CN221937305U - A tool for demoulding aircraft wall panels - Google Patents

Abstract

The utility model belongs to the technical field of aircraft assembly, and discloses a tool for demoulding aircraft wall panels. The tool for demoulding aircraft wall panels includes a frame, a connecting beam and a clamping assembly, wherein the connecting beam is detachably connected to the frame, the connecting beam is arranged below the frame and the distance between the connecting beam and the frame is adjustable, the clamping assembly is detachably connected to the connecting beam, and the frame is used to connect a lifting device. The aircraft wall panel includes a wall panel body and an ear piece integrally formed with the aircraft wall panel, the ear piece extends outward along the side of the aircraft wall panel, and the clamping assembly is used to fix the ear piece. When demoulding, it is only necessary to fix the ear piece in the clamping assembly, and then connect the lifting device to the frame, and the lifting device drives the frame to move upward, thereby driving the aircraft wall panel as a whole to move upward through the ear piece, so that the aircraft wall panel is separated from the forming mold of the aircraft wall panel, and the demoulding work of the aircraft wall panel is completed.

Description

A tool for demoulding aircraft wall panels

Technical Field

The utility model relates to the technical field of aircraft assembly, in particular to a tooling for aircraft wall panel demoulding.

Background Art

Aircraft siding constitutes the outer shell of the fuselage and is one of the most important components of the fuselage. The outer dimensions of aircraft siding are generally large. Aircraft siding needs to be formed by laying and curing in a molding mold. After molding, it needs to be demolded to obtain the desired aircraft siding product.

The existing demoulding technology is adsorption demoulding, which is to directly adsorb the adsorption mechanism to the surface of the aircraft wall panel. The adsorption mechanism is connected to a lifting device, and the lifting device lifts the wall panel from the mold through the adsorption mechanism, thereby completing the demoulding to obtain the aircraft wall panel product.

The adsorption demoulding method usually requires the installation of vacuum pumps, pressure sensors and other devices, and the overall cost of the adsorption demoulding tooling is relatively high. In addition, since the surface of the aircraft wall panel is relatively rough, after the adsorption demoulding tooling is adsorbed on the surface of the aircraft wall panel, air can easily enter and fall off between the vacuum suction cup and the aircraft wall panel, making the safety and stability of the adsorption demoulding tooling poor. In addition, since the aircraft wall panel is relatively thin, if the adsorption force is not properly controlled when using the adsorption demoulding tooling, the aircraft wall panel will be deformed.

Utility Model Content

The utility model aims to provide a tool for demoulding aircraft wall panels, so as to solve the problems of high cost, poor safety and stability of the tool for demoulding aircraft wall panels, and deformation of the aircraft wall panels caused by demoulding.

To achieve this purpose, the utility model adopts the following technical solutions:

Provided is a tool for demoulding an aircraft panel, which is used for demoulding an aircraft panel. The aircraft panel comprises a panel body and an ear piece integrally formed with the panel body, wherein the ear piece extends outward along the side of the panel body. The tool for demoulding an aircraft panel comprises:

A frame, the frame being used to be connected to a lifting device;

A connecting beam, wherein at least one connecting beam is provided, each connecting beam is detachably connected to the frame, the connecting beam is arranged below the frame, and the distance between the connecting beam and the frame is adjustable;

A clamping assembly is detachably connected to the connecting beam, and the two ends of each connecting beam are respectively provided with the clamping assembly, and the clamping assembly is used to fix the ear piece.

Preferably, the frame includes two cross beams and at least one longitudinal beam, the two cross beams are parallel and spaced apart, the longitudinal beam is arranged between the two cross beams, the two ends of the longitudinal beam are respectively connected to the two cross beams, the two ends of the connecting beam are detachably connected to the two cross beams, and the connecting beam is arranged parallel to the longitudinal beam.

Preferably, a connecting rod is provided between each of the cross beams and the connecting beam, one end of the connecting rod is detachably connected to the cross beam, and the other end of the connecting rod is detachably connected to the connecting beam.

