A pose adjustment device for an aircraft composite panel flip tool and method of use

Abstract

The application discloses a kind of for aircraft composite wallboard turnover tool's pose adjusting device and method, include multiple groups of turnover pose adjusting beam and control system, every group of turnover pose adjusting beam includes beam frame, pose adjusting mechanism, protective cover, maintenance cover plate, electrical element, beam frame main body is half-closed long strip plate welding structure, two ends are connected with wallboard turnover tool respectively, two groups of pose adjusting mechanism are embedded and fixed in the middle layer main bearing plate of beam frame, control system controls multiple groups of turnover pose adjusting beam pose adjusting and wallboard suction fixation, multiple groups of turnover pose adjusting beam synchronous turnover will wallboard be turned to required pose.

Description

Technical Field

[0001] This application relates to the field of aerospace manufacturing technology, and in particular to an attitude adjustment device and method for using a flipping fixture for aircraft composite panels. Background Technology

[0002] Modern aircraft wing structures widely utilize thin-walled stiffened structures consisting of a frame and skin. Stiffened panel structures are a crucial load-bearing structural form in wing architecture, characterized by a high aspect ratio, simple structure, light weight, and high flexibility. Weight reduction translates to increased payload, improving flight maneuverability and endurance. To meet increasingly stringent requirements for wing structures, composite materials are being used more and more extensively in wing construction.

[0003] During aircraft assembly, to meet the assembly and riveting requirements of panels at different workstations, the panels need to be flipped to change their orientation. Previously, metal panels were typically transported by flipping and hoisting. However, this method requires installing lifting joints on the panels, which can cause stress concentration at the joint connection points, affecting the product. Furthermore, the deformation of the panels during lifting and flipping is uncontrollable. Using this method for composite panels could potentially cause plastic deformation, internal damage, hidden scratches, and cracks. Moreover, because each panel has a different center of gravity, different panels require different hanging systems, resulting in poor versatility. The installation and removal of process joints are time-consuming and labor-intensive. Considering product safety, ease of use, and resource utilization, this flipping method is no longer suitable.

[0004] In addition, some domestic and international aerospace manufacturers have developed and designed specialized flipping equipment for large composite panel flipping. However, to ensure the safety of the panel throughout the flipping process, their equipment uses larger conformal frames and clamps. Because the panels themselves are large, the conformal frames are very bulky and heavy to enclose the panels and meet certain rigidity requirements, which in turn significantly increases the power and floor space required for the entire flipping equipment. Furthermore, different composite panels have significant surface variations, making conformal clamps incompatible. The clamps are also difficult to install and remove, and there is a risk of product damage during the installation and removal process. Therefore, it is necessary to develop an attitude adjustment device and a method for using a tooling system for flipping aircraft composite panels. Summary of the Invention

[0005] The purpose of this application is to provide an attitude adjustment device and a method for using a flipping fixture for aircraft composite panels. This method can be applied to the process flow of automatic flipping of aircraft composite panels in the aerospace manufacturing process.

[0006] To achieve the above objectives, this application adopts the following technical solution:

[0007] An attitude adjustment device for an aircraft composite panel flipping fixture includes multiple sets of flipping attitude adjustment beams and a control system. Each set of flipping attitude adjustment beams includes a beam frame, an attitude adjustment mechanism, a protective cover, a maintenance cover, and electrical components. The main body of the beam frame is a semi-enclosed long strip welded structure, with both ends connected to the panel flipping fixture. Two sets of attitude adjustment mechanisms are embedded and fixed on the main load-bearing plate in the middle layer of the beam frame. The electrical components are installed in the lower layer structure of the beam frame. The maintenance cover is installed at the lower layer opening of the beam frame. The top of the protective cover is connected to the attitude adjustment mechanism, and the bottom is fixed to the top opening of the beam frame. The control system controls the multiple sets of flipping attitude adjustment beams to adjust their attitude and adhere to the panel for fixation. The multiple sets of flipping attitude adjustment beams flip synchronously to flip the panel to the desired attitude.

