An aircraft fuselage panel assembly jig

Abstract

The utility model discloses an airplane fuselage wallboard assembly jig, it includes mainframe, the suspension frame stretches out horizontal pole lower end inside and is provided with winding gyro wheel, the suspension steel cable lower end joint place fixedly connected with the fixed ring that is provided, the slide rail outside surface is provided with the fixed frame, the fixed frame with the slide rail opposite side fixedly connected with the inside support that is provided, through above -mentioned structure, the mainframe is fixedly connected with a pair of suspension frame in the top, and the suspension frame stretches out horizontal pole lower end inside and is provided with winding gyro wheel, and the winding gyro wheel outside winding fixedly connected with the suspension steel cable, and the suspension steel cable lower end joint place fixedly connected with the fixed ring, so that the assembly jig can hoist the fuselage wallboard spare to the required fixed position, and the mainframe side horizontal pole fixedly connected with a pair of slide rails, and the slide rail outside surface is provided with the fixed frame, so that the assembly jig can flexibly adjust the distance between the assembly support frame according to the actual need of assembly.

Description

Technical Field

[0001] This utility model relates to the field of aircraft manufacturing technology, and in particular to an aircraft fuselage panel assembly jig. Background Technology

[0002] Aircraft are characterized by their complex shape, more than one million parts and components, compact internal space, and complex systems. Their assembly requires solving problems such as precise docking of multiple parts and coordinated interchange of multiple processes. Against this background, aircraft assembly jigs have emerged. Through structures such as skeletons, positioning parts, and clamping parts, they provide stable positioning and clamping support for parts and components, and have become the core equipment to ensure the quality of aircraft assembly. Their assembly accuracy directly determines the docking accuracy of aircraft parts and the reliability of the whole aircraft.

[0003] While existing aircraft fuselage panel assembly jigs can meet most assembly needs, they still have room for improvement. Improvements could greatly enhance the efficiency of the jigs. Due to the large size of aircraft fuselage components, securing them to the jigs often requires the support of hoisting equipment. The existing jigs have fixed support intervals, making it impossible to flexibly adjust the distance between the jigs according to actual assembly needs. Utility Model Content

[0004] The purpose of this utility model is to at least solve one of the technical problems existing in the prior art, and to provide an aircraft fuselage panel assembly frame, which can hoist fuselage panel parts to the required fixed position, and allows the assembly frame to flexibly adjust the distance between the assembly support frames according to the actual assembly needs.

[0005] This utility model also provides an aircraft fuselage panel assembly frame as described above, including a main frame. A pair of suspension frames are fixedly connected to the top of the main frame. A winding roller is provided on the inner side of the lower end of the horizontal bar of the suspension frame. A suspension steel cable is wound and fixedly connected to the outer side of the winding roller. A fixing ring is fixedly connected to the lower end of the suspension steel cable. A pair of sliding rails are fixedly connected to the side horizontal bar of the main frame. A fixing frame is provided on the outer side of the sliding rail. An inner support is fixedly connected to the side of the fixing frame opposite to the sliding rail.

[0006] According to the present invention, an aircraft fuselage panel assembly frame is provided, wherein a power motor is fixedly connected to the top of the main frame, and an active roller is fixedly connected to the output end of the power motor.

[0007] According to the present invention, a fuselage panel assembly frame is provided, wherein a power rod is fixedly connected to the center of the winding roller shaft, a passive roller is fixedly connected to the outer surface of the center of the power rod, a belt is slidably fixedly connected to the outer surface of the passive roller, and the inner side of the belt is slidably fixedly connected to the outer surface of the driving roller.

[0008] According to the present invention, a counterweight block is fixedly connected to the bottom of the lowest crossbar of the main frame in an aircraft fuselage panel assembly frame.

[0009] According to the present invention, an aircraft fuselage panel assembly frame is provided with an outer support on the outside of the inner support, and the outer support is closely attached to the side of the fixing frame.

[0010] According to the present invention, an aircraft fuselage panel assembly frame is provided with a connector fixedly connected to the outer side of the frame, and the inner side of the connector is fixedly connected to the outer support.

[0011] According to the present invention, an aircraft fuselage panel assembly frame is provided with multiple fasteners fixedly connected to the inner side of the inner support, and a pair of adjusting bolts are slidably fixedly connected to the inner side of the fasteners, with a buffer pad fixedly connected to the head of the adjusting bolt.

[0012] According to the present invention, an aircraft fuselage panel assembly frame is provided with two sets of screws slidably and fixedly connected to the inner side of the bottom horizontal support rod of the main frame. An adjustment knob is fixedly connected above the screws, and a shim is fixedly connected below the screws.

[0013] Beneficial effects:

[0014] 1. A pair of suspension brackets are fixedly connected to the top of the main frame. A winding roller is provided on the inner side of the lower end of the horizontal bar of the suspension bracket. A suspension steel cable is fixedly connected to the outer side of the winding roller. A fixing ring is fixedly connected at the lower end of the suspension steel cable, so that the assembly frame can hoist the body panel parts to the required fixed position.