Preferably, a fourth lifting ear seat is detachably connected to the crossbeam, a fourth lifting ear is connected to the fourth lifting ear seat, a first bolt is passed through two lifting ear holes of the fourth lifting ear, the first bolt is provided with a hole for the connecting rod to pass through along an axial direction perpendicular to the first bolt, and the connecting rod is threadedly connected to the first bolt.

Preferably, the clamping assembly includes a base, a pressure plate and a locking piece, one side of the pressure plate is detachably connected to the connecting beam, the base is an L-shaped structure, the other side of the pressure plate is detachably connected to one end of the base, and the pressure plate and the base are surrounded by a placement groove, the placement groove is used to plug in the ear piece, and the locking piece can be passed through and fix the ear piece.

Preferably, the clamping assembly also includes a first flexible member and a second flexible member, the first flexible member is arranged in the placement groove and connected to the side of the pressure plate, the second flexible member is arranged in the placement groove and connected to the surface of the base, and the first flexible member and the second flexible member are used to accommodate the ear piece.

Preferably, a third flexible member is provided on a side of the base facing away from the pressure plate, and the third flexible member is used to contact with a forming mold of the aircraft wall panel.

Preferably, the pressure plate is provided with a first lifting ear, the first lifting ear is provided with a first hole, the connecting beam is detachably connected to a second lifting ear, the second lifting ear is provided with a second hole, the first hole and the second hole are penetrated by a second bolt, and are locked by a second nut.

Preferably, the locking member comprises a locking bolt, one end of which passes through the pressure plate and the ear piece in sequence and is threadedly connected to the base.

Preferably, two locking members are spaced apart on the pressure plate along a direction perpendicular to the extension of the connecting beam.

Beneficial effects of the utility model:

The utility model provides a tool for demoulding an aircraft wall panel, comprising a frame, a connecting beam and a clamping assembly, wherein the frame is used to connect a lifting device, the connecting beam is detachably connected to the frame, and the clamping assembly is detachably connected to the connecting beam. When the tool for demoulding an aircraft wall panel is idle, the frame, the connecting beam and the clamping assembly can be disassembled and placed separately, which is conducive to saving storage space. The connecting beam is arranged below the frame and the distance between the connecting beam and the frame is adjustable, so that the tool is easy to adapt to aircraft wall panels with different outer contour shapes. The aircraft siding includes a siding body and an ear piece integrally formed with the siding body, the ear piece extends outward along the side of the siding body, the clamping assembly is used to fix the ear piece, and after the lifting device is connected to the frame, the lifting device drives the frame to move upward, thereby driving the aircraft siding as a whole to move upward through the ear piece, so that the aircraft siding is separated from the molding mold of the aircraft siding, and the demoulding of the aircraft siding is completed. This process only requires the tooling used for demoulding the aircraft siding to act on the ear piece of the aircraft siding, without the aid of additional devices, thereby reducing the cost of demoulding the aircraft siding, and has high safety and stability. The siding body will not be deformed. After the aircraft siding is demoulded, the ear piece integrally formed with the aircraft siding will be cut off, leaving only the aircraft siding product, so there is no need to worry about the ear piece being damaged after the clamping assembly acts on the ear piece.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a schematic structural diagram of a tooling for aircraft panel demoulding provided by an embodiment of the utility model;

FIG2 is a partial enlarged view of portion B in FIG1 ;

FIG3 is a partial enlarged view of portion A in FIG1 ;

FIG4 is a schematic structural diagram of a clamping assembly and a connecting member provided in an embodiment of the present utility model;

FIG. 5 is a schematic structural diagram of an aircraft wall panel provided by a specific embodiment of the utility model.

