CN217454997U

CN217454997U - Large-scale wrapping type composite material vacuum forming device for aircraft nose

Info

Publication number: CN217454997U
Application number: CN202220909817.0U
Authority: CN
Inventors: 蔡锡荣; 赵志林; 杨杰; 周立伟
Original assignee: Zhejiang Huarong Aviation Equipment Co ltd
Current assignee: Zhejiang Huarong Aviation Equipment Co ltd
Priority date: 2022-04-18
Filing date: 2022-04-18
Publication date: 2022-09-20
Anticipated expiration: 2032-04-18

Abstract

The utility model belongs to the technical field of the aircraft combined material takes shape, especially, relate to a large-scale formula combined material vacuum forming device that wraps up outward of aircraft nose. Including the forming processing base, a plurality of ventilation hole has been seted up on the forming processing base, be provided with on the forming processing base and be used for processing the die cavity, the side of forming processing base is provided with the accent fortune couple that is used for hoist and mount, mounting groove has been seted up to the inside of forming processing base, the below of processing die cavity is provided with supporting baseplate, supporting baseplate sets up in the mounting groove. The utility model discloses a be provided with supporting baseplate in the outside of processing die cavity, through the buffering connecting block and the buffering inserted bar that set up between supporting baseplate and processing die cavity, and then make the processing die cavity can obtain the buffering under buffer spring's deformation when deformation takes place in processing to can also guarantee the normal use of processing die cavity when carrying out the support to the processing die cavity.

Description

Large-scale wrapping type composite material vacuum forming device for aircraft nose

Technical Field

The utility model belongs to the technical field of the shaping of aircraft combined material, a large-scale formula combined material vacuum forming device that wraps up outward of aircraft nose is related to.

Background

The composite material is a mixture. Plays a great role in many fields and replaces many traditional materials. The composite material is divided into a metal and metal composite material, a nonmetal and metal composite material and a nonmetal and nonmetal composite material according to the components. According to the structure characteristics, the utility model is divided into: a fiber-reinforced composite material. The fiber reinforced material is compounded with various kinds of fiber reinforced material inside matrix material. Such as fiber reinforced plastics, fiber reinforced metals, and the like. ② sandwich composite material. Is composed of surface material and core material. The face stock is generally high in strength and thin; the core material is light in weight and low in strength, but has certain rigidity and thickness. The sandwich structure is divided into a solid sandwich layer and a honeycomb sandwich layer. ③ fine particle composite materials. The hard fine particles are uniformly distributed in the matrix, such as dispersion strengthening alloy, metal ceramic and the like. And fourthly, mixing the composite material. Is formed by mixing two or more than two reinforcing phase materials in a matrix phase material. Compared with the common single reinforced phase composite material, the impact strength, the fatigue strength and the fracture toughness of the composite material are obviously improved, and the composite material has special thermal expansion performance. The composite material is divided into intralayer hybrid, interlaminar hybrid, sandwich hybrid, intralayer/interlaminar hybrid and super hybrid composite.

Often can adopt high strength combined material to carry out the formula of wrapping up outward to aircraft nose position and cover the setting in aircraft nose processing production of aircraft, and when carrying out vacuum process shaping to the large-scale formula combined material that wraps up in aircraft nose, the forming die who all needs to use corresponding shape carries out the components of a whole that can function independently processing, current machine-shaping mould often carries out the support between the mould through the support frame, but when using the support frame to support, because the support bottom is the stereoplasm material, when the inside combined material of processing die cavity carries out the shaping and takes place deformation, can take place certain shrinkage and rise, and the support frame of stereoplasm will take place certain conflict to the mould when the material shrinks and rises, thereby probably lead to the impaired of mould, be not conform to user's user demand.

Disclosure of Invention

The utility model aims at the above-mentioned problem, a large-scale formula combined material vacuum forming device that wraps up outward of aircraft nose is provided.

In order to achieve the above purpose, the utility model adopts the following technical proposal:

the utility model provides a large-scale outer formula combined material vacuum forming device that wraps up in of aircraft nose, includes the shaping processing base, a plurality of ventilation hole has been seted up on the shaping processing base, be provided with on the shaping processing base and be used for processing the die cavity, the side of shaping processing base is provided with the transfer couple that is used for the hoist and mount, mounting groove has been seted up to the inside of shaping processing base, the below of processing the die cavity is provided with supporting baseplate, supporting baseplate sets up in the mounting groove, it is right to be provided with in the mounting groove be used for the supporting baseplate carries out the side bracing piece that supports, supporting baseplate's bottom is provided with the bottom sprag piece, the bottom sprag piece with the mounting groove inner wall links to each other.

In the large-scale wrapping type composite material vacuum forming device for the aircraft nose, the top ends of the left side and the right side of the forming processing base are both provided with side screw holes, and fixing screws are inserted into the side screw holes in a rotating mode.

