CN113103477A

CN113103477A - Large aircraft fuselage forming die

Info

Publication number: CN113103477A
Application number: CN202110369282.2A
Authority: CN
Inventors: 艾勃帆; 邹湘伏; 谢向国; 赵轶; 周志东
Original assignee: Hunan Sunward Science & Technology Co ltd
Current assignee: Shanhe Xinghang Industrial Co ltd
Priority date: 2021-04-06
Filing date: 2021-04-06
Publication date: 2021-07-13
Anticipated expiration: 2041-04-06
Also published as: CN113103477B

Abstract

The invention discloses a large-scale aircraft fuselage forming mold, which comprises a mold cavity, a mold base, an insert and a side mold. The mold cavity includes a first mold cavity and a second mold cavity, the mold base includes a first mold base and a second mold base, the first mold base is fixedly connected with the first mold cavity, and the second mold base is connected with the second mold cavity. For a fixed connection, the insert block and the edge lap mold are fixed on the mold cavity through bolt connection, and a positioning device and a gap adjustment device are installed on the mold frame. The invention not only solves the problem that the aircraft fuselage product is complicated in structure and difficult to demould, but also increases the strength of the fuselage through the detachable insert block and the side mold. The adjustment device is designed on the mold base, which overcomes the disadvantage of low precision of the mold. At the same time, the mold base is equipped with a positioning device and a reversible device to ensure the convenience and accuracy of the mold clamping of the large aircraft fuselage. The large-scale aircraft fuselage forming mold of the present invention can realize the paving of the left and right fuselage of the product, and also realize the clamping and bonding of the left and right fuselage.

Description

Large aircraft fuselage forming die

Technical Field

The invention relates to the technical field of forming dies, in particular to a forming die for a large airplane body.

Background

In recent years, carbon fiber composite materials have been widely used because of their advantage of extremely high specific strength, and particularly in the direction of lightweight design and the aerospace industry, carbon fiber materials can significantly reduce the weight of an aircraft fuselage while maintaining the strength of the aircraft fuselage. However, because of the large volume of the airplane fuselage, there is a technical bottleneck in laying large-scale carbon fiber composite products when the fuselage is manufactured by molding carbon fiber composite materials. The method mainly comprises the following steps: the size of a forming mold is large, the deformation of the mold is large, the mold closing precision is not high, and the phenomenon of mold closing dislocation exists; and secondly, the secondary paving and pasting mode is adopted for edge lapping treatment, so that the edge lapping is not attractive, and the edge lapping strength is not reliable. Aiming at the problem of product quality reduction caused by the forming die, the invention adopts a special lapping mode and a deformation adjusting mode, and overcomes the defects of low precision, difficult adjustment, rough lapping and the like of a large die. The precision of the large-scale carbon fiber composite material die is ensured, and the strength and the attractiveness of the large-scale carbon fiber composite material product are improved.

Disclosure of Invention

The invention aims to solve the technical problems that the existing large-scale carbon fiber composite material product is difficult to mold, low in precision and unsatisfactory in structural strength, and provides a large-scale airplane body molding mold which is simple to operate, high in efficiency, high in precision of the produced product and good in structural strength.

The purpose of the invention is realized by the following technical scheme:

a large-scale aircraft fuselage forming die comprises a die cavity, a die carrier, an insert block and a scrap edge die; the mould cavity comprises a first cavity and a second cavity, the mould frame comprises a first mould frame and a second mould frame, the first mould frame is fixedly connected with the first cavity, the second mould frame is fixedly connected with the second cavity, and the mould frame is provided with a positioning device and a gap adjusting device. The mould cavity is provided with an insert communicated with the cavity, and the lap mold is arranged on the parting surface of the first cavity and/or the second cavity. According to the invention, through the die carrier which can be positioned, turned and adjusted in gap and the detachable insert block, the accurate butt joint position of the first cavity and the second cavity is ensured during die assembly, the problem that the product is complex in structure and difficult to demould is solved, and the strength of the product is increased. Meanwhile, the lap is integrated into the product, and the product laid and pasted has better integrity, higher strength and more attractive appearance.

Furthermore, the insert block is fixed on the outer surface of the cavity of the first cavity or the second cavity, and demolding of the product with the negative angle is completed by the aid of the insert block.

Further, the scrap (bridge) die comprises an abdomen scrap (bridge) die and a vertical tail scrap (bridge) die, the abdomen scrap (bridge) die is arranged on the die parting surfaces of the first cavity and the second cavity, the upper half and the lower half of the scrap (bridge) needed by die assembly and the product are paved together on the die parting surface of the first cavity or the second cavity of the vertical tail scrap (bridge) die cavity, and the paved product has better integrity, high strength and more attractive appearance.