In the figure:

1. Frame; 11. Crossbeam; 12. Longitudinal beam;

2. Clamping assembly; 21. Base; 22. Pressing plate; 23. First flexible member; 24. Second flexible member; 25. Third flexible member; 26. First lifting ear; 261. First hole; 27. Locking member;

3. Connecting beam;

4. Connecting rod; 41. Connecting rod seat;

5. Connecting piece; 51. Second lifting ear; 511. Second hole; 52. Second bolt; 53. Second nut; 54. Second lifting ear seat;

6. The third lifting eye; 7. Lifting piece; 8. The fourth lifting eye; 81. The fourth lifting eye seat; 9. The fifth lifting eye; 91. The fifth lifting eye seat;

100. Wall panel body; 200. Ears.

DETAILED DESCRIPTION

The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only the parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

In the description of this embodiment, the terms "upper", "lower", "right", etc., are based on the directions or positions shown in the drawings, and are only for the convenience of description and simplified operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

As shown in Fig. 1 to Fig. 5, a specific embodiment of the utility model provides a tool for demoulding an aircraft wall panel. The aircraft wall panel is generally large in size and includes a wall panel body 100 and an ear piece 200 integrally formed with the wall panel body 100, and the ear piece 200 extends outward along the side of the wall panel body 100. The aircraft wall panel needs to be formed by laying and curing in a molding mold, and after molding, it needs to be demoulded to obtain the desired aircraft wall panel product.

The tooling for demoulding aircraft wall panels includes a frame 1, a connecting beam 3 and a clamping assembly 2, wherein the frame 1 is used to be connected to a lifting device; at least one connecting beam 3 is provided, each connecting beam 3 is detachably connected to the frame 1, the connecting beam 3 is arranged below the frame 1, and the distance between the connecting beam 3 and the frame 1 is adjustable; the clamping assembly 2 is detachably connected to the connecting beam 3, and clamping assemblies 2 are provided at both ends of each connecting beam 3, and the clamping assembly 2 is used to fix the ear piece 200.

The connecting beam 3 is detachably connected to the frame 1, and the clamping assembly 2 is detachably connected to the connecting beam 3. When the tooling for demoulding the aircraft wall panel is idle, the frame 1, the connecting beam 3 and the clamping assembly 2 can be disassembled and placed separately, which is conducive to saving storage space. The connecting beam 3 is arranged below the frame 1 and the distance between the connecting beam 3 and the frame 1 is adjustable, so that the tooling can be adapted to aircraft wall panels with different outer contour shapes. The aircraft siding includes a siding body 100 and an ear piece 200 integrally formed with the siding body 100, the ear piece 200 extends outward along the side of the siding body 100, and the clamping assembly 2 is used to fix the ear piece 200. After the lifting device is connected to the frame 1, the lifting device drives the frame 1 to move upward, thereby driving the aircraft siding as a whole to move upward through the ear piece 200, so that the aircraft siding is separated from the molding mold of the aircraft siding, and the demoulding work of the aircraft siding is completed. This process only requires the tooling used for demoulding the aircraft siding to act on the ear piece 200 of the aircraft siding, without the aid of additional devices, reducing the cost of demoulding the aircraft siding, and having higher safety and stability. The siding body 100 will not be deformed. After the aircraft siding is demoulded, the ear piece 200 integrally formed with the aircraft siding will be cut off, leaving only the aircraft siding product, so there is no need to worry about the ear piece 200 being damaged after the clamping assembly 2 acts on the ear piece 200.

The frame 1 includes two cross beams 11 and at least one longitudinal beam 12. The two cross beams 11 are parallel and spaced apart. The longitudinal beam 12 is disposed between the two cross beams 11. The two ends of the longitudinal beam 12 are respectively connected to the two cross beams 11. The two ends of the connecting beam 3 are detachably connected to the two cross beams 11. When the tooling for demoulding the aircraft wall panel is idle, the connecting beam 3 can be placed alone to save storage space. The connecting beam 3 is arranged in parallel with the longitudinal beam 12. In this embodiment, two longitudinal beams 12 are spaced apart. The two cross beams 11 and the two longitudinal beams 12 form a frame 1. The cross beams 11 and the longitudinal beams 12 can be connected by welding or other methods to improve the overall stability of the frame 1. When acting on the aircraft wall panel, two frames 1 are required. The two frames 1 are spaced apart above the aircraft wall panel along the length direction of the aircraft wall panel to be demoulded. This design can reduce the length dimension of each frame 1, which is conducive to saving storage space for the frame 1.

