Overturning and positioning platform for overlong beam-shaped part of airplane and using method of overturning and positioning platform

Abstract

The invention belongs to the technical field of aircraft manufacturing, and discloses an aircraft ultra-long beam-shaped part overturning and positioning platform and a using method, the platform comprises N sets of swing rod assemblies, an overturning long shaft, a set of supporting assemblies, N sets of driving assemblies, two sets of overturning limiting assemblies, 2N sets of product clamping assemblies, an assembling shape maintaining frame and a control system; the front and rear end faces of the bottom of the supporting assembly are installed outside the bottom of the assembly shape-maintaining frame enclosure frame. N shaft supporting assemblies are arranged above the supporting assembly in the length direction, the overturning long shaft penetrates through the N shaft supporting assemblies, and the N sets of swing rod assemblies are fixed to the overturning long shaft; the N driving assemblies are installed on the inner side face of the bottom of the supporting assembly and drive the overturning long shaft to rotate so as to drive the swing rod assembly to rotate. The two sets of overturning limiting assemblies are installed on the supporting assembly and used for limiting different overturning angles. The upper end and the lower end of the same swing rod assembly are each provided with one product clamping assembly, and aircraft products are clamped and positioned. The control system is placed on one side of the whole platform, and the overturning action of the whole platform can be controlled through a control button on the control system.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft manufacturing, and in particular to an overturning and positioning platform for an extra-long beam-shaped component of an aircraft and a use method thereof. Background Art

[0002] Generally, the way to assemble the conformal frame on the aircraft product is to use a multi-point hanging and crane lifting method to approach the assembly conformal frame, and then fix the aircraft product after positioning it on the positioning component of the assembly conformal frame. Due to the extra-long size of the beam-shaped part and its assembly conformal frame being a frame-type structure, a simple crane lifting cannot approach the positioning component of the assembly conformal frame. If the problem of product transportation in places that cannot be reached by crane is solved manually, twenty or thirty people are needed to lift and find the position at the same time. This process is time-consuming and labor-intensive, and it is not easy to fine-tune the product position. Therefore, it is urgent to design a transfer platform to solve the problem of product transportation in places that cannot be reached by crane lifting. Summary of the invention

[0003] The purpose of the present application is to provide an overturning and positioning platform for an aircraft super-long beam-shaped component, a method for using the platform, and a method for measuring the disassembly force.

[0004] In order to achieve the above objectives, this application adopts the following technical solutions:

[0005] An aircraft super-long beam-shaped component flip positioning platform, comprising: N sets of swing arm assemblies, a flip long axis, a set of support assemblies, N sets of drive assemblies, two sets of flip limit assemblies, 2N sets of product clamping assemblies, an assembly retaining frame, and a control system;

[0006] The front and rear end surfaces of the bottom of the support assembly are installed on the outside of the bottom of the assembly profile frame;

[0007] N shaft support assemblies are arranged along the length above the support assembly, the flip long axis passes through the N shaft support assemblies, and N sets of swing rod assemblies are fixed on the flip long axis;

[0008] N sets of driving components are installed on the inner side of the bottom of the supporting component, and the driving components drive the flip long axis to rotate, thereby driving the swing arm component to rotate;

[0009] Two sets of flip limit assemblies are respectively installed on the support assembly to limit different flip angles;

[0010] A set of product clamping assemblies are respectively installed at the upper and lower ends of the same set of swing arm assemblies to clamp and adjust the aircraft products;

[0011] The control system is placed on one side of the entire platform, and the flipping action of the entire platform can be controlled through the control buttons thereon.

[0012] Furthermore, the swing arm assembly comprises: a rectangular tube, a blocking plate, a mounting plate, a tension sleeve, a shaft sleeve, a rib plate and a connecting plate;

[0013] The shaft sleeve is a cylindrical structure with a stepped through hole, and a flat structure is cut on one side. The stepped through hole of the shaft sleeve passes through the flip long shaft. The tension sleeve is installed in the large hole of the shaft sleeve and plays a role in holding the flip long shaft;

[0014] The plane end of the sleeve is connected to the connecting plate, the rib plate is connected between the sleeve and the connecting plate, the connecting plate is fixed to the mounting plate by bolts, the mounting plate is fixed to the upper surface of the rectangular tube, and the blocking plates are installed at both ends of the rectangular tube.

[0015] Furthermore, the flip long shaft is composed of several hollow short shafts, each short shaft is provided with keyways at both ends, and the short shafts are connected by couplings.

