CN110682544A

CN110682544A - Gluing mold and gluing method for thin-wall composite material leading edge fairing

Info

Publication number: CN110682544A
Application number: CN201910948364.5A
Authority: CN
Inventors: 郭蕊娜; 高翔; 梅钦海; 黄红初; 李萍; 褚中华; 吴霞; 胡静; 尹萍; 刘晓雯
Original assignee: Jiangxi Hongdu Aviation Industry Group Co Ltd
Current assignee: Jiangxi Hongdu Aviation Industry Group Co Ltd
Priority date: 2019-10-08
Filing date: 2019-10-08
Publication date: 2020-01-14

Abstract

The invention provides a gluing mold and a gluing method for a thin-wall composite material front edge fairing, wherein the mold comprises an upper mold (1), a lower mold (2), a front edge stop block (3), a locking block (4) and a bolt (5), the upper mold (1), the lower mold (2) and the front edge stop block (3) enclose to form a cavity shape of an airfoil part, and the locking block (4) fixedly connects the front edge stop block (3), the upper mold (1) and the lower mold (2) together through the bolt (5). By using the mould, the airfoil-shaped parts are glued step by step, and a drying oven heating method is combined, so that the gluing of the thin-wall composite material leading edge fairing can be realized, the equipment is simple, and the cost is low.

Description

Gluing mold and gluing method for thin-wall composite material leading edge fairing

Technical Field

The invention belongs to the field of machining, and particularly relates to a bonding technology of a thin-wall composite material leading edge fairing.

Background

For the glue joint of the thin-wall composite material leading edge fairing of the airfoil part, the heating and pressurizing glue joint solidification of the matched mould through an autoclave or a press is generally adopted. The heating and pressurizing cementing and curing technology of the autoclave and the press machine has the disadvantages of high technical performance required on equipment and high manufacturing cost.

Disclosure of Invention

In order to solve the defects of the prior art, the invention provides a novel mould structure and realizes the gluing of the leading edge fairing of the thin-wall composite material by combining an oven heating method. The combination of the mould and the method realizes the adhesive bonding and curing of the oven, so that the manufacturing cost is lower, and the technical performance requirement of the equipment is lower compared with that of an autoclave and an autoclave.

In order to solve the technical problem, the novel die provided by the invention comprises an upper die, a lower die, a front edge stop block, a locking block, a bolt and the like. The upper die and the lower die are butted to form a framework cavity of the airfoil-shaped part; the front edge fairing cavity of the front edge block is embedded into the opening parts of the upper die and the lower die and is butted with an airfoil part framework cavity formed by butting the upper die and the lower die to form an airfoil part cavity shape; the locking block fixedly connects the front edge stop block, the upper die and the lower die together through bolts.

Further, the mold is utilized, and an oven heating method is combined, so that the thin-wall composite material front edge fairing can be bonded, and the specific bonding method comprises the following steps:

s1: and (5) gluing the framework. Manually completing the gluing of other parts of the airfoil parts except the thin-wall leading edge fairing to form an airfoil part framework.

S2: the leading edge fairing is glued. And assembling and sealing the airfoil part framework and the front edge fairing, and performing pre-compaction.

S3: and laying an adhesive film. And laying a glue film between the leading edge fairing and the framework to form the airfoil part.

S4: and (5) heating the oven. And placing the combined airfoil parts into a die cavity, closing the upper die, the lower die and the front edge stop block, screwing the bolts to install the locking blocks in place, and placing the whole body into an oven for heating and curing.

The mould and the cementing method enable the cementing equipment of the leading edge fairing to be simple and low in cost.

Drawings

FIG. 1 is a schematic view of a mold of the present invention.

FIG. 2 is a schematic view of the airfoil-like component assembly of the present invention.

In FIGS. 1-2: 1. the structure comprises an upper die, 2, a lower die, 3, a front edge stop block, 4, a locking block, 5, bolts, 6, an airfoil part framework, 7 and a front edge fairing.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to fig. 1 and fig. 2, and it is obvious that the described embodiment is only a specific embodiment of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The airfoil part to be glued consists of an airfoil framework 6 and a leading edge fairing 7, wherein the airfoil framework 6 consists of an upper airfoil and a lower airfoil, and the leading edge fairing 7 is made of a thin-wall composite material.

The invented die is composed of upper die 1, lower die 2, front edge stop 3, locking block 4 and bolt 5. The upper die 1 and the lower die 2 are butted to form a framework cavity of the airfoil-shaped part; the front edge fairing cavity of the front edge block 3 is embedded into the opening parts of the upper die 1 and the lower die 2, and is butted with an airfoil part framework cavity formed by butting the upper die 1 and the lower die 2 to enclose an airfoil part cavity shape; the locking block 4 fixedly connects the front edge stop 3, the upper die 1 and the lower die 2 together through bolts 5.

When in gluing, the gluing of other parts of the airfoil parts except the thin-wall leading edge fairing 7 is manually completed to form an airfoil part framework 6; assembling and sealing the leading edge fairing 7 by using a sealing material, a breathable material and a vacuum bag, and performing pre-compaction; then, a glue film is laid between the front edge fairing 7 and the framework 6 to form a wing surface part; and finally, placing the combined airfoil parts into a die cavity, closing the upper die 1, the lower die 2 and the front edge stop block 3, screwing the bolts 5 to install the locking blocks 4 in place, and placing the whole body into an oven for heating and curing.

Claims

1. The utility model provides a thin wall composite material leading edge radome's glueing mould which characterized in that: the mould include mould (1), lower mould (2), leading edge dog (3), latch segment (4) and bolt (5), go up mould (1) and lower mould (2) butt joint and form airfoil class part skeleton chamber, mould (1) and lower mould (2) opening part are gone up in the leading edge fairing chamber embedding of leading edge dog (3), with the butt joint of the airfoil class part skeleton chamber of going up mould (1) and lower mould (2) butt joint formation, enclose synthetic airfoil class part chamber shape, latch segment (4) are in the same place leading edge dog (3) through bolt (5), go up mould (1) and lower mould (2) fixed connection.

2. A method of bonding using the bonding mold for thin-walled composite leading edge fairings of claim 1, comprising:

the gluing method adopts the following steps:

s1: and (5) gluing the framework. Manually completing the gluing of other parts of the airfoil parts except the thin-wall leading edge fairing (7) to form an airfoil part framework (6);

s2: the leading edge fairing (7) is glued. Assembling and sealing the airfoil part framework (6) and the front edge fairing (7), and performing pre-compaction;

s3: and laying an adhesive film. A glue film is laid between the leading edge fairing (7) and the framework (6) to form an airfoil part;

s4: and (5) heating the oven. And placing the combined airfoil parts into a die cavity, closing the upper die (1), the lower die (2) and the front edge stop block (3), screwing the bolt (5) to install the locking block (4) in place, and placing the whole body into an oven for heating and curing.