In the large-scale externally-wrapped composite material vacuum forming device for the aircraft nose, the end part of the fixing screw is rotatably provided with the touch plate, and the side edge of the touch plate is provided with the fixing pad.

In the large-sized externally-wrapped composite material vacuum forming device for the aircraft nose, the fixing pad is abutted against the surface of the supporting base plate, and a top end fixing bolt for fixing the supporting base plate and the forming base plate is arranged at the top end of the forming base.

In the large-scale externally-wrapped composite material vacuum forming device for the aircraft nose, the buffer connecting block is arranged above the supporting bottom plate and is abutted against the bottom side of the processing cavity.

In the large-scale externally-wrapped composite material vacuum forming device for the aircraft nose, the bottom end of the buffer connecting block is provided with the buffer inserting block, and the bottom end of the buffer inserting block is provided with the buffer slot.

In the large-scale externally-wrapped composite material vacuum forming device for the aircraft nose, the top side of the supporting base plate is provided with a plurality of buffer insertion rods, and the top ends of the buffer insertion rods are provided with inner side grooves.

In the large-scale externally-wrapped composite material vacuum forming device for the aircraft nose, the inner side groove is inserted into the buffer slot, and the buffer spring is arranged on the inner side groove.

In the large-scale externally-wrapped composite material vacuum forming device for the aircraft nose, the buffer spring is connected with the inner wall of the buffer slot, and the bottom end of the inner wall of the buffer slot is provided with the side sliding block.

In the large-scale externally-wrapped composite material vacuum forming device for the aircraft nose, the side edge of the buffering insertion rod is provided with the side edge sliding groove, and the side edge sliding block is slidably inserted into the side edge sliding groove.

Compared with the prior art, the utility model has the advantages of:

1. the utility model discloses a be provided with supporting baseplate in the outside of processing die cavity, through the buffer connection piece and the buffering inserted bar that set up between supporting baseplate and processing die cavity, through the buffer spring who sets up between buffer connection piece and buffering inserted bar, it links to each other to carry out elasticity between die cavity and the supporting baseplate will process, and then make the processing die cavity can obtain the buffering under buffer spring's deformation when processing takes place to deform, thereby can also guarantee the normal use of processing die cavity when carrying out the support to the processing die cavity, it is impaired in the course of working to avoid processing the die cavity.

2. The utility model discloses a side at the shaping processing base is provided with clamping screw, and the user promotes through clamping screw that the side of touch panel and fixed bolster and supporting baseplate is inconsistent to carry out better fixing between supporting baseplate and the processing die cavity.

Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.

Drawings

Fig. 1 is an overall schematic view of the present invention.

Fig. 2 is a schematic side view of the present invention.

Fig. 3 is a schematic side view of the present invention.

Fig. 4 is an enlarged schematic view of the buffering connecting block in fig. 3 according to the present invention.

In the figure: the forming and processing device comprises a forming and processing base 1, a vent hole 2, a processing cavity 3, a transferring hook 4, an installation groove 5, a supporting bottom plate 6, a side supporting rod 7, a bottom end supporting block 8, a side screw hole 9, a fixing screw rod 10, a collision plate 11, a fixing pad 12, a top end fixing bolt 13, a buffering connecting block 14, a buffering inserting block 15, a buffering inserting groove 16, a buffering inserting rod 17, an inner side groove 18, a buffering spring 19, a side sliding block 20 and a side sliding groove 21.

Detailed Description

The present invention will be further explained with reference to the accompanying drawings.

As shown in fig. 1-4, the large-scale wrapping type composite material vacuum forming device for the aircraft nose comprises a forming base 1, wherein a plurality of vent holes 2 are formed in the forming base 1, a processing cavity 3 is formed in the forming base 1, and a transferring hook 4 for hoisting is arranged on the side edge of the forming base 1.

In the present embodiment, since the high-strength composite material is often used to cover the nose portion of the aircraft during the machining of the nose of the aircraft, the forming mold with the corresponding shape is required to perform the split machining when the large-sized composite material with the nose is vacuum-formed.

And current machine-shaping mould often carries out the support between the mould through the support frame, but when using the support frame to support, because the support bottom is the stereoplasm material, when processing 3 inside composite materials of die cavity take place deformations, can take place certain contracting and rise, and the support frame of stereoplasm will take place certain conflict to the mould when the material contracts and rises to probably lead to the impaired of mould, be not conform to user's user demand.

When specifically carrying out the processing operation, will process die cavity 3 setting fixed connection on the shaping processing base 1 usually, to the inside injection combined material of 3 of processing die cavity to the required aircraft nose shaping product is obtained in processing, and sets up ventilation hole 2 on the shaping processing base 1, can be favorable to the ventilation of shaping processing base 1 inside, makes the cooling efficiency of processing die cavity 3 higher, reduces the required cooling time of product shaping.