[0016] Further, the support assembly comprises: a rectangular tube base, 2N oblique supports and 2N shaft support assemblies;

[0017] 2N oblique supports are fixed on the rectangular tube base and tilted at a certain angle to avoid the assembly conformal frame of the aircraft's super-long beam-shaped parts. An axle support assembly is installed on each oblique support, and the axle support assembly is used to support the flip long axis;

[0018] The shaft support assembly consists of a bearing, two bearing covers, an upper bearing seat, and a lower bearing seat. The lower seat is installed on the inclined support, and the bearing is installed between the upper and lower seats and connected by screws; the two bearing covers are arranged on both sides of the upper and lower seats.

[0019] Further, the driving assembly includes: a connecting rectangular seat assembly, a support leg, a servo electric cylinder, a hinge seat assembly, a driving arm and a pin assembly;

[0020] One end of the driving arm is provided with a stepped through hole, with two sets of tension sleeves built in it connected to the flip long axis assembly, and one end is a fork ear structure connected to the piston rod ball head of the servo electric cylinder through a pin assembly;

[0021] The front end face of the connecting rectangular seat assembly is fixed to the inner side of the rectangular tube base of the supporting assembly, two sets of hinge seat assemblies are installed on both sides above the connecting rectangular seat assembly, the servo electric cylinder is installed between the two sets of hinge seat assemblies, and the support legs are supported on the lower surface of the connecting rectangular seat assembly to play a supporting role.

[0022] Furthermore, the two groups of flip limit assemblies are respectively installed at different limit positions, and are used to limit the product to be fixed in the horizontal and vertical positions;

[0023] Each set of rollover limit assembly consists of a limit switch mounting plate, a limit switch, a limit bumper and fasteners;

[0024] The limit switch mounting plate is fixed on the inclined support by fasteners, and the limit switch is mounted on the limit switch mounting plate;

[0025] The limit collision block is a quarter-circle ring, which is fixed on the flip long axis by fasteners;

[0026] When the flip long axis rotates and touches the limit switch, the limit switch sends a limit signal.

[0027] Furthermore, each two groups of the product clamping components are respectively mounted relatively on the upper and lower ends of the same group of swing arm component mounting plates, and a single group of product clamping components is composed of a clamping plate, a hook bolt, a handle nut, a movable handle clamping screw, a movable handle, and a rubber clamping block;

[0028] The position can be adjusted on the top, bottom, back and front of the product;

[0029] The card plate is mounted on the mounting plate of the swing arm assembly, and a vertical plate with threaded holes is provided on the card plate;

[0030] A set of clamping components is provided on the vertical plate, and another set of clamping components is provided on the clamping plate. The two sets of clamping components cooperate to clamp the product to be fixed;

[0031] A handle nut is also screwed onto the clamping plate, and a hook-shaped bolt is connected to the front of the handle nut to hook the product to be fixed;

[0032] The clamping assembly includes: a movable handle clamping screw and a movable handle, the movable handle is installed at one end of the movable handle clamping screw, and the other end of the movable handle clamping screw is provided with a rubber clamping block for clamping the product to be fixed.

[0033] A method for using an over-long beam-shaped component flipping and positioning platform for an aircraft, the steps are as follows:

[0034] Step 1. Press the horizontal position button of the control system to make the over-long beam-shaped part flip positioning platform of the aircraft in the horizontal position, unscrew all the movable handle clamping screws and hook bolts to make them in the outermost position;

[0035] Step 2. Use a crane to transport the aircraft product to the cardboard of the overlong beam-shaped part flipping positioning platform of the aircraft by hanging, and screw in all the movable handle clamping screws and handle nuts respectively, so that the rubber clamping blocks on the upper and lower sides and the back side clamp the product, and the hook-shaped bolts on the front side hook the product, and clamp the product to the product clamping assembly;

[0036] Step 3. Press the vertical station button of the control system, and the overturn positioning platform of the aircraft super-long beam-shaped component equipped with the aircraft product is overturned by the driving component, and stops after contacting the overturn limit component at the 90° position;

[0037] Step 4. The clamped aircraft product contacts the positioning assembly of the assembly retaining frame of the aircraft super-long beam-shaped part at the 90° position, and the movable handle clamping screw and the handle nut of the product clamping assembly are adjusted respectively, so that the laser measurement positioning point of the product meets the design requirements, and then the aircraft product can be processed for hole making;

[0038] Step 5. After the aircraft product is processed, the horizontal position button of the control system is pressed, and the over-long beam-shaped component flip positioning platform with the aircraft product installed is flipped under the drive of the driving component, and stops after contacting the flip limit component at the 0° position;

[0039] Step 6. Unscrew all the movable handle clamping screws and hook bolts to place them in the outermost position and separate them from the aircraft product, thus completing a use cycle of the aircraft super-long beam-shaped component flip positioning platform.