Further, as shown in Fig. 1 and Fig. 2, in order to facilitate the connection between the frame 1 and the lifting device, the frame 1 is provided with a third lifting lug 6, and the third lifting lug 6 is connected with a lifting member 7, and the lifting member 7 is an arched member for hooking. In this embodiment, the third lifting lug 6 is arranged on the upper surface of the crossbeam 11, and two third lifting lugs 6 are arranged on each crossbeam 11 at intervals, so that when lifting, the frame 1 moves upward more smoothly.

As shown in Figures 1 and 3, a connecting rod 4 is provided between each cross beam 11 and the connecting beam 3, one end of the connecting rod 4 is detachably connected to the cross beam 11, and the other end of the connecting rod 4 is detachably connected to the connecting beam 3. When the tooling for demoulding the aircraft wall panel is idle, the connecting rod 4 can be placed separately to save storage space. Specifically, a fourth lifting ear seat 81 is detachably connected to the cross beam 11, and a fourth lifting ear 8 is connected to the fourth lifting ear seat 81. A first bolt is inserted into two lifting ear holes of the fourth lifting ear 8. The first bolt is provided with a hole for the connecting rod 4 to be inserted in the axial direction perpendicular to the first bolt. The connecting rod 4 is screwed to the first bolt, so that the connecting rod 4 can rise or fall along the cross beam 11, so as to adjust the distance between the connecting beam 3 connected to the other end of the connecting rod 4 and the aircraft wall panel. In this embodiment, the lengths of the connecting rods 4 selected between the two cross beams 11 and each connecting beam 3 are different to adapt to the outer contour shape of the aircraft panel to be demolded. In other embodiments, connecting rods 4 of the same length can also be selected, and the distance between the connecting beams 3 and the aircraft panel to be demolded can be adjusted by adjusting the screw connection position between the connecting rods 4 and the cross beams 11.

Specifically, in order to achieve the purpose of detachable connection between the connecting beam 3 and the connecting rod 4, the connecting beam 3 is detachably connected with a fifth hanging ear seat 91, the fifth hanging ear seat 91 is connected with a fifth hanging ear 9, the fifth hanging ear 9 is provided with a fifth hole, one end of the connecting rod 4 is welded with a connecting rod seat 41, the connecting rod seat 41 is provided with two connecting holes, and the connecting bolt can pass through one connecting hole, the fifth hole and the other connecting hole in sequence to connect the connecting rod seat 41 and the fifth hanging ear 9. In this embodiment, the butterfly nut is screwed with the connecting bolt, and the butterfly nut will not loosen under vibration or dynamic load, thereby improving the reliability of the connection. The butterfly nut can also be conveniently rotated and disassembled manually when disassembly is required.

As shown in Fig. 1, Fig. 4 and Fig. 5, the clamping assembly 2 includes a base 21, a pressing plate 22 and a locking member 27. One side of the pressing plate 22 is detachably connected to the connecting beam 3. The base 21 is in an L-shaped structure. The other side of the pressing plate 22 is detachably connected to one end of the base 21. The pressing plate 22 and the base 21 are surrounded by a placement groove, which is used to insert the ear piece 200. The locking member 27 can penetrate and fix the ear piece 200. Specifically, the locking member 27 includes a locking bolt, one end of which penetrates the pressing plate 22 and the ear piece 200 in turn and is threadedly connected to the base 21. Two locking members 27 are arranged on the pressing plate 22 at intervals along the direction perpendicular to the extension of the connecting beam 3. This makes the connection between the clamping assembly 2 and the ear piece 200 more stable.