[0008] The beam frame includes beam lifting point joints, welded frames, and bearing inner ring fixing components. The welded frame is a semi-enclosed long strip welded structure. One end of its length is a flat surface that is connected and fixed to the beam lifting point joint, which is connected to the wall panel flipping fixture. The other end is a double-ear structure that is connected to the inner ring of the slewing bearing in the wall panel flipping fixture through two bearing inner ring fixing components. The welded frame is divided into two layers in the height direction. The upper layer has no top plate, and the lower layer is a closed cavity with a maintenance opening cover. The middle layer is the main load-bearing plate. Two sets of posture adjustment mechanisms are embedded and fixed to the main load-bearing plate of the welded frame from the top.

[0009] The attitude adjustment mechanism includes a bottom fixed base, a top frame, three sets of clamping and adsorption components, two sets of scissor mechanisms, two guide rails, three vacuum sensors, and a polyurethane pad. The bottom fixed base is a welded structure of straight trapezoidal square steel with a base plate and positioning pins at the bottom, and two guide rail mounting plates and one mounting plate at the top. The attitude adjustment mechanism is positioned on the main load-bearing plate of the beam frame by the positioning pins on the bottom fixed base and the base plate. The two guide rails are respectively mounted on the guide rail mounting plates of the bottom fixed base.

[0010] The scissor lift mechanism includes a motor end fixed base, a movable base, a top frame mounting base, two long rods, two short rods, a lead screw, a bearing housing, a coupling, a motor, and a reducer. The short rods and long rods are arranged in pairs on either side of the lead screw. One end of the short rod is hinged to the motor end fixed base, and the other end is hinged to the center of the long rod. One end of the long rod is hinged to the movable base, and the other end is hinged to the top frame mounting base. The lead screw nut is fixed to the movable base. The end of the lead screw is connected sequentially to the bearing housing, coupling, reducer, and motor. The bottom of the bearing housing is fixed to the motor end fixed base. Two sets of scissor lift mechanisms are symmetrically arranged on the bottom fixed base. In one set, the bottom of the motor end fixed base of the scissor lift mechanism is fixed to the bottom fixed base of the attitude adjustment mechanism, and the movable base is fixed to the guide rail slider. In the other set, both the motor end fixed base and the movable base are fixed to the guide rail slider.

[0011] The top frame is a rectangular box-shaped welded plate with no bottom sealing plate. Three vacuum sensors are evenly distributed on the long side plates. In the two sets of scissor mechanisms, the top frame mounting base is fixed under the top plate of the top frame, and the polyurethane pad is installed on top of the top plate of the top frame. The three sets of clamping and adsorption assemblies are installed on the top frame from top to bottom. The clamping and adsorption assemblies include a cylinder, a transition joint, a flexible joint, a suction cup, and a support frame. The suction cup is connected to the flexible joint, the transition joint, and the cylinder in sequence. The cylinder flange mounting surface is fixed to the bottom of the support frame.

[0012] The method of using this attitude adjustment device includes the following:

[0013] 1. The control system selects and determines the position and number of suction cups that need to work based on the shape of the wall panel;

[0014] 2. The control system shuts off the air path of the cylinder below the suction cup of the wall panel to be flipped, which does not require working.

[0015] 3. The attitude adjustment mechanism on the flipping attitude adjustment beam adjusts the attitude of the wall panel to the theoretical position according to the theoretical shape of the panel to be flipped.

[0016] 4. Hoist the wall panel to the top of the multi-functional attitude adjustment device and lower it until the wall panel contacts the polyurethane pad of the tilting attitude adjustment beam;

[0017] 5. The suction cups on the tilting beam are simultaneously lifted to the adaptive contact wall panel skin adsorption wall panel;

[0018] 6. Observe the pressure value of the vacuum sensor on the side of the tilting and adjusting beam, check the suction cup pressure to confirm that the adsorption is correct, and then remove the hoisting equipment.

[0019] The 7-panel flipping fixture simultaneously flips multiple sets of flipping and adjusting beams to complete the panel flipping.

[0020] The advantages of this application lie in the combination of scissor-type attitude adjustment and dot matrix adsorption technology to achieve rapid conformal and clamping fixation of composite material wall panels with different shapes, and to realize the rapid docking and shape retention of large-size composite material wall panels and wall panel flipping fixtures. It solves the problems of stress concentration and hidden cracks that may exist in the flipping process of large-size composite material wall panels. Its features include simple structure, strong versatility, relatively low cost, and full automation. It is universally applicable to the flipping of composite material wall panel skins and even ordinary metal wall panels.