[0040] Beneficial effects: This application is mainly designed to solve the problem that the extra-long beam-shaped parts of aircraft cannot be close to the frame-type assembly conforming frame when being lifted by a crane. The platform adopts a rectangular tube array to greatly reduce the weight of the platform while ensuring the structural rigidity of the extra-long flip platform. The servo electric cylinder has good synchronous control accuracy, and the drive arm is used to hold the flip long axis assembly structure. Several drive assemblies are evenly distributed in the axial direction to achieve the flip long axis assembly. The rotation of the flip long axis assembly is achieved as the servo electric cylinder push rod is pushed out and recovered. The working platform has a simple structure and uses less human resources, which greatly reduces the original workload and ensures the quality and safety of the product. It solves the problem that the crane cannot reach the frame-type assembly conforming frame, and can be directly extended to the manufacture of other aircraft products in the aviation manufacturing industry.

[0041] The present application is further described in detail below in conjunction with the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 A schematic diagram of a vertical workstation of a flip positioning platform for an extra-long beam-shaped component of an aircraft;

[0043] Figure 2 A schematic diagram of a horizontal workstation of a flip positioning platform for an extra-long beam-shaped component of an aircraft;

[0044] Figure 3 Structural diagram of the swing arm assembly;

[0045] Figure 4 Schematic diagram of a single rocker assembly;

[0046] Figure 5 Support component structure diagram;

[0047] Figure 6 Schematic diagram of the shaft support assembly;

[0048] Figure 7 Drive component structure diagram;

[0049] Figure 8 Flip limit assembly structure diagram;

[0050] Fig. 9 Product clamping assembly structure diagram;

[0051] Explanation of the numbers in the figure: 1 rocker assembly; 1-1 rectangular tube; 1-2 blocking plate; 1-3 mounting plate; 1-4 tension sleeve; 1-5 shaft sleeve; 1-6 rib plate; 1-7 connecting plate; 2 flip long shaft; 3 support assembly; 3-1 rectangular tube base; 3-2 oblique support; 3-3 shaft support assembly; 3-3-1 bearing; 3-3-2 bearing cover; 3-3-3 upper half of the bearing seat; 3-3-4 lower half of the bearing seat; 4 drive assembly; 4-1 connecting rectangular seat assembly; 4-2 Support foot; 4-3 servo electric cylinder; 4-4 hinge assembly; 4-5 drive arm; 4-6 pin assembly; 5 flip limit assembly; 5-1 limit switch mounting plate; 5-2 limit switch; 5-3 limit bumper; 5-4 fastener; 6 product clamping assembly; 6-1 card plate; 6-2 hook bolt; 6-3 handle nut; 6-4 movable handle clamping screw; 6-5 movable handle; 6-6 rubber clamping block; 7 control system; 8 assembly conformal frame; 9 aircraft products. DETAILED DESCRIPTION

[0052] See also Figure 1 , Figure 2 A flip positioning platform for an aircraft super-long beam-shaped component comprises: N groups of rocker assemblies 1, a flip long axis 2, a support assembly 3, N groups of drive assemblies 4, two groups of flip limit assemblies 5, 2N groups of product clamping assemblies 6 and a control system 7.

[0053] The front and rear end surfaces of the bottom of the support assembly 3 are fixed to the outer side of the bottom of the surrounding frame of the assembly shape-protecting frame 8;

[0054] N shaft support assemblies are arranged along the length above the support assembly 3, the flip long axis 2 passes through the N shaft support assemblies, and N sets of rocker arm assemblies 1 are fixed on the flip long axis 2.