[0015] 2. A pair of sliding rails are fixedly connected to the side crossbars of the main frame. The outer side of the sliding rails is equipped with a fixed frame, which allows the assembly frame to flexibly adjust the distance between the assembly support frames according to the actual assembly needs. Attached Figure Description

[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments;

[0017] Figure 1 This is a perspective view of an aircraft fuselage panel assembly frame according to the present invention.

[0018] Figure 2This is a front view of an aircraft fuselage panel assembly jig according to the present invention;

[0019] Figure 3 This is a perspective view of an aircraft fuselage panel assembly frame and panel assembly support frame according to the present invention.

[0020] Figure 4 In this utility model Figure 1 Enlarged view of point A in the middle;

[0021] Figure 5 In this utility model Figure 3 Enlarged view of point B in the middle.

[0022] Legend:

[0023] 1. Main frame; 2. Suspension frame; 3. Winding roller; 4. Power rod; 5. Suspension cable; 6. Fixing ring; 7. Power motor; 8. Driving roller; 9. Belt; 10. Driven roller; 11. Counterweight; 12. Screw; 13. Adjusting knob; 14. Shim; 15. Fixing frame; 16. Connector; 17. Inner support; 18. Outer support; 19. Fixing component; 20. Adjusting bolt; 21. Buffer pad; 22. Sliding rail. Detailed Implementation

[0024] This section will describe in detail the specific embodiments of the present utility model. The preferred embodiments of the present utility model are shown in the accompanying drawings. The purpose of the drawings is to supplement the textual description with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the present utility model, but they should not be construed as limiting the scope of protection of the present utility model.

[0025] Reference Figure 1-5 This utility model provides an aircraft fuselage panel assembly frame, which includes a main frame 1. A pair of suspension frames 2 are fixedly connected to the top of the main frame 1. A winding roller 3 is provided on the inner side of the lower end of the horizontal bar of the suspension frame 2. A suspension steel cable 5 is wound and fixedly connected to the outer side of the winding roller 3. A fixing ring 6 is fixedly connected to the lower end of the suspension steel cable 5. A pair of sliding rails 22 are fixedly connected to the side horizontal bar of the main frame 1. A fixing frame 15 is provided on the outer side of the sliding rail 22. An inner support 17 is fixedly connected to the side of the fixing frame 15 opposite to the sliding rail 22.

[0026] Specifically, the power motor 7 drives the active roller 8 to rotate, and the power of the active roller 8 is transmitted to the passive roller 10 through the belt 9. The passive roller 10 rotates and drives the power rod 4, which in turn transmits the power to the winding roller 3. The winding roller 3 winds up the suspension cable 5, and the fixing ring 6, which is fixed to the suspension cable 5, lifts the aircraft fuselage panel to the outside of the inner support 17. Then, the inner support 17 and the outer support 18 cooperate to fix it. The sliding track 22 is provided with a track groove that runs vertically through it. The fixing frame 15 is fixed to the inside of the track groove by two fixing bolts. The fixing bolts can move within the track groove to achieve synchronous movement of the fixing frame 15. Because the aircraft fuselage panel is fixed between the inner support 17 and the outer support 18, the fixing frame 15, which is fixed to the inner support 17 and the outer support 18, can move laterally with the two to a suitable position as needed.

[0027] A power motor 7 is fixedly connected to the top of the main frame 1, and an active roller 8 is fixedly connected to the output end of the power motor 7.

[0028] Specifically, a motor bracket is provided on the outer surface of the power motor 7. The motor bracket is fixedly connected to the main frame 1 and the power motor 7. The power motor 7 provides power for the winding and hoisting of the winding roller 3.

[0029] A power rod 4 is fixedly connected to the center of the winding roller 3. A passive roller 10 is fixedly connected to the outer surface of the center of the power rod 4. A belt 9 is slidably fixedly connected to the outer surface of the passive roller 10. The inner side of the belt 9 is slidably fixedly connected to the outer surface of the driving roller 8.

[0030] Specifically, the function of belt 9 is to transmit the power of rotation of drive roller 8 to driven roller 10.

[0031] A counterweight 11 is fixedly connected to the bottom of the lowest horizontal bar of the main frame 1.

[0032] Specifically, the counterweight 11 is used to lower the center of gravity of the main frame 1 and prevent the main frame 1 from tipping over due to excessive upward shift of the center of gravity when hoisting the aircraft fuselage panels.

[0033] An outer support 18 is provided on the outside of the inner support 17, and the outer support 18 is closely attached to the side of the fixing frame 15.

[0034] Specifically, the gap between the outer support 18 and the inner support 17 is the fixed position of the aircraft fuselage panel.

[0035] A connector 16 is fixedly connected to the outer side of the fixed frame 15, and the inner side of the connector 16 is fixedly connected to the outer support 18 and the fixed frame 15.

[0036] Specifically, the connector 16 is fixed to the fixing bracket 15 by a pair of bolts.