Furthermore, the positioning device comprises a positioning sleeve and a positioning pin, the positioning sleeve and the positioning pin are respectively fixed on the first die carrier and the second die carrier, and the accurate butt joint position of the first cavity and the second cavity is ensured during die assembly.

Furthermore, four or more than four positioning devices are arranged on the die carrier.

Further, the clearance adjusting device comprises a die base plate, an adjusting screw rod, a nut, a pressing rod and an adjusting device, the die base plate is fixed on the die frame, the adjusting screw rod is fixed on the die base plate, the adjusting device is sleeved with the adjusting screw rod through the nut, the pressing rod is connected with the adjusting device, and the pressing rod is connected with the die cavity. When the die is closed, a large gap exists between the first cavity die surface and the second cavity die surface. The adjusting screw rod of the first cavity can be pushed downwards or the adjusting screw rod of the second cavity can be pushed upwards by rotating the nut, so that the purpose of eliminating local gaps is achieved.

Furthermore, the first die carrier and the second die carrier are formed by welding sectional materials, and the second cavity and the first cavity are respectively fixed through composite materials and resin.

Furthermore, the die carrier is also provided with a movable wheel.

Furthermore, a turnover device is arranged between the first die carrier and the second die carrier.

Compared with the prior art, the beneficial effects are:

according to the invention, through the detachable embedded block, the problem that the product is complex in structure and difficult to demould is solved, and the thought and the use function of product design are widened. Meanwhile, the lap is integrated into the product, and the product laid and pasted has better integrity, higher strength and more attractive appearance. In addition, the adjusting device is designed on the die frame, the defect that the precision of the large-scale die is not high is overcome, and the die frame is provided with the positioning device and the turnover device, so that the convenience and the accuracy of the die assembly of the large-scale composite material die are ensured. The large airplane body forming die can realize the independent paving and adhering of the left and right bodies of a product and can also realize the die assembly and adhering of the left and right bodies.

Drawings

FIG. 1 is a schematic view of a lower cavity configuration;

FIG. 2 is a schematic view of a lower cavity and its scrap form construction;

FIG. 3 is a schematic view of a mold structure;

FIG. 4 is a schematic view of a gap-setting device;

fig. 5 is a schematic structural diagram of the positioning device.

1 lower die cavity, 2 abaculus, 3 belly overlap edge moulds, 4 vertical fin overlap edge moulds, 5 removal wheels, 6 clearance adjusting device, 7 rotary device, 8 positioner, 9 lower die carriers, 10 upper die carriers, 11 mould backing plates, 12 adjusting screw, 13 nuts, 14 compression bar, 15 adjusting device, 16 position sleeve, 17 locating pins.

Detailed Description

The following examples are further explained and illustrated, but the present invention is not limited in any way by the specific examples. Unless otherwise indicated, the methods and equipment used in the examples are conventional in the art and all materials used are conventional commercially available materials.

Example 1

As shown in the figure, the carbon fiber composite material airplane fuselage paving and die assembly forming die comprises a die cavity, a die frame, an insert block 2 and a flanging die. The mould die cavity includes die cavity and lower die cavity 1, and the die carrier includes die carrier 10 and lower die carrier 9, goes up die carrier 10 and lower die carrier 9 and is formed by the section bar welding, goes up die carrier 10 and last die cavity fixed connection, lower die carrier 9 and lower die cavity 1 fixed connection, abaculus 2 is the aluminum alloy material, passes through the bolt from the die carrier outside and is connected with lower die cavity 1. The scrap (bridge) formwork comprises an abdomen scrap (bridge) formwork 3 and a vertical tail scrap (bridge) formwork 4, wherein the abdomen scrap (bridge) formwork 3 is fixed on the parting surfaces of the upper cavity and the lower cavity 1 through bolt connection, and the vertical tail scrap (bridge) formwork 4 is fixed on the parting surface of the lower cavity 1 through bolt connection.

Four positioning pins 17 are uniformly arranged on the upper die frame 10, and a positioning sleeve 16 correspondingly matched with the positioning pins 17 is fixed on the lower die frame 9. The clearance adjusting device comprises a die base plate 11, an adjusting screw 12, a nut 13, a pressing rod 14 and an adjusting device 15, the upper die frame 10 is fixed with the die base plate 11, the adjusting screw 12 is fixed on the die base plate 11, the adjusting device 15 is sleeved with the adjusting screw 12 through the nut 13, the pressing rod 14 is connected with the adjusting device 15, and the pressing rod 14 is connected to the outer surface close to a die cavity.