[0055] N sets of driving components 4 are installed on the inner side of the bottom of the supporting component 3, and the driving components 4 drive the flip shaft 2 to rotate, thereby driving the swing arm component 1 to rotate;

[0056] Two groups of flip limit assemblies 5 are respectively installed on the support assembly 3 to limit different flip angles;

[0057] Two groups of flip limit assemblies 5 are respectively installed on the support assembly 3 to limit different flip angles;

[0058] A set of product clamping assemblies 6 are respectively installed at the upper and lower ends of the same set of swing arm assemblies 1 to clamp and adjust the position of the aircraft product 9;

[0059] The control system 7 is placed on one side of the entire platform, and the turning action of the entire platform can be controlled by the control buttons thereon.

[0060] See also Figure 3 , Figure 4 The swing arm assembly 1 includes: a rectangular tube 1-1, a blocking plate 1-2, a mounting plate 1-3, a tension sleeve 1-4, a shaft sleeve 1-5, a rib plate 1-6 and a connecting plate 1-7;

[0061] The shaft sleeve 1-5 is a cylindrical structure with a stepped through hole, and a plane structure is cut on one side. The stepped through hole of the shaft sleeve 1-5 passes through the flip long shaft assembly 2. The tension sleeve 1-4 is installed in the large hole in the shaft sleeve 1-5 and plays a role in holding the flip long shaft assembly 2;

[0062] The plane end of the sleeve 1-5 is connected to the connecting plate 1-7, the rib plate 1-6 is connected between the sleeve 1-5 and the connecting plate 1-7, the connecting plate 1-7 is fixed to the mounting plate 1-3 by bolts, the mounting plate 1-3 is fixed to the upper surface of the rectangular tube 1-1, and the surface is required to be flat and smooth, and the blocking plate 1-2 is installed at both ends of the rectangular tube 1-1.

[0063] The flip long axis assembly 2 is composed of several hollow short axes, each of which is provided with keyways at both ends, and the short axes are connected by couplings.

[0064] See also Figure 5 , Figure 6 The support assembly 3 is composed of a rectangular tube base 3-1, several inclined supports 3-2 and an axle support assembly 3-3. The axle support assembly 3-3 is composed of a bearing 3-3-1, two bearing covers 3-3-2, an upper bearing seat 3-3-3 and a lower bearing seat 3-3-4. Several inclined supports 3-2 are installed on the rectangular tube base 3-1 and are tilted at a certain angle to avoid the assembly conformal frame 8 of the aircraft product 9.

[0065] See also Figure 7 The driving assembly 4 is composed of a connecting rectangular seat assembly 4-1, a support leg 4-2, a servo electric cylinder 4-3, a hinge assembly 4-4, a driving arm 4-5 and a pin assembly 4-6. A step through hole is set at one end of the driving arm 4-5, and two sets of tension sleeves are built in and connected to the flip long axis assembly 2. One end is an ear structure connected to the piston rod ball head of the servo electric cylinder 4-3 through the pin assembly 4-6. The front end face of the connecting rectangular seat assembly 4-1 is fixed to the inner side of the rectangular tube base 3-1 of the support assembly 3. Two sets of hinge assemblies 4-4 are installed on both sides above the connecting rectangular seat assembly 4-1. The servo electric cylinder 4-3 is installed between the two sets of hinge assemblies 4-4. The support leg 4-2 is supported on the lower surface of the connecting rectangular seat assembly 4-1 to play a supporting role.

[0066] See also Figure 8The two groups of flip limit assemblies 5 are respectively installed at different limit positions. Each group of flip limit assemblies 5 consists of a limit switch mounting plate 5-1, a limit switch 5-2, a limit bump block 5-3 and a fastener 5-4. The limit switch mounting plate 5-1 is fixed to the inclined support 3-2 by the fastener 5-4. The limit switch 5-2 is installed on the limit switch mounting plate 5-1. The limit bump block 5-3 is a quarter ring and is fixed to the flip long axis assembly 2 by the fastener 5-4.

[0067] See also Fig. 9 Every two groups of product clamping assemblies 6 are relatively installed on the upper and lower ends of the same group of rocker assembly 1 mounting plate 1-3. A single group of product clamping assemblies consists of a clamping plate 6-1, a hook bolt 6-2, a handle nut 6-3, a movable handle clamping screw 6-4, a movable handle 6-5, and a rubber clamping block 6-6, which can be adjusted in position above, below, on the back and in front of the aircraft product 9.