Referring to fig. 1 and 4, in the present embodiment, a mounting groove 5 is provided inside a forming base 1, a supporting bottom plate 6 is provided below a processing cavity 3, the supporting bottom plate 6 is provided in the mounting groove 5, a side supporting rod 7 for supporting the supporting bottom plate 6 is provided in the mounting groove 5, a bottom end supporting block 8 is provided at the bottom end of the supporting bottom plate 6, the bottom end supporting block 8 is connected with the inner wall of the mounting groove 5, and side screw holes 9 are provided at the top ends of the left side and the right side of the forming base 1.

The inside of side screw 9 rotates to insert and is equipped with clamping screw 10, and clamping screw 10's tip rotates and is provided with conflict board 11, and the side of conflict board 11 is provided with fixed bolster 12, and fixed bolster 12 is inconsistent with the surface of supporting baseplate 6, and the top of forming machining base 1 is provided with and is used for supporting baseplate 6 and forming machining base 1 fixed top fixing bolt 13.

In this embodiment, through improving the inside of the forming base 1, through being provided with the mounting groove 5 inside the forming base 1, the mounting groove 5 is internally provided with the supporting bottom plate 6 matched with the appearance of the processing cavity 3, and the processing cavity 3 is supported and abutted through the supporting bottom plate 6.

The left and right sides and the bottom of the supporting bottom plate 6 are supported by side supporting rods 7 and bottom supporting blocks 8 arranged inside the mounting groove 5, and fixing screws 10 arranged on the top of the sides of the forming processing base 1 are rotated for fixing the fixing screws 10 by rotation.

Make fixing screw 10 rotate in the inside of side screw 9 and remove to one side that is close to supporting baseplate 6, drive and set up conflict board 11 and the fixed bolster 12 of fixing screw 10 tip and conflict with supporting baseplate 6's the outside to make fixed bolster 12 contradict supporting baseplate 6's top side, better support mutually with the surface of processing die cavity 3, make processing die cavity 3 more stable when vacuum forming.

As shown in fig. 1 and 4, in the present embodiment, a buffer connecting block 14 is disposed above the supporting base plate 6, the buffer connecting block 14 abuts against the bottom side of the processing cavity 3, a buffer inserting block 15 is disposed at the bottom end of the buffer connecting block 14, and a buffer slot 16 is disposed at the bottom end of the buffer inserting block 15.

The top side of supporting baseplate 6 is provided with a plurality of buffering inserted bar 17, inboard recess 18 has been seted up on the top of buffering inserted bar 17, inboard recess 18 is inserted and is established in buffering slot 16, be provided with buffer spring 19 on the inboard recess 18, buffer spring 19 links to each other with buffering slot 16's inner wall, the bottom of buffering slot 16 inner wall is provided with side slider 20, the side of buffering inserted bar 17 is provided with side spout 21, side slider 20 slides and inserts and establish in side spout 21.

In the embodiment, in order to make the die change to some extent without being influenced by the supporting frame when the composite material is molded inside the processing cavity 3, the buffer connecting block 14 is arranged in the middle of the supporting bottom plate 6 and the processing cavity 3.

Be provided with buffering inserted block 15 in the bottom of buffering connecting block 14, insert through the buffering inserted bar 17 that sets up on supporting baseplate 6 and establish the inside buffering slot 16 of seting up of buffering inserted block 15 in, set up the buffer spring 19 that links to each other with buffering inserted block 15 elasticity on the top of buffering inserted bar 17 for buffering connecting block 14 is receiving when conflicting.

Can produce certain resilience force, and then the direct surface to processing die cavity 3 is contradicted, and buffer spring 19 takes place the resilience force of deformation and can also reset the deformation on processing die cavity 3 surface after the combined material cooling to better provide the holding power for processing die cavity 3 processing.

The utility model discloses a theory of operation is:

before the machine-shaping, through being provided with supporting baseplate 6 in the inside mounting groove 5 of shaping processing base 1, supporting baseplate 6 can support processing die cavity 3, supports supporting baseplate 6 bottom side through setting up at the inside side support pole 7 of mounting groove 5 and bottom end support piece 8 to make supporting baseplate 6 can have certain holding power and contradict processing die cavity 3 surface.

Also through the rotation to fixing screw 10 for fixing screw 10 promotes to collide the support to the top side of supporting baseplate 6 by touch panel 11 and fixed bolster 12, makes supporting baseplate 6 set up more stably in mounting groove 5 is inside.

In order to make supporting baseplate 6 take place can be better conflict when processing die cavity 3 man-hour, avoid excessively conflicting to produce the influence to the section bar of processing die cavity 3, be provided with buffering connecting block 14 through the middle part at supporting baseplate 6 and processing die cavity 3, be provided with buffering inserted block 15 in the bottom of buffering connecting block 14.