[0021] The present application will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0022] Figure 1 Axonometric drawing of an attitude adjustment device for an aircraft composite panel flipping fixture

[0023] Figure 2 Axonometric view of the tilting beam

[0024] Figure 3 Axonometric view of attitude adjustment mechanism

[0025] Figure 4 Isometric view of scissor lift mechanism

[0026] Figure 5 Axonometric view of clamping and adsorption components

[0027] Figure 6 Axonometric view of an attitude adjustment device for positioning and adsorbing composite panel in an aircraft composite panel flipping fixture.

[0028] The numbers in the diagram are explained as follows: 1. Tilting and adjusting beam; 2. Control system; 3. Beam frame; 4. Adjusting mechanism; 5. Protective cover; 6. Maintenance cover plate; 7. Electrical components; 8. Beam lifting point joint; 9. Welded frame; 10. Bearing inner ring fixing component; 11. Bottom fixing seat; 12. Top frame; 13. Clamping and adsorption assembly; 14. Scissor mechanism; 15. Guide rail; 16. Vacuum sensor; 17. Polyurethane pad; 18. Motor end fixing seat; 19. Moving seat; 20. Top frame mounting seat; 21. Long rod; 22. Short rod; 23. Lead screw; 24. Bearing seat; 25. Coupling; 26. Motor; 27. Reducer; 28. Cylinder; 29. ​​Transition joint; 30. Flexible joint; 31. Suction cup; 32. Support frame; 33. Panel tilting fixture. Detailed Implementation

[0029] See Figures 1-6 An attitude adjustment device for a flipping fixture for aircraft composite panels includes multiple sets of flipping attitude adjustment beams 1 and a control system 2. Each set of flipping attitude adjustment beams 1 includes a beam frame 3, an attitude adjustment mechanism 4, a protective cover 5, a maintenance cover 6, and electrical components 7. The main body of the beam frame 3 is a semi-enclosed long strip welded structure, with both ends connected to the panel flipping fixture 33. Two sets of attitude adjustment mechanisms 4 are embedded and fixed on the main load-bearing plate in the middle layer of the beam frame 3. The electrical components 7 are installed in the lower structure of the beam frame 3. The maintenance cover 6 is installed at the lower opening of the beam frame 3. The top of the protective cover 5 is connected to the attitude adjustment mechanism 4, and the bottom is fixed to the top opening of the beam frame 3. The control system 2 controls the multiple sets of flipping attitude adjustment beams 1 to adjust their attitude and adhere to the panel for fixation. The multiple sets of flipping attitude adjustment beams 1 flip synchronously to flip the panel to the desired attitude.

[0030] The beam frame 3 includes a beam lifting point joint 8, a welded frame 9, and a bearing inner ring fixing component 10. The welded frame 9 is a semi-enclosed long strip plate welded structure. One end of its length is a plane that is connected and fixed to the beam lifting point joint 8. The beam lifting point joint 8 is connected to the wall panel flipping fixture 33. The other end is a double-ear structure that is connected to the inner ring of the slewing bearing in the wall panel flipping fixture 33 through two bearing inner ring fixing components 10. The welded frame 9 is divided into two layers in the height direction. The upper layer has no top plate, and the lower layer is a closed cavity with a maintenance opening cover. The middle layer is the main load-bearing plate. Two sets of attitude adjustment mechanisms 4 are embedded and fixed to the main load-bearing plate of the welded frame 9 through the opening at the top of the welded frame 9.

[0031] The attitude adjustment mechanism 4 includes a bottom fixed seat 11, a top frame 12, three sets of clamping and adsorption components 13, two sets of scissor mechanisms 14, two guide rails 15, three vacuum sensors 16, and a polyurethane pad 17. The bottom fixed seat 11 is a straight trapezoidal square steel welded structure with a base plate and positioning pin at the bottom, and two guide rail mounting plates and one mounting plate at the top. The attitude adjustment mechanism 4 is positioned and mounted on the main load-bearing plate of the beam frame 3 by the positioning pin on the bottom fixed seat 11 and the base plate. The two guide rails 15 are respectively mounted on the guide rail mounting plates of the bottom fixed seat 11.