[0068] A method for using an over-long beam-shaped component flipping and positioning platform for an aircraft, further comprising the following contents:

[0069] Step 1. Press the horizontal position button of the control system 7 to make the over-long beam-shaped part flip positioning platform of the aircraft in the horizontal position, and unscrew all the movable handle clamping screws 6-4 and hook bolts 6-2 to make them in the outermost position;

[0070] Step 2. Use a crane to transport the aircraft product 9 to the clamping plate 6-1 of the over-long beam-shaped part flipping positioning platform of the aircraft by hanging, and screw in all the movable handle clamping screws 6-4 and handle nuts 6-3 respectively, so that the rubber clamping blocks 6-6 on the upper and lower sides and the back side clamp the product, and the hook-shaped bolt 6-2 on the front side hooks the product, and clamps the product on the product clamping assembly 6;

[0071] Step 3. Press the vertical position button of the control system 7, and the overturn positioning platform of the aircraft super-long beam-shaped component equipped with the aircraft product 9 is overturned under the drive of the driving component 4, and stops after contacting the overturn limit component 5 at the 90° position;

[0072] Step 4. The clamped aircraft product contacts the positioning assembly of the assembly retaining frame 8 of the aircraft super-long beam-shaped part at the 90° position, and the movable handle clamping screw 6-4 and the handle nut 6-3 of the product clamping assembly 6 are adjusted respectively, so that the laser measurement positioning point of the product meets the design requirements, and then the aircraft product 9 can be processed for hole making;

[0073] Step 5. After the aircraft product is processed, the horizontal position button of the control system 7 is pressed, and the aircraft super-long beam-shaped component flip positioning platform with the aircraft product is flipped under the drive of the driving component 4, and stops after contacting the flip limit component 5 at the 0° position;

[0074] Step 6. Unscrew all the movable handle clamping screws 6-4 and hook bolts 6-3 to place them in the outermost position and separate them from the aircraft product 9, thus completing a use cycle of the aircraft super-long beam-shaped component flipping and positioning platform.

Claims

1. An aircraft super-long beam-shaped component flipping and positioning platform, characterized in that The platform includes: N sets of swing arm assemblies, a flip long axis, a set of support assemblies, N sets of drive assemblies, two sets of flip limit assemblies, 2N sets of product clamping assemblies, an assembly profile holder, and a control system; The front and rear end surfaces of the bottom of the support assembly are installed on the outside of the bottom of the assembly profile frame; N shaft support assemblies are arranged along the length above the support assembly, the flip long axis passes through the N shaft support assemblies, and N sets of swing rod assemblies are fixed on the flip long axis; N sets of driving components are installed on the inner side of the bottom of the supporting component, and the driving components drive the flip long axis to rotate, thereby driving the swing arm component to rotate; Two sets of flip limit assemblies are respectively installed on the support assembly to limit different flip angles; A set of product clamping assemblies are respectively installed at the upper and lower ends of the same set of swing arm assemblies to clamp and adjust the aircraft products; The control system is placed on one side of the entire platform, and the flipping action of the entire platform can be controlled through the control buttons thereon.

2. The overturning and positioning platform for an aircraft super-long beam-shaped component according to claim 1, characterized in that: The swing rod assembly comprises: a rectangular tube, a blocking plate, a mounting plate, a tension sleeve, a shaft sleeve, a rib plate and a connecting plate; The shaft sleeve is a cylindrical structure with a stepped through hole, and a flat structure is cut on one side. The stepped through hole of the shaft sleeve passes through the flip long shaft. The tension sleeve is installed in the large hole of the shaft sleeve and plays a role in holding the flip long shaft; The plane end of the sleeve is connected to the connecting plate, the rib plate is connected between the sleeve and the connecting plate, the connecting plate is fixed to the mounting plate by bolts, the mounting plate is fixed to the upper surface of the rectangular tube, and the blocking plates are installed at both ends of the rectangular tube.

3. The overturning and positioning platform for an extra-long beam-shaped component of an aircraft according to claim 1, characterized in that: The flip long shaft is composed of several hollow short shafts, each short shaft is provided with key slots at both ends, and the short shafts are connected by couplings.

4. The overturning and positioning platform for an aircraft super-long beam-shaped component according to claim 1, characterized in that: The support assembly includes: a rectangular tube base, 2N oblique supports and 2N shaft support assemblies; 2N oblique supports are fixed on the rectangular tube base and tilted at a certain angle to avoid the assembly conformal frame of the aircraft's super-long beam-shaped parts. An axle support assembly is installed on each oblique support, and the axle support assembly is used to support the flip long axis; The shaft support assembly consists of a bearing, two bearing covers, an upper bearing seat, and a lower bearing seat. The lower seat is installed on the inclined support, and the bearing is installed between the upper and lower seats and connected by screws; the two bearing covers are arranged on both sides of the upper and lower seats.

