阅读说明：本技术 一种固体火箭燃烧室隔热层的粘接结构及方法 (Bonding structure and method for thermal insulation layer of solid rocket combustion chamber ) 是由 李凤珍 朱晓军 李�杰 吉少波 于 2021-05-25 设计创作，主要内容包括：一种固体火箭燃烧室隔热层的粘接结构及方法,包括金属壳体、橡胶件、气囊、密封端盖、进气气管和抽气气管；金属壳体为单侧开口的筒状结构,橡胶件贴合设置在金属壳体的内侧壁；密封端盖设置在金属壳体的开口处,密封端盖内侧密封连接有气囊,进气气管和抽气气管均设置在密封端盖上,进气气管连通气囊,抽气气管连通气囊与橡胶件之间的空间。本发明采用气囊对隔热橡胶件进行压紧压实,使得橡胶件质地细密均匀,和金属壳体的贴合完整且紧密,比贴生胶工艺的性能更好。无论金属壳体的形状如何,气囊的柔性特点,配合充气和抽气,实现气囊和内侧壁的紧密贴合压紧。(A bonding structure and a bonding method of a thermal insulation layer of a solid rocket combustion chamber comprise a metal shell, a rubber piece, an air bag, a sealing end cover, an air inlet pipe and an air exhaust pipe; the metal shell is of a cylindrical structure with an opening at one side, and the rubber piece is attached to the inner side wall of the metal shell; the sealing end cover is arranged at the opening of the metal shell, the inner side of the sealing end cover is connected with an air bag in a sealing mode, the air inlet pipe and the air exhaust pipe are arranged on the sealing end cover, the air inlet pipe is communicated with the air bag, and the air exhaust pipe is communicated with the space between the air bag and the rubber piece. The invention adopts the air bag to compress and compact the heat-insulating rubber piece, so that the rubber piece has fine and uniform texture, is completely and tightly jointed with the metal shell, and has better performance than the raw rubber jointing process. No matter how the shape of the metal shell is, the flexible characteristic of the air bag is matched with inflation and air exhaust, and the air bag is tightly attached and compressed with the inner side wall.)

1. A bonding structure of a thermal insulation layer of a solid rocket combustion chamber is characterized by comprising a metal shell (1), a rubber piece (2), an air bag (3), a sealing end cover, an air inlet pipe (8) and an air exhaust pipe (11); the metal shell (1) is of a cylindrical structure with an opening at one side, and the rubber piece (2) is attached to the inner side wall of the metal shell (1); the sealing end cover is arranged at an opening of the metal shell (1), the inner side of the sealing end cover is connected with the air bag (3) in a sealing mode, the air inlet pipe (8) and the air exhaust pipe (11) are arranged on the sealing end cover, the air inlet pipe (8) is communicated with the inner side of the air bag (3), and the air exhaust pipe (11) is communicated with the space between the outer side of the air bag (3) and the rubber part (2).

2. The bonding structure of the insulation layer of the combustion chamber of the solid rocket according to claim 1, wherein the sealing end cover comprises a flange ring (5), an end cover (7) and a spring collar (9); the flange ring (5) is fixedly connected with the end cover (7) through screws, the air bag (3) is arranged on the inner side of the flange ring (5) in a sealing and fitting mode, and the spring retainer ring (9) is arranged on the inner side wall of an opening of the air bag (3).

3. The bonding structure of the insulation layer of the combustion chamber of a solid rocket as claimed in claim 2, wherein a sealing ring (6) is arranged between the flange ring (5) and the end cover (7).

4. The bonding structure of the insulation layer of the combustion chamber of a solid rocket as claimed in claim 2, wherein the outer side wall of the opening of the air bag (3) is connected with the inner side wall of the flange ring (5) by a sealant.

5. The bonding structure of the thermal insulation layer of the solid rocket combustion chamber as claimed in claim 2, wherein the air inlet pipe (8) is arranged on the end cover (7), and the air inlet pipe (8) is connected with an external high-pressure air source; the air exhaust pipe (11) is arranged on the flange ring (5), and the air exhaust pipe (11) is connected with an external air exhaust pump.

6. The bonding structure of the solid rocket combustion chamber insulation according to claim 1, wherein the flange ring (5) and the metal casing (1) are connected by screws.

7. The bonding structure of the solid rocket combustion chamber insulation according to claim 1, wherein the outer side wall of the rubber member (2) and the inner side wall of the metal casing (1) are coated with adhesive; the rubber part (2) is a fiber reinforced ethylene propylene diene monomer or butadiene acrylonitrile rubber molded part.