[0032] The scissor lift mechanism 14 includes a motor end fixed seat 18, a movable seat 19, a top frame mounting seat 20, two long rods 21, two short rods 22, a lead screw 23, a bearing seat 24, a coupling 25, a motor 26, and a reducer 27. The short rods 22 and long rods 21 are arranged in pairs on both sides of the lead screw 23. One end of the short rod 22 is hinged to the motor end fixed seat 18, and the other end is hinged to the center of the long rod 21. One end of the long rod 21 is hinged to the movable seat 19, and the other end is hinged to the top frame mounting seat 20. The lead screw nut is fixed to the movable seat 19. The end of the lead screw is connected to the bearing seat 24, the coupling 25, the reducer 27, and the motor 26 in sequence. The bottom of the bearing seat 24 is fixed to the motor end fixed seat 18. Two sets of scissor lift mechanisms 14 are symmetrically arranged on the bottom fixed base 11. The motor end fixed base 18 of one set of scissor lift mechanisms 14 is fixed to the bottom fixed base 11 of the posture adjustment mechanism 4, and the movable base 19 is fixed on the slider of the guide rail 15. The motor end fixed base 18 and the movable base 19 of the other set of scissor lift mechanisms 14 are both fixed to the slider of the guide rail 15.

[0033] The top frame 12 is a rectangular box-shaped welded plate with no bottom sealing plate. Three vacuum sensors 16 are evenly distributed on the long side plate. In the two sets of scissor mechanisms 14, the top frame mounting base 20 is installed and fixed under the top plate of the top frame 12, and the polyurethane pad 17 is installed on the top plate of the top frame 12. The three sets of clamping and adsorption assemblies 13 are installed on the top frame 12 from top to bottom. The clamping and adsorption assembly 13 includes a cylinder 28, a transition joint 29, a flexible joint 30, a suction cup 31, and a support frame 32. The suction cup 31 is connected to the flexible joint 30, the transition joint 29, and the cylinder 28 in sequence. The flange mounting surface of the cylinder 28 is fixed to the bottom of the support frame 32.

[0034] The method of using this attitude adjustment device includes the following:

[0035] 1. Control system 2. Select and determine the position and quantity of suction cups that need to work based on the shape of the wall panel;

[0036] 2 Control system 2 Close the working suction cup 31 below the non-working wall panel to be flipped; 28 Air passage;

[0037] 3. The attitude adjustment mechanism 4 on the flipping attitude adjustment beam 1 adjusts the attitude of the wall panel to the theoretical position according to the theoretical shape of the wall panel to be flipped.

[0038] 4. Hoist the wall panel to the top of the multi-functional attitude adjustment device and lower it until the wall panel contacts the polyurethane pad 17 of the flipping attitude adjustment beam 1;

[0039] 5. The working cylinder 28 on the tilting beam 1 synchronously lifts the suction cup 31 to the adaptive contact wall panel skin adsorption wall panel.

[0040] 6. Observe the pressure value of the vacuum sensor 16 on the side of the tilting beam 1, check the pressure of the suction cup 31 to confirm that the adsorption is correct, and then remove the hoisting equipment.

[0041] The wall panel flipping fixture 33 flips multiple sets of flipping and adjusting beams 1 simultaneously to complete the wall panel flipping.