5. The overturning and positioning platform for an extra-long beam-shaped component of an aircraft according to claim 1, characterized in that: The driving assembly includes: a connecting rectangular seat assembly, a support leg, a servo electric cylinder, a hinge seat assembly, a driving arm and a pin assembly; One end of the driving arm is provided with a stepped through hole, with two sets of tension sleeves built in it connected to the flip long axis assembly, and one end is a fork ear structure connected to the piston rod ball head of the servo electric cylinder through a pin assembly; The front end face of the connecting rectangular seat assembly is fixed to the inner side of the rectangular tube base of the supporting assembly, two sets of hinge seat assemblies are installed on both sides above the connecting rectangular seat assembly, the servo electric cylinder is installed between the two sets of hinge seat assemblies, and the support legs are supported on the lower surface of the connecting rectangular seat assembly to play a supporting role.

6. The overturning and positioning platform for an extra-long beam-shaped component of an aircraft according to claim 1, characterized in that: The two groups of flip limit assemblies are respectively installed at different limit positions, and are used to limit the product to be fixed in the horizontal and vertical positions; Each set of rollover limit assembly consists of a limit switch mounting plate, a limit switch, a limit bumper and fasteners; The limit switch mounting plate is fixed on the inclined support by fasteners, and the limit switch is mounted on the limit switch mounting plate; The limit collision block is a quarter-circle ring, which is fixed on the flip long axis by fasteners; When the flip long axis rotates and touches the limit switch, the limit switch sends a limit signal.

7. The overturning and positioning platform for an extra-long beam-shaped component of an aircraft according to claim 1, characterized in that: Each two groups of the product clamping components are relatively mounted on the upper and lower ends of the same group of swing arm component mounting plates, and a single group of product clamping components is composed of a clamping plate, a hook bolt, a handle nut, a movable handle clamping screw, a movable handle, and a rubber clamping block; The position can be adjusted on the top, bottom, back and front of the product; The card plate is mounted on the mounting plate of the swing arm assembly, and a vertical plate with threaded holes is provided on the card plate; A set of clamping components is provided on the vertical plate, and another set of clamping components is provided on the clamping plate. The two sets of clamping components cooperate to clamp the product to be fixed; A handle nut is also screwed onto the clamping plate, and a hook-shaped bolt is connected to the front of the handle nut to hook the product to be fixed; The clamping assembly includes: a movable handle clamping screw and a movable handle, the movable handle is installed at one end of the movable handle clamping screw, and the other end of the movable handle clamping screw is provided with a rubber clamping block for clamping the product to be fixed.

8. A method for using an overturning and positioning platform for an aircraft super-long beam-shaped member, characterized in that: The specific steps include: Step 1. Press the horizontal position button of the control system to make the over-long beam-shaped part flip positioning platform of the aircraft in the horizontal position, unscrew all the movable handle clamping screws and hook bolts to make them in the outermost position; Step 2. Use a crane to transport the aircraft product to the cardboard of the overlong beam-shaped part flipping positioning platform of the aircraft by hanging, and screw in all the movable handle clamping screws and handle nuts respectively, so that the rubber clamping blocks on the upper and lower sides and the back side clamp the product, and the hook-shaped bolts on the front side hook the product, and clamp the product to the product clamping assembly; Step 3. Press the vertical station button of the control system, and the overturn positioning platform of the aircraft super-long beam-shaped component equipped with the aircraft product is overturned by the driving component, and stops after contacting the overturn limit component at the 90° position; Step 4. The clamped aircraft product contacts the positioning assembly of the assembly retaining frame of the aircraft super-long beam-shaped part at the 90° position, and the movable handle clamping screw and the handle nut of the product clamping assembly are adjusted respectively, so that the laser measurement positioning point of the product meets the design requirements, and then the aircraft product is processed for hole making; Step 5. After the aircraft product is processed, the horizontal position button of the control system is pressed, and the over-long beam-shaped component flip positioning platform with the aircraft product installed is flipped under the drive of the driving component, and stops after contacting the flip limit component at the 0° position; Step 6. Unscrew all the clamping screws and hook bolts of the movable handles to place them in the outermost position and separate them from the aircraft product, thus completing a use cycle of the over-long beam-shaped part flipping and positioning platform for the aircraft.

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