8. The method for bonding a bonding structure of a thermal insulating layer of a solid rocket combustion chamber as recited in any one of claims 1 to 7, comprising the steps of:

step 1, manufacturing a rubber piece (2): putting the ethylene propylene diene monomer raw material into a forming die, heating, pressurizing, vulcanizing and preforming; then, the rubber part (2) with the outline size consistent with the height of the inner cavity of the metal shell is formed by machining;

step 2, gluing and surface pretreatment: carrying out sand blasting treatment on the inner cavity of the metal shell (1); gluing the inner cavity of the metal shell (1) and the outer surface of the rubber piece (2);

step 3, bonding: the rubber part (2) is plugged into the metal shell (1); the air bag (3) is inserted into the inner cavity of the rubber piece, a flange ring (5) at one end of an opening of the air bag (3) and an end cover (7) are fastened into a whole by a screw (10) and are airtight between a sealing ring (6) seat and the air bag, and a contact section of the air bag (3) and the flange ring (5) is coated with sealant and is pressed by an elastic retainer ring (10); fastening a flange ring connected to the airbag (3) to an open end of the metal case (1) with screws (10); the interior of the metal shell (1) outside the air bag is vacuumized through an air exhaust pipe (11); introducing high-pressure air into the air bag (3) to expand the air bag (3) and fully compress the outer surface of the rubber part (2) and the inner cavity surface of the metal shell (1); the adhesive is cured by heating.

Technical Field

The invention relates to the technical field of manufacturing of solid rocket combustion chambers, in particular to a bonding structure and a bonding method for a thermal insulation layer of a solid rocket combustion chamber.

Background

The heat insulating layer of the metal shell solid rocket combustion chamber is used for isolating heat transfer between the explosive column and the outer shell in the combustion process of the rocket engine. In the past, ethylene propylene diene monomer raw material is firstly pasted on the inner wall of a shell, and then is heated and vulcanized to form a compact rubber layer with a certain thickness. For a metal shell with a small diameter, particularly a slender shell, the traditional method is very difficult to manufacture the heat insulation layer, and the quality is not easy to ensure.

Disclosure of Invention

The invention aims to provide a bonding structure and a bonding method for a thermal insulation layer of a solid rocket combustion chamber, which aim to solve the problems.

In order to achieve the purpose, the invention adopts the following technical scheme:

a bonding structure of a solid rocket combustion chamber heat insulation layer comprises a metal shell, a rubber piece, an air bag, a sealing end cover, an air inlet pipe and an air exhaust pipe; the metal shell is of a cylindrical structure with an opening at one side, and the rubber piece is attached to the inner side wall of the metal shell; the sealing end cover is arranged at the opening of the metal shell, the air bag is connected to the inner side of the sealing end cover in a sealing mode, the air inlet pipe and the air exhaust pipe are arranged on the sealing end cover, the air inlet pipe is communicated with the inner side of the air bag, and the air exhaust pipe is communicated with the space between the outer side of the air bag and the rubber piece.

Further, the sealing end cover comprises a flange ring, an end cover and a spring retainer ring; the flange ring is fixedly connected with the end cover through screws, the air bag is arranged on the inner side of the flange ring in a sealing and fitting mode, and the spring retainer ring is arranged on the inner side wall of the air bag opening.

Further, a sealing ring is arranged between the flange ring and the end cover.

Furthermore, the outer side wall of the air bag opening and the inner side wall of the flange ring are coated with adhesives.

Further, the air inlet pipe is arranged on the end cover and is connected with an external high-pressure air source; the air exhaust pipe is arranged on the flange ring and is connected with an external air exhaust pump.

Further, the flange ring and the metal shell are connected through screws.

Further, the outer side wall of the rubber part is connected with the inner side wall of the metal shell through a sealant; the rubber part is a fiber reinforced ethylene propylene diene monomer or butadiene acrylonitrile rubber molded part.