Claims

1. An attitude adjustment device for an aircraft composite panel flipping fixture, characterized in that... It includes multiple sets of tilting and attitude-adjusting beams and a control system. Each set of tilting and attitude-adjusting beams includes a beam frame, attitude-adjusting mechanism, protective cover, maintenance cover, and electrical components. Both ends are connected to the wall panel tilting fixture. Two sets of attitude-adjusting mechanisms are embedded and fixed to the main load-bearing plate in the middle layer of the beam frame. The electrical components are installed in the lower structure of the beam frame. The maintenance cover is installed at the lower opening of the beam frame. The top of the protective cover is connected to the attitude-adjusting mechanism, and the bottom is fixed to the top opening of the beam frame. The control system controls multiple sets of tilting and adjusting beams to adjust their posture and adhere to the wall panel for fixation. The multiple sets of tilting and adjusting beams synchronously tilt the wall panel to the desired posture. The beam frame includes beam lifting point joints, a welded frame, and bearing inner ring fixing components. The welded frame is a semi-enclosed, long strip-shaped welded structure. One end of its length is a flat surface connected and fixed to the beam lifting point joint, which is connected to the wall panel tilting fixture. The other end is a double-ear structure, connected to the inner ring of the slewing bearing in the wall panel tilting fixture via two bearing inner ring fixing components. The welded frame is divided into two layers in its height direction: the upper layer has no top plate, the lower layer is a closed cavity with a maintenance cover, and the middle layer is the main load-bearing plate. The attitude adjustment mechanism is embedded and fixed to the main load-bearing plate of the welded frame from the top. The mechanism includes a bottom fixing seat, a top frame, three sets of clamping and adsorption components, two sets of scissor mechanisms, two guide rails, three vacuum sensors, and a polyurethane pad. The bottom fixing seat is a welded structure of straight trapezoidal square steel, with a base plate and positioning pins at the bottom. The top has two guide rail mounting plates and one mounting plate. The attitude adjustment mechanism is positioned on the main load-bearing plate of the middle layer of the beam frame via the positioning pins on the bottom fixing seat and the base plate. The two guide rails are respectively mounted on the guide rail mounting plates of the bottom fixing seat. The two sets of scissor mechanisms are symmetrically arranged on the bottom fixing seat. One set of scissor lift mechanisms has its motor end fixed base on the bottom of the attitude adjustment mechanism, and its movable base fixed on the guide rail slider; the other set of scissor lift mechanisms has both its motor end fixed base and movable base fixed on the guide rail slider. The top frame is a rectangular box-shaped welded plate with no bottom sealing plate. Three vacuum sensors are evenly distributed on the long side plates. In both sets of scissor lift mechanisms, the top frame mounting base is fixed below the top plate of the top frame, and a polyurethane pad is installed on top of the top plate of the top frame. Three sets of clamping and adsorption components are installed on the top frame from top to bottom. The scissor lift mechanism includes a motor end fixed base, a movable base, a top frame mounting base, two long rods, two short rods, and a wire. The screw includes a lever, bearing housing, coupling, motor, and reducer. Short rods and long rods are arranged in pairs on both sides of the lead screw. One end of the short rod is hinged to the motor end fixed seat, and the other end is hinged to the center of the long rod. One end of the long rod is hinged to the movable seat, and the other end is hinged to the top frame mounting seat. The lead screw nut is fixed to the movable seat. The end of the lead screw is connected to the bearing housing, coupling, reducer, and motor in sequence. The bottom of the bearing housing is fixed to the motor end fixed seat. The clamping and adsorption assembly includes a cylinder, transition joint, flexible joint, suction cup, and support frame. The suction cup is connected to the flexible joint, transition joint, and cylinder in sequence. The cylinder flange mounting surface is fixed to the bottom of the support frame.

2. A method of using the attitude adjustment device for aircraft composite panel flipping fixture as described in claim 1, characterized in that... Includes the following: 2-1 The control system selects and determines the location and number of suction cups that need to work based on the shape of the wall panel; 2-2 The control system shuts off the air path of the cylinder below the suction cup of the wall panel to be flipped that does not require work; 2-3 The attitude adjustment mechanism on the tilting and attitude adjustment beam adjusts the attitude of the wall panel to be tilted to the theoretical position according to the theoretical shape of the panel to be tilted; 2-4 Hoist the wall panel to the top of the attitude adjustment device and lower it until the wall panel contacts the polyurethane pad of the tilting attitude adjustment beam; 2-5 The suction cups on the tilting beam are simultaneously lifted to the adaptive contact wall panel skin adsorption wall panel; 2-6 Observe the pressure value of the vacuum sensor on the side of the tilting and adjusting beam, check the suction cup pressure to confirm that the adsorption is correct, and then remove the hoisting equipment; 2-7 The panel flipping fixture will simultaneously flip multiple sets of flipping and adjusting beams to complete the panel flipping.

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