[0037] The inner support 17 is fixedly connected to multiple fasteners 19, and the inner side of the fasteners 19 is fixedly connected to a pair of adjusting bolts 20. The bolt head of the adjusting bolts 20 is fixedly connected to a buffer pad 21.

[0038] Specifically, adjusting the distance between the adjusting bolt 20 and the adjusting buffer pad 21 and the fuselage wall panel, by applying pressure to the fuselage wall panel, makes the fuselage wall panel more tightly fixed. The buffer pad 21 can prevent the adjusting bolt 20 from damaging the fuselage wall panel due to excessive pressure. The outer support 18 is fixed with the same specification fastener 19 and buffer pad 21, and their function is the same as described above.

[0039] Two sets of screws 12 are slidably and fixedly connected to the inner side of the bottom horizontal support rod of the main frame 1. An adjustment knob 13 is fixedly connected above the screws 12, and a shim 14 is fixedly connected below the screws 12.

[0040] Specifically, by rotating the adjustment knob 13 and adjusting the extension length of the screw 12, when facing an uneven ground, the assembly frame can be adjusted to a horizontal state using the adjustment knob 13. The function of the shim 14 is to increase the contact area between the assembly frame and the ground, making the assembly frame more stable.

[0041] Working principle: First, the aircraft fuselage panel is fixed by passing through the holes of the fixing ring 6. Then, the power motor 7 drives the active roller 8 to rotate. The power of the active roller 8 is transmitted to the passive roller 10 through the belt 9. The passive roller 10 rotates and drives the power rod 4. The power rod 4 then transmits the power to the winding roller 3. The winding roller 3 winds up the suspension cable 5. The fixing ring 6, which is fixed to the suspension cable 5, lifts the aircraft fuselage panel to the outside of the inner support 17. Then, the outer support 18 is fixedly connected to the fixing frame 15 through the connector 16. At this time, the aircraft fuselage panel is in the bracket of the inner support 17 and the outer support 18. The fixing ring 6 is disengaged. After adjusting the relative position of the bolts on the side of the fixing frame 15 in the sliding rail 22, the bolts are tightened to fix the fixing frame 15. Finally, the adjusting bolt 20 is rotated, and the two sets of buffer pads 21 press against each other to fix the aircraft fuselage panel. The aircraft fuselage panel is thus fixed.

[0042] The embodiments of the present utility model have been described in detail above with reference to the accompanying drawings. However, the present utility model is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present utility model.

Claims

1. An aircraft fuselage panel assembly jig, comprising a main frame (1), characterized in that: A pair of suspension brackets (2) are fixedly connected to the top of the main frame (1). A winding roller (3) is provided on the inner side of the lower end of the horizontal bar of the suspension bracket (2). A suspension steel cable (5) is fixedly connected to the outer side of the winding roller (3). A fixing ring (6) is fixedly connected to the lower end of the suspension steel cable (5). A pair of sliding rails (22) are fixedly connected to the side horizontal bar of the main frame (1). A fixing frame (15) is provided on the outer side of the sliding rail (22). An inner support (17) is fixedly connected to the opposite side of the fixing frame (15) and the sliding rail (22).

2. The aircraft fuselage panel assembly jig according to claim 1, characterized in that, A power motor (7) is fixedly connected to the top of the main frame (1), and an active roller (8) is fixedly connected to the output end of the power motor (7).

3. The aircraft fuselage panel assembly jig according to claim 1, characterized in that, A power rod (4) is fixedly connected to the center of the winding roller (3), a passive roller (10) is fixedly connected to the outer surface of the center of the power rod (4), a belt (9) is slidably fixedly connected to the outer surface of the passive roller (10), and the inner side of the belt (9) is slidably fixedly connected to the outer surface of the active roller (8).

4. The aircraft fuselage panel assembly jig according to claim 1, characterized in that, A counterweight (11) is fixedly connected to the bottom of the lowest crossbar of the main frame (1).

5. The aircraft fuselage panel assembly jig according to claim 1, characterized in that, An outer support (18) is provided on the outside of the inner support (17), and the outer support (18) is close to the side of the fixing frame (15).

6. The aircraft fuselage panel assembly jig according to claim 1, characterized in that, The outer side of the fixed frame (15) is fixedly connected to a connector (16), and the inner side of the connector (16) is fixedly connected to the outer support (18).

7. The aircraft fuselage panel assembly jig according to claim 1, characterized in that, The inner support (17) is fixedly connected to a plurality of fasteners (19), and the fasteners (19) are slidably fixedly connected to a pair of adjusting bolts (20), and the adjusting bolts (20) are fixedly connected to a buffer pad (21) at the bolt head.

8. The aircraft fuselage panel assembly jig according to claim 1, characterized in that, The bottom horizontal support rod of the main frame (1) is slidably fixedly connected to two sets of screws (12). An adjustment knob (13) is fixedly connected above the screws (12), and a shim (14) is fixedly connected below the screws (12).

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