In order to facilitate the connection between the clamping assembly 2 and the connecting beam 3, a connecting member 5 is connected to the connecting beam 3, and the clamping assembly 2 is detachably connected to the connecting beam 3 through the connecting member 5. Optionally, a first lifting ear 26 is provided on the pressure plate 22, and a first hole 261 is provided on the first lifting ear 26. The connecting member 5 includes a second lifting ear 51 detachably connected to the connecting beam 3. When the tooling for demoulding the aircraft wall panel is idle, the second lifting ear 51 can be placed separately to save storage space. A second hole 511 is provided on the second lifting ear 51, and the first hole 261 and the second hole 511 are penetrated by a second bolt 52, and locked by a second nut 53. In this embodiment, a second lifting ear seat 54 is connected between the second lifting ear 51 and the connecting beam 3, and the second lifting ear seat 54 is detachably connected to the connecting beam 3, and the second lifting ear 51 is detachably connected to the second lifting ear seat 54. The second lifting ear seat 54 can make the connection between the second lifting ear 51 and the connecting beam 3 more stable. There are two first lifting ears 26. When the first lifting ear 26 and the second lifting ear 51 are connected, the second lifting ear 51 is placed between the two first lifting ears 26 to make the connection more stable. The second nut 53 is a butterfly nut. The butterfly nut will not loosen under vibration or dynamic load, thereby improving the reliability of the connection. The butterfly nut can also be conveniently rotated and disassembled manually when disassembly is required.

Furthermore, in order to protect the aircraft wall panel, the clamping assembly 2 further includes a first flexible member 23 and a second flexible member 24. The first flexible member 23 is disposed in the placement groove and connected to the side of the pressure plate 22, and the second flexible member 24 is disposed in the placement groove and connected to the surface of the base 21. The first flexible member 23 and the second flexible member 24 are used to accommodate the ear piece 200. The first flexible member 23 and the second flexible member 24 are disposed so that after the clamping assembly 2 is locked with the ear piece 200, the wall panel body 100 is not worn at the position where the clamping assembly 2 contacts the wall panel body 100. The first flexible member 23 and the second flexible member 24 can be made of rubber or other materials.

Furthermore, in order to protect the forming mold of the aircraft wall panel, a third flexible member 25 is provided on the side of the base 21 away from the pressure plate 22, and the third flexible member 25 is used to contact the forming mold of the aircraft wall panel. Since the bottom surface of the base 21 will contact the forming mold of the aircraft wall panel after the clamping assembly 2 is locked with the ear piece 200, the provision of the third flexible member 25 plays a role in protecting the forming mold of the aircraft wall panel from wear and tear, which is conducive to extending the service life of the forming mold. In this embodiment, the third flexible member 25 is provided with an observation hole along the axial direction of the locking member 27, so that the operator can check the degree of screw connection between the locking member 27 and the base 21. The third flexible member 25 can be made of rubber or other materials.

When the tooling for demoulding the aircraft panel provided by the specific embodiment of the utility model is used, two toolings are required after assembling the frame 1, the connecting beam 3 and the clamping assembly 2. The two toolings act on the two ends of the aircraft panel to be demoulded along the length direction respectively, and the frame 1 is connected to the lifting device. The lifting device drives the frame 1 to move upward, thereby driving the aircraft panel as a whole to move upward through the ear piece 200, so that the aircraft panel is separated from the molding mold of the aircraft panel, and the demoulding work of the aircraft panel is completed. After demoulding, the ear piece 200 is cut off by water jet cutting to obtain the aircraft panel product.

Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation methods of the present invention. For ordinary technicians in the relevant field, various obvious changes, readjustments and substitutions can be made without departing from the protection scope of the present invention. It is not necessary and impossible to list all implementation methods here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims (10)

1. A tool for demoulding an aircraft panel, used for demoulding an aircraft panel, the aircraft panel comprising a panel body (100) and an ear piece (200) integrally formed with the panel body (100), the ear piece (200) extending outward along the side of the panel body (100), characterized in that the tool for demoulding an aircraft panel comprises: A frame (1), the frame (1) being used for connecting to a lifting device; A connecting beam (3), at least one connecting beam (3) is provided, each connecting beam (3) is detachably connected to the frame (1), the connecting beam (3) is arranged below the frame (1), and the distance between the connecting beam (3) and the frame (1) is adjustable; A clamping assembly (2), the clamping assembly (2) being detachably connected to the connecting beam (3), the two ends of each connecting beam (3) being respectively provided with the clamping assembly (2), the clamping assembly (2) being used to fix the ear piece (200). 2. The tooling for demoulding aircraft wall panels according to claim 1 is characterized in that the frame (1) comprises two cross beams (11) and at least one longitudinal beam (12), the two cross beams (11) are parallel and spaced apart, the longitudinal beam (12) is arranged between the two cross beams (11), the two ends of the longitudinal beam (12) are respectively connected to the two cross beams (11), the two ends of the connecting beam (3) are detachably connected to the two cross beams (11), and the connecting beam (3) and the longitudinal beam (12) are arranged in parallel. 3. The tooling for demoulding aircraft wall panels according to claim 2 is characterized in that a connecting rod (4) is provided between each of the cross beams (11) and the connecting beams (3), one end of the connecting rod (4) is detachably connected to the cross beam (11), and the other end of the connecting rod (4) is detachably connected to the connecting beam (3). 4. The tooling for demoulding aircraft wall panels according to claim 3 is characterized in that a fourth lifting ear seat (81) is detachably connected to the cross beam (11), a fourth lifting ear seat (81) is connected to a fourth lifting ear (8), a first bolt is passed through two lifting ear holes of the fourth lifting ear (8), the first bolt is provided with a hole for the connecting rod (4) to pass through along an axial direction perpendicular to the first bolt, and the connecting rod (4) is threadedly connected to the first bolt. 5. The tooling for demoulding aircraft wall panels according to claim 1 is characterized in that the clamping assembly (2) includes a base (21), a pressure plate (22) and a locking piece (27), one side of the pressure plate (22) is detachably connected to the connecting beam (3), the base (21) is an L-shaped structure, the other side of the pressure plate (22) is detachably connected to one end of the base (21), and the pressure plate (22) and the base (21) are surrounded by a placement groove, the placement groove is used to plug in the ear piece (200), and the locking piece (27) can be penetrated and fixed to the ear piece (200). 6. The tooling for demoulding aircraft wall panels according to claim 5 is characterized in that the clamping assembly (2) also includes a first flexible member (23) and a second flexible member (24), the first flexible member (23) is arranged in the placement groove and connected to the side of the pressure plate (22), the second flexible member (24) is arranged in the placement groove and connected to the surface of the base (21), and the first flexible member (23) and the second flexible member (24) are used to accommodate the ear piece (200). 7. The tooling for demoulding aircraft wall panels according to any one of claims 5-6 is characterized in that a third flexible member (25) is provided on the side of the base (21) facing away from the pressure plate (22), and the third flexible member (25) is used to contact the forming mold of the aircraft wall panel. 8. The tooling for demoulding aircraft wall panels according to claim 5 is characterized in that the pressure plate (22) is provided with a first lifting ear (26), the first lifting ear (26) is provided with a first hole (261), the connecting beam (3) is detachably connected with a second lifting ear (51), the second lifting ear (51) is provided with a second hole (511), the first hole (261) and the second hole (511) are penetrated by a second bolt (52), and are locked by a second nut (53). 9. The tooling for demoulding aircraft wall panels according to claim 5 is characterized in that the locking member (27) comprises a locking bolt, one end of which passes through the pressure plate (22) and the ear piece (200) in sequence and is threadedly connected to the base (21). 10. The tooling for demoulding aircraft panels according to claim 5, characterized in that two locking members (27) are spaced apart on the pressure plate (22) along a direction perpendicular to the extension of the connecting beam (3).