Turning tool and turning method for lower structure of large aircraft

Abstract

The present invention discloses a turning tool and turning method for the lower structure of a large aircraft in the field of aircraft manufacturing technology. The turning tool comprises a turning support frame and a turning frame. The top of the turning support frame is provided with a support seat with a V-shaped groove. The left and right sides of the turning frame are provided with a connecting seat inside and a turning support outside. The turning support is provided with a rotating shaft and a lifting joint. When in use, two turning support frames are used to support the two sides of the turning frame respectively. The rotating shaft of the turning support is placed in the V-shaped groove of the corresponding support seat. The turning process is to use the lifting equipment to drive one side of the turning frame to move up, so that it turns 90° with the turning support frame on the other side as the fulcrum, and then the turning frame is lifted to another turning support frame to continue to turn 90°, so as to realize the 180° turning of the product assembly. The whole tooling structure is simple, low cost, small footprint, and the turning of the product assembly is completed using a traditional mechanical structure, and the safety is controllable.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft manufacturing, and in particular to a turning tool and a turning method for a lower structure of a large aircraft. Background Art

[0002] In the manufacturing process of large aircraft structures, the assembly of aircraft parts is often completed by matching the upper and lower aircraft structures. Before the aircraft parts are matched, the posture of the lower part of the aircraft needs to be consistent with the posture in the aircraft coordinate system. However, during the assembly process of the lower part of the aircraft, depending on the form of the aircraft structure, the difficulty of construction, the openness of operation, etc., the lower part of the aircraft may be in the upright position or turned over 180° in the aircraft coordinate system. If the aircraft production is low and the assembly efficiency is not high, the upright assembly form can be adopted. This method can save at least one set of turning tooling and reduce costs; but if the aircraft production is high, it is necessary to avoid a large number of closed structures in the lower part of the aircraft structure, improve the openness and assembly efficiency of the lower structure assembly, and usually use the 180° turning posture for structural assembly, and then the lower structure needs to be turned over 180° when the aircraft is assembled as a whole.

[0003] The lower part of the existing aircraft structure is turned over mainly using special large-scale automated turning equipment, such as the large component turning tool with publication number CN105382778A. This type of special large-scale automated equipment mainly hoists the upper or lower large components assembled on other tools directly into the equipment in the turned-over posture after assembly, and completely wraps the upper or lower part of the aircraft, so that the equipment forms a rigid connection with the product structure of the upper or lower part of the aircraft, and then starts the automated equipment program to slowly turn over. The main disadvantages of this type of equipment are that the special large-scale automated turning equipment itself is expensive, the equipment occupies a large area, it cannot be moved at will after being placed, and there is a risk of programming failure in the program. If the aircraft structure fails before completing the complete turning over, it will seriously affect product safety. In addition, during the process of hoisting the aircraft structure to the large-scale automated turning equipment, the upper and lower parts of the aircraft must be completely wrapped, which makes hoisting difficult and the installation risk high. Summary of the invention

[0004] In order to overcome the above-mentioned deficiencies of the existing large component turning equipment, the technical problem to be solved by the present invention is to provide a turning tool and turning method for the lower structure of a large aircraft which is simple in structure, safe and reliable.

[0005] The technical solution adopted by the present invention to solve its technical problem is:

[0006] The turning tooling of the lower structure of a large aircraft includes a turning support frame and a turning frame, wherein at least two support seats are provided on the top of the turning support frame along its length direction, and a V-shaped groove whose axis is parallel to the length direction of the turning support frame is provided on the top of the support seat, and connecting seats for installing product components are provided inside the left and right sides of the turning frame, and turning supports that can be connected with the support seats are provided outside the left and right sides of the turning frame, and a rotating shaft and a lifting joint are provided on the turning support, and the turning support includes two, and the turning supports on the left and right sides of the turning frame are respectively placed in the V-shaped grooves of the support seats on the tops of the two turning support frames through rotating shafts, and the turning frame can rotate around the rotating shaft on any side.

[0007] Furthermore, the turning support frame includes two tripods and a connecting frame connected between the two tripods, and the supporting base includes two, which are respectively arranged on the top of the two tripods.

[0008] Furthermore, a foot plate is provided at the bottom of the tripod, and an anchor bolt which can be connected and fixed to a ground foundation is provided on the foot plate.

[0009] Furthermore, the turning frame includes two front and rear C-shaped beams and a plurality of cross beams connected between the two C-shaped beams, and the turning supports and connecting seats each include four, which are correspondingly arranged at the ends of the two C-shaped beams.

