CN203427250U

CN203427250U - Combined mold for molding aircraft with steps on inner wall of shell

Info

Publication number: CN203427250U
Application number: CN201320428366.XU
Authority: CN
Inventors: 刘巧练
Original assignee: Individual
Current assignee: Metal Aluminium Technology Co ltd
Priority date: 2013-07-18
Filing date: 2013-07-18
Publication date: 2014-02-12
Anticipated expiration: 2023-07-18

Abstract

The utility model discloses a combined mold for molding an aircraft with steps on an inner wall of a shell. The combined mold comprises a set of aircraft molding mold, a set of silica gel liner manufacturing mold and a silica gel liner molded by casting the silica gel liner manufacturing mold, wherein the outline dimension of the silica gel liner is inwards recessed relative to the outline dimension of a product molded by the aircraft molding mold; the aircraft molding mold is a steel mold; the silica gel liner manufacturing mold is an aluminum mold. The combined mold is used for molding production of the aircraft with steps on the inner wall of the shell and has the advantages of high production efficiency, high intensity of the molded product, attractive appearance, accurate finishing size and the like.

Description

The assembling die that has the aircraft moulding of step for outer casing inner wall

Technical field

The utility model belongs to carbon fibre composite aircraft field shaping technique, is specifically related to a kind of assembling die that has the aircraft moulding of step for outer casing inner wall.

Background technology

Conventional wall thickness is even, the wheel chair access carbon fibre composite aircraft of inwall generally can be by compression molding or nylon airbag air-pressure forming technological forming.Die press technology for forming utilizes forming furnace table to mould pressurizing, heating, and pressurize to product to be formed by mould, heating realizes the moulding of product, it comprises drawing confirmation, Design of Dies and manufacture, get the raw materials ready, cut out yarn, the pre-type of coiled strip, moulding, deburring processing of cutting, gummed, mend the procedure of processings such as soil and application, yet this die press technology for forming is not suitable for producing and does not wait wall thickness and product very light in weight, utilizing this die press technology for forming to produce outer casing inner wall has its Design of Dies of carbon fibre composite aircraft of step complicated, cost is high, even exist and cannot produce the possibility that above-mentioned outer casing inner wall has the carbon fibre composite aircraft of step.Another moulding process is that nylon airbag air-pressure forming technology utilization forming furnace table is to mould pressurizing, heating, gases at high pressure are entered nylon airbag and from product cavity, product are exerted pressure by valve, forming furnace table heats mould simultaneously, realize formed product, its procedure of processing and die press technology for forming are basically identical, itself and die press technology for forming difference mainly increase and wear airduct step in the pre-type of the coiled strip stage, be about to airduct and put in advance product cavity, yet above-mentioned nylon airbag air-pressure forming technique also cannot be produced the carbon fibre composite aircraft that outer casing inner wall has step, it is this carry-on motor fixed head gummed step as shown in Figure 2 that above-mentioned outer casing inner wall has its stepped form of carbon fibre composite aircraft of step, comprise motor fixed head plate body 1 and step 10.

For solving above-mentioned existing two kinds of moulding process, cannot produce outer casing inner wall with the technical problem of the carbon fibre composite aircraft of step as shown in Figure 2, I have proposed a solution can realize the moulding production that above-mentioned outer casing inner wall has the carbon fibre composite aircraft of step when guaranteeing shaped article intensity, machining accuracy and production efficiency, and is to coordinate above-mentioned technique to research and develop in person as shown in Figure 1 a kind of assembling die that has the aircraft moulding of step for outer casing inner wall accordingly.

Summary of the invention

For the deficiencies in the prior art, the utility model aims to provide a kind of assembling die that has the aircraft moulding of step for outer casing inner wall.

For achieving the above object, the utility model adopts following technical scheme:

The assembling die that has the aircraft moulding of step for outer casing inner wall, comprise a set of aircraft shaping mould, a set of silica gel inner container making mould and utilize this silica gel inner container to make mould and record the silica gel inner container of moulding, the relative aircraft shaping mould of this silica gel inner container appearance and size shaped article appearance and size inside contracts; Described silica gel inner container profile inside contracts and is of a size of 3 times of aircraft wall thickness, and silica gel inner container thickness is 3-5mm.

Preferably, described aircraft shaping mould is punching block, and it is aluminum dipping form that silica gel inner container is made mould.

The utlity model has following beneficial effect:

The utility model has the assembling die of the aircraft moulding of step for outer casing inner wall, utilize the pressure of silica gel inner container expanded by heating that product is compressing, die sinking after mold cools down, the silica gel inner container contraction size decreases of catching a cold, can take out very easily, the outer casing inner wall that coordinates me to propose has the carbon fibre composite aircraft production technology of step, can produce the outer casing inner wall of stepped form as shown in Figure 2 has the carbon fibre composite aircraft finished product of step, has that production efficiency is high, shaped article intensity is high and the advantage such as good appearance, processing dimension be accurate.

Accompanying drawing explanation

Fig. 1 is the carbon fibre composite aircraft production technological process that outer casing inner wall has step;

Fig. 2 is its motor glued board gummed step schematic diagram of carbon fibre composite aircraft that outer casing inner wall to be processed has step;

Fig. 3 is the utility model structural representation.

