connected to the rear sides of the plurality of rotating plates (4), the tooling base (1) includes a fixed seat (11), a front rotating seat (12) and a rear rotating seat (13), the front rotating seat (12) and the rear rotating seat (13) are respectively hinged to the front and rear ends of the fixed seat (11), fixing components are arranged between the front rotating seat (12) and the rear rotating seat (13) and the fixed seat (11), the tooling base (1) is fixed after being unfolded, rotating components for driving the plurality of rotating plates (4) to rotate are arranged in the fixed seat (11), the front rotating seat (12) and the rear rotating seat (13), and limiting mechanisms for fixing the plurality of fixing blocks (41) are arranged in the fixed seat (11), the front rotating seat (12) and the rear rotating seat (13).

2. The assembly tooling for an aircraft fuselage according to claim 1, characterized in that, The fixing component includes a fixing piece (71), a first threaded rod (72) and a knob (73), the fixing piece (71) is fixedly connected to the rear side of the front rotating seat (12), the first threaded rod (72) is connected to the rear side of the fixed seat (11), the knob (73) is in threaded connection with the first threaded rod (72), a U-shaped groove is formed in the fixing piece (71), and the size of the U-shaped groove is adapted to the size of the first threaded rod (72).

3. The assembly tooling for an aircraft fuselage according to claim 1, characterized in that Casters (121) are arranged at the bottom ends of the fixed seat (11), the front rotating seat (12) and the rear rotating seat (13).

4. The assembly tooling for an aircraft fuselage according to claim 1, characterized in that, The rotating component includes a first motor (51), a worm (52), a rotating rod (53), a worm gear (54) and a plurality of connecting blocks (55), the first motor (51) is arranged on the rear side wall of the fixed seat (11), one end of the worm (52) is coaxially connected to the output shaft of the first motor (51), and the other end is rotatably connected to the rear side wall of the fixed seat (11), the rotating rod (53) is rotatably connected between the left and right side walls of the fixed seat (11), the worm gear (54) is coaxially and fixedly sleeved on the rotating rod (53) and meshes with the worm (52), the plurality of connecting blocks (55) are coaxially and fixedly sleeved on the rotating rod (53) and are respectively connected to the plurality of rotating plates (4).

5. The assembly tooling for an aircraft fuselage according to claim 4, wherein, A plurality of sliding windows are formed in the fixed seat (11), the front rotating seat (12) and the rear rotating seat (13), and the sizes of the sliding windows are respectively adapted to the sizes of the plurality of connecting blocks (55).

6. The assembly tooling for an aircraft fuselage according to claim 1, wherein, The limiting mechanism includes a second motor (61), a fixing plate (62), a limiting plate (63), a second threaded rod (64), a moving plate (65) and a plurality of fixing members (66). The fixing plate (62) is connected inside the fixing seat (11). The fixing plate (62) is arranged on the left side of the second motor (61). One end of the second threaded rod (64) is coaxially connected to the output shaft of the second motor (61), and the other end is rotatably connected to the right side wall of the fixing seat (11). The limiting plate (63) is fixedly connected to the rear side wall of the fixing seat (11). The moving plate (65) is threadedly connected to the second threaded rod (64) and is slidably connected to the limiting plate (63). A plurality of the fixing members (66) are connected to the front side of the moving plate (65).

7. An assembly tooling for an aircraft fuselage according to claim 6, characterized in that, A fixing hole is formed in each of the plurality of fixing blocks (41), and the sizes of the plurality of fixing members (66) respectively match the sizes of the plurality of fixing holes.

8. A method for assembling an aircraft fuselage according to claim 1, characterized in that It includes the following steps: S1. After pushing the tooling base (1) into the site, spread the front rotating seat (12) and the rear rotating seat (13) towards the opposite sides, so that they form a straight line with the fixing seat (11), and fix them to the fixing seat (11) by using the fixing components. S2. When the rotating plate (4) is in contact with the top end of the tooling base (1), use bolts to respectively install a plurality of skeletons (3) on the plurality of rotating plates (4). Start the first motor (51) to drive the worm (52) to rotate, drive the worm wheel (54) to rotate, drive the rotating rod (53) to rotate, so that a plurality of connecting blocks (55) drive a plurality of rotating plates (4) to rotate, and make the rotating plate (4) fit with the front side of the tooling base (1). At this time, use the limiting mechanism to fix a plurality of fixing blocks (41), support and fix a plurality of skeletons (3), make the plurality of skeletons (3) perpendicular to the top end of the tooling base (1), which is convenient for subsequent assembly of the fuselage.

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