[0010] Furthermore, the turning support also includes a connecting plate fixedly connected to the turning frame, the rotating shaft is arranged at the outer end of the connecting plate, and the lifting joint is rotatably arranged on the rotating shaft.

[0011] Furthermore, one end of the connection seat is rotatably arranged on the inner end of the connection plate, and a product connection joint is provided on a side of the connection seat away from the turning frame.

[0012] Furthermore, the support seat includes a base plate, one end of which is provided with an opening for the lifting joint to pass through, L-shaped pads are provided on the base plate on both sides of the opening, a clamping plate is vertically provided on the horizontal section of the L-shaped pad, a V-shaped groove is provided on the clamping plate, and a rib is provided between the vertical section of the L-shaped pad and the base plate, and the support seat is fixed to the turning support frame by welding the base plate.

[0013] The method for turning over the lower structure of a large aircraft adopts the above-mentioned turning over tool for the lower structure of a large aircraft, and further comprises the following steps:

[0014] Step 1: Use the connecting seat to install the product components in the turning frame;

[0015] Step 2: Connect the lifting equipment to all lifting joints, lift the turning frame onto the turning support frame, and place the rotating shafts of the turning supports on both sides of the turning frame into the V-shaped grooves of the support seats of the turning support frame;

[0016] Step 3: When turning over is required, connect the lifting device to the lifting joint on the left side of the turning frame, lift the left side of the turning frame to the upper right, and rotate it 90° around the right axis;

[0017] Step 4: Lift the turning frame as a whole from the turning support frame on the right side and onto the turning support frame on the left side, so that the rotating shaft of the turning support seat under the turning frame slides into the V-shaped groove of the support seat of the turning support frame on the left side;

[0018] Step 5. The lifting equipment drives the top of the turning frame to move to the right and lowers the turning frame, so that it rotates 90° to the right around the rotating shaft below, so that the rotating shaft of the turning support above the turning frame slides into the V-shaped groove of the support seat of the turning support frame on the right, completing the turning of the product assembly.

[0019] The beneficial effects of the present invention are as follows: a turning tool is composed of two turning support frames and a turning frame and cooperates with a lifting device to turn over the product components. The entire tool has a simple structure, and compared with expensive automated equipment, it has a lower cost and occupies a small area. When not in use, it can be moved and stored close together, which greatly reduces the layout pressure of the factory. In addition, the installation form of the product components and the turning tool and the lifting process are simple and easy to operate. The traditional mechanical structure is used to complete the turning of the lower structure of the aircraft. There is no risk of programming failure, and the safety of the turning process is controllable. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0021] Figure 2 It is a structural schematic diagram of the turning over support frame of the present invention;

[0022] Figure 3 It is a structural schematic diagram of the turning frame of the present invention;

[0023] Figure 4 It is a structural schematic diagram of the turning step three of the present invention;

[0024] Figure 5 It is a structural schematic diagram of the turning-over step 4 of the present invention;

[0025] Figure 6 It is a structural schematic diagram of the fifth step of turning over of the present invention;

[0026] Figure 7 yes Figure 1 A magnified view of part A;

[0027] Figure 8 yes Figure 2 A magnified view of part B;

[0028] Fig. 9 yes Figure 2Enlarged view of part C;

[0029] Fig.10 yes Figure 3 A magnified view of part D in the middle;

[0030] Fig.11 yes Figure 4 Enlarged view of part E in the middle;

[0031] Fig.12 yes Figure 5 Enlarged view of part F;

[0032] Fig.13 yes Figure 6 Enlarged view of section G.

[0033] Marked in the figure, 1- turning support frame, 2- turning frame, 3- product component, 4- supporting seat, 5- connecting seat, 6- turning support, 11- tripod, 12- connecting frame, 13- foot plate, 14- anchor bolt, 21- C-shaped beam, 22- cross beam, 41- V-shaped groove, 42- bottom plate, 43- opening, 44- L-shaped pad, 45- clamping plate, 46- rib plate, 51- product connection joint, 61- rotating shaft, 62- lifting joint, 63- connecting plate. DETAILED DESCRIPTION

[0034] The present invention is further described below in conjunction with the accompanying drawings.