Example 2

A carbon fiber composite material airplane body paving and die assembly forming die comprises a die cavity, a die frame, an insert block 2 and a flanging die. The mould die cavity includes die cavity and lower die cavity 1, and the die carrier includes die carrier 10 and lower die carrier 9, goes up die carrier 10 and lower die carrier 9 and is formed by the section bar welding, goes up die carrier 10 and last die cavity fixed connection, lower die carrier 9 and lower die cavity 1 fixed connection, abaculus 2 is the aluminum alloy material, is connected it with the die cavity in the 1 outside of die cavity down through the bolt fastening. Before demoulding, the bolts of the insert blocks on the upper die frame are completely dismounted, the upper die frame is lifted by using a lifting device, the upper die frame is separated from the lower die frame, and the insert blocks of the upper die frame are still left on the lower die frame. Then the bolts of the embedded blocks on the lower die frame are all disassembled, and the demoulding of the machine body can be completed at the moment. This is the "stripping" of the negative angle product by the insert.

The scrap (bridge) formwork comprises an abdomen scrap (bridge) formwork 3 and a vertical tail scrap (bridge) formwork 4, wherein the abdomen scrap (bridge) formwork 3 is fixed on the parting surfaces of the upper cavity and the lower cavity 1 through bolt connection, and the vertical tail scrap (bridge) formwork 4 of the vertical tail scrap (bridge) formwork 4 is fixed on the parting surface of the lower cavity 1 through bolt connection. The abdomen side overlapping die 3 and the vertical tail side overlapping die 4 are also formed by paving and pasting composite materials, wherein the abdomen side overlapping die 3 is required to be installed when the upper half product and the lower half product are paved and pasted. And the vertical tail side lapping die 4 is only installed when the lower half product is paved. The abdomen side lapping die 3 and the vertical tail side lapping die 4 creatively integrate the lapping required by die assembly on a product, and do not need to be paved separately in the die assembly process. After the upper half product and the lower half product are matched, the lap is bonded by using the structural adhesive to complete the 'matching' of the product. The lap is integrated into the product, and the product laid out is better in integrity, higher in strength and more attractive.

Four positioning pins 17 are uniformly arranged on the upper die frame 10, and a positioning sleeve 16 correspondingly matched with the positioning pins 17 is fixed on the lower die frame 9. The clearance adjusting device comprises a die base plate 11, an adjusting screw 12, a nut 13, a pressing rod 14 and an adjusting device 15, the die base plate 11 and the pressing rod 14 are respectively fixed on the upper die frame 10 and the lower die frame 9, the adjusting screw 12 is fixed on the die base plate 11, the adjusting device 15 is sleeved with the adjusting screw 12 through the nut 13, and the pressing rod 14 is connected with the adjusting device 15.

The bottom of the lower die frame is provided with a movable wheel 5, and the upper part of the lower die frame 9 and one side of the bottom of the upper die frame 10 are provided with a turnover device.

It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A large-scale aircraft fuselage forming die is characterized by comprising a die cavity, a die carrier, an insert block and a scrap edge die; the mould cavity comprises a first cavity and a second cavity, the mould frame comprises a first mould frame and a second mould frame, the first mould frame is fixedly connected with the first cavity, the second mould frame is fixedly connected with the second cavity, and the mould frame is provided with a positioning device and a gap adjusting device; the mould cavity is provided with an insert communicated with the cavity, and the lap mold is arranged on the parting surface of the first cavity and/or the second cavity.

2. The large aircraft fuselage forming mold of claim 1, wherein the insert is fixed to the outer surface of the first cavity or the second cavity.

3. The large aircraft fuselage forming die of claim 1, wherein the overlap dies comprise an abdominal overlap die and a vertical fin overlap die, the abdominal overlap die is arranged on the parting surfaces of the first cavity and the second cavity, and the vertical fin overlap die is arranged on the parting surfaces of the first cavity or the second cavity.

4. The large aircraft fuselage forming die of claim 3, wherein the belly and vertical fin flanging dies are detachably connected with the die cavity by bolts.

5. The large aircraft fuselage forming die of claim 1, wherein the positioning device comprises a positioning sleeve and a positioning pin, and the positioning sleeve and the positioning pin are respectively fixed on the first die carrier and the second die carrier.

6. The large aircraft fuselage forming die of claim 1, wherein four or more than four positioning devices are arranged on the die frame.

7. The large aircraft fuselage forming die of claim 1, wherein the gap adjusting device comprises a die backing plate, an adjusting screw, a nut, a pressing rod and an adjusting device, the die backing plate is fixed on the die frame, the adjusting screw is fixed on the die backing plate, the adjusting device is sleeved with the adjusting screw through the nut, the pressing rod is connected with the adjusting device, and the pressing rod is connected with the die cavity.

8. The large aircraft fuselage forming die of claim 1, wherein the first die carrier and the second die carrier are formed by welding sectional materials, and the second cavity and the first cavity are respectively fixed by composite materials and resin.

9. The large aircraft fuselage forming die of claim 1, wherein the die carrier is further provided with moving wheels.

10. The large aircraft fuselage forming die of claim 1, wherein a turning device is further arranged between the first die carrier and the second die carrier.