The specific embodiment

Below in conjunction with drawings and the specific embodiments, the utility model will be further described, understands the claimed technological thought of the utility model so that clearer.

The outer casing inner wall of my research and development has the carbon fibre composite aircraft production technology of step, comprise as shown in Figure 1 that drawing is confirmed, design silica gel inner container, Design of Dies and manufacture, record silica gel inner container, get the raw materials ready, cut out yarn, coiled strip moulding, moulding, deburring processing of cutting, gummed, benefit soil and coating process step, concrete technology step is as follows:

Step 1, drawing is confirmed, according to product figure, carries out industrial analysis, whether assessment each position of product figure is applicable to explained hereafter, as fillet, size etc., if there is improper explained hereafter position to revise product figure;

Step 2, design silica gel inner container 2, as shown in Figure 3, confirm after drawing monolateral inside contracting on the said goods figure overall dimensions basis, inside contract size depending on product thickness, monolateral the inside contracting of silica gel inner container 2 is of a size of 3 times of aircraft wall thickness to be processed particularly, determines silica gel inner container 2 thickness after reserving silica gel inner container 2 appearance and sizes, these silica gel inner container 2 thickness requirements are even, and thickness is 3-5mm;

Step 3, Design of Dies and manufacture, manufacture respectively an aircraft shaping mould 3 and a silica gel inner container making mould (not shown), this aircraft shaping mould 3 is punching block, it is aluminum dipping form that silica gel inner container is made mould, and on above-mentioned aircraft shaping mould 3, need to design locked mode screw, silica gel inner container 2 bulbs of pressure are by aircraft spalling to be formed when avoiding mold cools down;

Step 4, record silica gel inner container 2, by the silica gel inner container of step 2 design 2 estimation silica gel inner container 2 weight, take in proportion two ingredient liquids silica gel, be placed in Plastic Drum, this Plastic Drum size be take can just put vacuum tank into as good, stir, the Plastic Drum that liquid silica gel is housed is put into vacuum tank and vacuumize 18-22 minute, pay close attention at any time silica gel situation in Plastic Drum, until silica gel, everywhere exit during Plastic Drum, and pour the silica gel of liquid in step 3 silica gel inner container and make in the die cavity of mould, allow silica gel spontaneous curing 220-260 minute, after silica gel solidifies, silica gel inner container 2 is made mould and taken out from silica gel inner container,

Step 5, gets the raw materials ready, and according to the regulation of aircraft product standard book, prepares moulding and produces required material;

Step 6, cuts out yarn, and the structure chart issuing according to engineer is cut into carbon yarn the specification needing;

Step 7, the pre-type of coiled strip is recorded the preservative film that the resistance to 180 ℃ of high temperature of one deck are wrapped up on silica gel inner container 2 surfaces that obtain in step 4, and the structure chart then issuing according to engineer in step 6 rolls shape and the thickness of aircraft in advance, and tests; Step 8, moulding, puts into product rolled in step 7 the die cavity of aircraft shaping mould 3, and cover mold is also delivered to mould on the hot-platen stove plate of forming furnace table and is heated, and concrete tool parameters is set as: oil pressure 100kg/cm ², temperature 145-155 ℃ continues hot briquetting 15 minutes after product temperature in mould reaches 150 ℃, then aircraft shaping mould 3 is delivered to cooling table cooling, and die sinking is also taken out moulding aircraft;

Step 9, deburring processing of cutting, by type outer casing inner wall have step the deburring of carbon fibre composite aircraft, cut into needed size;

Step 10, gummed, by adhesive by aircraft, other cannot be adhesive in aircraft body by integrated parts;

Step 11, mends soil, the aircraft surface in step 10 is carried out to grinding process, so that aircraft outward appearance is clean and tidy;

Step 12, application, carries out baking vanish and the processing such as label by customer requirement to aircraft surface.

The utility model has the carbon fibre composite aircraft production technology of step for above-mentioned outer casing inner wall, concrete occupation mode is as follows: before die sinking, on the basis of product figure size, inside contract, design a silica gel inner container 2, in the time of die sinking, open two sleeve forming moulds: a set of is aircraft shaping mould 3, a set of is that silica gel inner container is made mould (not shown); During moulding, utilize the pressure of silica gel inner container 2 expanded by heating that product is compressing, die sinking after mold cools down, the silica gel inner container 2 contraction size decreases of catching a cold, can take out very easily, thereby reach, produces the object of formal product as shown in Figure 2.

For a person skilled in the art, can make other various corresponding changes and distortion according to technical scheme described above and design, and these all changes and distortion all should belong to the protection domain of the utility model claim within.

Claims

1. for outer casing inner wall, there is the assembling die of the aircraft moulding of step, it is characterized in that: comprise a set of aircraft shaping mould (3), a set of silica gel inner container making mould and utilize this silica gel inner container to make mould and record the silica gel inner container (2) of moulding, the relative aircraft shaping mould of this silica gel inner container (2) appearance and size (3) shaped article appearance and size inside contracts; Described silica gel inner container (2) profile inside contracts and is of a size of 3 times of aircraft wall thickness, and silica gel inner container (2) thickness is 3-5mm.

2. the assembling die that has the aircraft moulding of step for outer casing inner wall as claimed in claim 1, is characterized in that: described aircraft shaping mould (3) is punching block, and it is aluminum dipping form that silica gel inner container is made mould.