[0035] It should be noted that if there are directional indication terms in the present invention, such as the directions and orientations of up, down, left, right, front and back, they are for the purpose of facilitating the description of the relative position relationship between components, and are not specific to the absolute position of the related components or the position relationship between components. They are only used to explain the relative position relationship and movement of the components in a certain posture. If the specific posture changes, the directional indication will also change accordingly. If there are terms related to quantity in the present invention, such as "multiple", "multiple", "several", etc., they specifically refer to two or more.

[0036] like Figure 1-3 and Figure 7As shown, a large aircraft lower structure turning tool provided by the present invention includes a turning support frame 1 and a turning frame 2. The top of the turning support frame 1 is provided with at least two support seats 4 along its length direction. The top of the support seat 4 is provided with a V-shaped groove 41 whose axis is parallel to the length direction of the turning support frame 1. The inside of the left and right sides of the turning frame 2 is provided with a connecting seat 5 for installing the product component 3. The outside of the left and right sides of the turning frame 2 is provided with a turning support 6 that can be connected with the support seat 4. The turning support 6 is provided with a rotating shaft 61 and a lifting joint 62. The turning support frame 1 includes two, and the turning supports 6 on the left and right sides of the turning frame 2 are respectively placed in the V-shaped groove 41 of the support seat 4 on the top of the two turning support frames 1 through the rotating shaft 61, and the turning frame 2 can rotate around the rotating shaft 61 on any side. Among them, the turning support frame 1 and the turning frame 2 are both made of welded steel structures to ensure that they have sufficient rigidity and can stably support the product component 3. The multiple support seats 4 on the top of the turning support frame 1 need to ensure that the axes of the V-shaped grooves 41 are located on the same straight line. The turning frame 2 is preferably a bilaterally symmetrical structure, and the turning supports 6 on the left and right sides are also preferably symmetrically arranged, so as to avoid moving or adjusting the turning support frame 1 during the turning process, and also ensure that the positioning reference of the product component 3 is unified when it is upright and turned 180 degrees, which is convenient for assembly.

[0037] The turning over process of the present invention comprises the following steps:

[0038] Step 1: Figure 3 As shown, the product assembly is installed in the turning frame 2 using the connecting seat 5;

[0039] Step 2: Connect the lifting equipment to all the lifting joints 62, and lift the turning frame 2 onto the turning support frame 1, so that the rotating shafts 61 of the turning supports 6 on both sides of the turning frame 2 are placed in the V-shaped grooves 41 of the supporting seats 4 of the turning support frame 1. Figure 1 The structure shown;

[0040] Step 3: When turning over is required, connect the lifting device to the lifting joint 62 on the left side of the turning frame 2, lift the left side of the turning frame 2 to the upper right, and rotate it 90° around the right side shaft 61 with the turning support frame 1 on the right side as the fulcrum, as shown in FIG. Figure 4 , Fig.11 As shown;

[0041] Step 4: Lift the turning frame 2 as a whole from the turning support frame 1 on the right side and onto the turning support frame 1 on the left side, so that the rotating shaft 61 of the turning support 6 below the turning frame 2 slides into the V-shaped groove 41 of the supporting seat 4 of the turning support frame 1 on the left side, as shown in FIG. Figure 5 , Fig.12 As shown;

[0042] Step 5: The lifting device drives the top of the turning frame 2 to move rightward and lowers the turning frame 2, so that it rotates 90° to the right around the rotating shaft 61 below, so that the rotating shaft 61 of the turning support 6 above the turning frame 2 slides into the V-shaped groove 41 of the supporting seat 4 of the turning support frame 1 on the right side, and the turning of the product component 3 is completed. Figure 6 , Fig.13 shown.

[0043] Compared with the existing large-scale automated turning equipment, the solution provided by the present invention has a simple structure, low cost, and small footprint. When not in use, the turning support frame 1 and the turning frame 2 can be transferred and stored close together, which greatly reduces the layout pressure of the factory. In addition, the installation form of the product component 3 and the turning tooling and the hoisting process are simple and easy to operate. The lifting equipment and the turning frame 2 only need to be clamped once to achieve a 180° turning of the turning frame 2, and the traditional mechanical structure is used throughout the process to complete the turning of the lower structure of the aircraft. There is no risk of programming failure, and the safety of the turning process is controllable.

[0044] For turning work clothes, the present application also provides the following preferred solutions:

[0045] like Figure 2 As shown, the turning support frame 1 includes two tripods 11 and a connecting frame 12 connected between the two tripods 11, and the supporting base 4 includes two, which are respectively arranged on the top of the two tripods 11. The tripod 11 can ensure the stability of the turning support frame 1 to avoid tipping over during the turning process. The connecting frame 12 connects the two tripods 11 into a whole to ensure the positioning accuracy of the two supporting bases 4 and the V-shaped groove 41.