The buffer insertion rod 17 arranged on the supporting bottom plate 6 is inserted into a buffer slot 16 arranged in the buffer insertion block 15, and a buffer spring 19 elastically connected with the buffer insertion block 15 is arranged at the top end of the buffer insertion rod 17.

Make buffer connection piece 14 when receiving the conflict, can produce certain resilience force, and then the direct surface to processing die cavity 3 is contradicted, and buffer spring 19 takes place the resilience force of deformation and can also reset the deformation on processing die cavity 3 surface after the combined material cooling to better provide the holding power for processing die cavity 3 processing. So that the processing cavity 3 can be better protected.

The specific embodiments described herein are merely illustrative of the spirit of the invention. Various modifications, additions and substitutions for the specific embodiments described herein will be apparent to those skilled in the art without departing from the spirit of the invention.

Although the terms of the forming processing base 1, the vent hole 2, the processing cavity 3, the transferring hook 4, the mounting groove 5, the supporting bottom plate 6, the side supporting rod 7, the bottom supporting block 8, the side screw hole 9, the fixing screw 10, the interference plate 11, the fixing pad 12, the top fixing bolt 13, the buffer connecting block 14, the buffer inserting block 15, the buffer inserting slot 16, the buffer inserting rod 17, the inner side groove 18, the buffer spring 19, the side slider 20, the side sliding slot 21, etc. are used more frequently herein, the possibility of using other terms is not excluded. These terms are used merely to more conveniently describe and explain the nature of the present invention and should not be interpreted as imposing any additional limitations that are contrary to the spirit of the present invention.

Claims

1. A large-scale wrapping type composite material vacuum forming device for an aircraft nose comprises a forming processing base (1), wherein a plurality of vent holes (2) are formed in the forming processing base (1), and is characterized in that a processing cavity (3) is formed in the forming processing base (1), a transferring hook (4) for hoisting is arranged on the side edge of the forming processing base (1), an installation groove (5) is formed in the forming processing base (1), a supporting bottom plate (6) is arranged below the processing cavity (3), the supporting bottom plate (6) is arranged in the installation groove (5), a side supporting rod (7) for supporting the supporting bottom plate (6) is arranged in the installation groove (5), a bottom supporting block (8) is arranged at the bottom end of the supporting bottom plate (6), and the supporting block (8) is connected with the inner wall of the installation groove (5),

and a buffer connecting block (14) is arranged above the supporting bottom plate (6), and the buffer connecting block (14) is abutted to the bottom side of the processing cavity (3).

2. The vacuum forming device for the large-scale wrapped composite material of the aircraft nose of the aircraft as claimed in claim 1, wherein the top ends of the left and right sides of the forming processing base (1) are both provided with side screw holes (9), and fixing screws (10) are rotatably inserted into the side screw holes (9).

3. The aircraft nose large-scale wrapped composite vacuum forming device according to claim 2, characterized in that the end of the fixing screw (10) is rotatably provided with a contact plate (11), and the side of the contact plate (11) is provided with a fixing pad (12).

4. The aircraft nose large-scale wrapped composite vacuum forming device according to claim 3, characterized in that the fixing pads (12) are in contact with the surface of the support baseplate (6), and the top end of the forming base (1) is provided with a top end fixing bolt (13) for fixing the support baseplate (6) and the forming base (1).

5. The vacuum forming device for the large-scale externally wrapped composite material of the aircraft nose as claimed in claim 4, wherein a buffer insert block (15) is arranged at the bottom end of the buffer connecting block (14), and a buffer slot (16) is arranged at the bottom end of the buffer insert block (15).

6. The vacuum forming device for the large-scale wrapped composite material of the aircraft nose of claim 5, characterized in that a plurality of buffer insertion rods (17) are arranged on the top side of the supporting bottom plate (6), and the top ends of the buffer insertion rods (17) are provided with inner grooves (18).

7. The vacuum forming device for the large-scale wrapped composite material of the aircraft nose of claim 6, characterized in that the inner groove (18) is inserted into the buffer slot (16), and a buffer spring (19) is arranged on the inner groove (18).

8. The vacuum forming device for the large-scale wrapped composite material of the aircraft nose of claim 7, characterized in that the buffer spring (19) is connected with the inner wall of the buffer slot (16), and the bottom end of the inner wall of the buffer slot (16) is provided with a side slide block (20).

9. The vacuum forming device for the large-scale wrapped composite material of the aircraft nose of the claim 8 is characterized in that the side edge of the buffering inserted rod (17) is provided with a side edge sliding groove (21), and the side edge sliding block (20) is slidably inserted in the side edge sliding groove (21).