[0046] like Fig. 9 As shown, in order to ensure the stability of the installation of the turning support frame 1 and to enable it to be moved and stored, a foot plate 13 is provided at the bottom of the tripod 11, and an anchor bolt 14 that can be connected and fixed to the ground foundation is provided on the foot plate 13. The ground foundation can be a fixing ring fixed in a groove on the ground, and a hook is provided at the lower end of the anchor bolt 14. When installing, the foot plate 13 contacts the ground, and the anchor bolt 14 is first connected to the fixing ring through the hook, and then the upper end passes through the foot plate 13 and is locked by a nut.

[0047] For the turning frame 2, in order to improve the convenience of turning over, the weight should be reduced as much as possible under the premise of ensuring its rigidity, so the preferred solution of the present application is as follows: Figure 3As shown, the turning frame 2 includes two front and rear C-shaped beams 21 and multiple cross beams 22 connected between the two C-shaped beams 21, and the turning support 6 and the connecting seat 5 each include four, which are correspondingly arranged at the ends of the two C-shaped beams 21, that is, one turning support 6 and one connecting seat 5 are a group of structures, and four groups of structures are arranged on the four ends of the two C-shaped beams 21, and ensure that the connecting seat 5 is located on the inner side of the end and the turning support 6 is located on the outer side of the end, so as to avoid the turning frame 2 from interfering with the support seat 4 during the turning process.

[0048] Regarding the connection form between the turning support 6 and the connecting seat 5 and the turning frame 2, the preferred solution provided by the present application is as follows: Fig.10 As shown, the turning support 6 also includes a connecting plate 63 fixedly connected to the turning frame 2, the rotating shaft 61 is arranged at the outer end of the connecting plate 63, and the lifting joint 62 is rotatably arranged on the rotating shaft 61; one end of the connecting seat 5 is rotatably arranged at the inner end of the connecting plate 63, and the side of the connecting seat 5 away from the turning frame 2 is provided with a product connecting joint 51. The connecting plate 63 can be fixed to the end of the C-shaped beam 21 by welding. In order to improve the stability of the support, the rotating shaft 61 is preferably passed through the connecting plate 63 so that both ends thereof can be placed in the V-shaped groove 41. Similarly, in order to improve the connection strength of the lifting joint 62, the lifting joint 62 can be clamped on both sides of the connecting plate 63 by setting a U-shaped opening, and is rotatably connected to the rotating shafts 61 on both sides. The connecting seat 5 is hinged to the connecting plate 63, which can make it more convenient to install and dock with the product component 3, and at the same time, the product component 3 can form a rigid connection whole with the connecting seat 5 and the turning support 6, thereby ensuring the stability of lifting and turning. The purpose of providing the product connection joint 51 on the connection seat 5 is that after turning over 180°, the lifting joint 62 may rotate to the bottom of the support seat 4, and at this time the lifting equipment can use the product connection joint 51 to drive the turning frame 2 to turn over.

[0049] Finally, when the lifting joint 62 is used as Fig.10 When the U-shaped opening is connected to the rotating shaft 61, during the turning process of the turning frame 2, the lifting joint 62 may abut against the support seat 4 due to the rotation limit between it and the connecting plate 63, thereby interfering with the turning of the turning frame 2. Therefore, a further solution is to improve the support seat 4, such as Figure 8As shown, the support seat 4 includes a bottom plate 42, one end of the bottom plate 42 is provided with an opening 43 for the lifting joint 62 to pass through, L-shaped pads 44 are provided on the bottom plate 42 on both sides of the opening 43, a clamping plate 45 is vertically provided on the horizontal section of the L-shaped pad 44, a V-shaped groove 41 is provided on the clamping plate 45, and a rib 46 is provided between the vertical section of the L-shaped pad 44 and the bottom plate 42, and the support seat 4 is welded and fixed to the turning support frame 1 through the bottom plate 42. By setting the opening 43, during the turning process of the turning frame 2, the lifting joint 62 is always located in the opening 43 under the action of its own gravity, and does not affect the turning of the turning frame 2. The two clamping plates 45 on both sides of the opening 43 support the two ends of the rotating shaft 61 respectively, which is stable and reliable. The L-shaped pad 44 mainly plays the role of dispersing the force, and the rib 46 is used to improve the stability of the connection between the L-shaped pad 44 and the bottom plate 42.

Claims

1. A method for turning over a large aircraft lower structure, characterized in that: The invention comprises a turning tool for the lower structure of a large aircraft, wherein the turning tool for the lower structure of the large aircraft comprises a turning support frame (1) and a turning frame (2), wherein at least two supporting seats (4) are provided at the top of the turning support frame (1) along its length direction, and a V-shaped groove (41) whose axis is parallel to the length direction of the turning support frame (1) is provided at the top of the supporting seat (4), and a connecting seat (5) for installing a product component (3) is provided inside the left and right sides of the turning frame (2), and a turning support (6) capable of docking with the supporting seat (4) is provided outside the left and right sides of the turning frame (2), and a rotating shaft (61) and a lifting joint (62) are provided on the turning support (6), and the turning support (1) comprises two turning support frames (1), and the turning supports (6) on the left and right sides of the turning frame (2) are respectively placed in the V-shaped grooves (41) of the supporting seats (4) at the tops of the two turning support frames (1) through the rotating shafts (61), and the turning frame (2) can rotate around the rotating shaft (61) on any side; The following steps are also included: Step 1: Using the connecting seat (5), install the product component in the turning frame (2); Step 2: Connect the lifting device to all the lifting joints (62), lift the turning frame (2) onto the turning support frame (1), and place the rotating shafts (61) of the turning supports (6) on both sides of the turning frame (2) in the V-shaped grooves (41) of the support seats (4) of the turning support frame (1); Step 3: When turning over is required, connect the lifting device to the lifting joint (62) on the left side of the turning frame (2), lift the left side of the turning frame (2) to the upper right, and rotate it 90° around the rotating shaft (61) on the right side; Step 4: hoist the turning frame (2) as a whole away from the turning support frame (1) on the right side and onto the turning support frame (1) on the left side, so that the rotating shaft (61) of the turning support (6) below the turning frame (2) slides into the V-shaped groove (41) of the supporting seat (4) of the turning support frame (1) on the left side; Step 5: The lifting device drives the top of the turning frame (2) to move to the right and lowers the turning frame (2), so that it rotates 90° to the right around the rotating shaft (61) below, so that the rotating shaft (61) of the turning support (6) above the turning frame (2) slides into the V-shaped groove (41) of the support seat (4) of the turning support frame (1) on the right, thereby completing the turning of the product component (3).

2. The method for turning over the lower structure of a large aircraft according to claim 1, characterized in that: The turning support frame (1) comprises two tripods (11) and a connecting frame (12) connected between the two tripods (11); the supporting base (4) comprises two, which are respectively arranged on the top of the two tripods (11).

3. The method for turning over the lower structure of a large aircraft as claimed in claim 2, characterized in that: A foot plate (13) is provided at the bottom of the tripod (11), and an anchor bolt (14) is provided on the foot plate (13) and can be connected and fixed to a ground foundation.

4. The method for turning over the lower structure of a large aircraft as claimed in claim 2, characterized in that: The turning frame (2) comprises two front and rear C-shaped beams (21) and a plurality of cross beams (22) connected between the two C-shaped beams (21), and the turning supports (6) and the connecting seats (5) each comprise four, which are correspondingly arranged at the ends of the two C-shaped beams (21).

5. The method for turning over the lower structure of a large aircraft as claimed in claim 1, characterized in that: The turning support (6) further comprises a connecting plate (63) fixedly connected to the turning frame (2); the rotating shaft (61) is arranged at the outer end of the connecting plate (63); and the lifting joint (62) is rotatably arranged on the rotating shaft (61).

6. The method for turning over the lower structure of a large aircraft as claimed in claim 5, characterized in that: One end of the connection seat (5) is rotatably arranged at the inner end of the connection plate (63), and a product connection joint (51) is provided on a side of the connection seat (5) away from the turning frame (2).

7. The method for turning over the lower structure of a large aircraft as claimed in claim 5, characterized in that: The support seat (4) comprises a bottom plate (42), one end of the bottom plate (42) is provided with an opening (43) for the lifting joint (62) to pass through, L-shaped pads (44) are provided on the bottom plate (42) on both sides of the opening (43), a clamping plate (45) is vertically arranged on the horizontal section of the L-shaped pad (44), a V-shaped groove (41) is provided on the clamping plate (45), and a rib plate (46) is provided between the vertical section of the L-shaped pad (44) and the bottom plate (42), and the support seat (4) is fixed to the turning support frame (1) by welding through the bottom plate (42).

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