Further, the bonding method of the bonding structure of the thermal insulation layer of the solid rocket combustion chamber comprises the following steps:

step 1, manufacturing a rubber piece: putting the ethylene propylene diene monomer raw material into a forming die, heating, pressurizing, vulcanizing and preforming; then, the rubber part with the outline size consistent with the height of the inner cavity of the metal shell is formed by machining;

step 2, gluing and surface pretreatment: carrying out sand blasting treatment on the inner cavity of the metal shell; coating the inner cavity of the metal shell and the outer surface of the rubber piece with glue;

step 3, bonding: the rubber part is plugged into the metal shell; the air bag is inserted into the inner cavity of the rubber piece, a flange ring at one end of an opening of the air bag and an end cover are fastened into a whole by screws and have air tightness between a sealing ring seat and the air bag, and the contact section of the air bag and the flange ring is coated with sealant and is pressed by an elastic retaining ring; fastening a flange ring connected to the airbag to an open end of the metal case with screws; vacuumizing the interior of the metal shell outside the air bag through an air exhaust pipe; introducing high-pressure air into the air bag to expand the air bag and fully compress the outer surface of the rubber part and the surface of the inner cavity of the metal shell; the adhesive is cured by heating.

Compared with the prior art, the invention has the following technical effects:

the invention adopts the air bag to compress and compact the heat-insulating rubber piece, so that the rubber piece has fine and uniform texture, is completely and tightly jointed with the metal shell, and has better performance than the raw rubber jointing process. No matter how the shape of the metal shell is, the flexible characteristic of the air bag is matched with inflation and air exhaust, and the air bag is tightly attached and compressed with the inner side wall.

The invention has high production efficiency, small influence of human factors and stable product quality.

Drawings

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

1-metal shell, 2-rubber piece, 3-air bag, 3' -expanded air bag, 4-screw, 5-flange ring, 6-sealing ring, 7-end cover, 8-air inlet pipe, 9-spring retainer ring, 10-screw and 11-air exhaust pipe.

Detailed Description

The invention is further described below with reference to the accompanying drawings:

referring to fig. 1, the heat insulating layer bonding structure and the bonding method of the present invention include a metal casing 1, a rubber member 2, an air bag 3, a sealing end cap, an air inlet pipe 8 and an air exhaust pipe 11; the metal shell 1 is a cylindrical structure with an opening on one side, and the rubber part 2 is attached to the inner side wall of the metal shell 1; the end cover sets up the opening part at metal casing 1, and the inboard sealing connection of end cover has gasbag 3, and intake pipe 8 all sets up on sealed end cover with the trachea 11 of bleeding, and intake pipe 8 communicates the inboard of gasbag 3, the trachea 11 space between the outside and the rubber spare 2 of the trachea 3 of bleeding.

The heat-insulation rubber part is compacted by injecting high-pressure air into the inner side of the air bag, so that the rubber part is fine and uniform in texture, is completely and tightly attached to the metal shell, and has better performance than a raw rubber attaching process. No matter how the shape of the metal shell is, the flexible characteristic of the air bag is matched with inflation and air exhaust, and the air bag can be tightly attached and compressed with the inner side wall of the metal shell.

The sealing end cover comprises a flange ring 5, an end cover 7 and a spring retainer ring 9; flange ring 5 and end cover 7 pass through screw fixed connection, and the sealed laminating of gasbag 3 sets up at flange ring 5 inboardly, and circlip 9 sets up at 3 open-ended inside walls of gasbag.

Firstly, putting ethylene propylene diene monomer raw material into a special forming die, heating, pressurizing, vulcanizing and preforming, then machining a rubber piece with the outline size consistent with the height of the inner cavity of the metal shell, then coating glue on the joint surface of the inner cavity of the metal shell and the rubber piece, plugging the rubber piece into the metal shell, and heating to cure the adhesive.

In order to ensure that the rubber part is fully combined with the inner cavity of the metal shell, after the rubber part is plugged into the metal shell, a special air bag is plugged into the inner cavity of the rubber part, and high-pressure air is introduced into the air bag, so that the outer surface of the rubber part and the surface of the inner cavity of the metal shell are fully pressed by the expansion of the air bag.

Because the shell is longer, in order to prevent bubbles from accumulating on the bonding surface, before the high-pressure air is communicated for the expansion of the air bag, the space between the rubber part and the inner cavity of the metal shell is vacuumized.

The surface is roughened before the inner cavity of the metal shell is coated with glue.

Example (b):

this embodiment is described with reference to fig. 1.

Firstly, manufacturing an ethylene propylene diene monomer rubber heat insulation piece: putting the ethylene propylene diene monomer raw material into a special forming die, heating, pressurizing, vulcanizing and preforming; and then the rubber part 2 with the outline size consistent with the height of the inner cavity of the metal shell is formed by machining.

Step two, gluing and surface pretreatment: carrying out sand blasting treatment on the inner cavity of the metal shell 1; the inner cavity of the metal shell 1 and the outer surface of the rubber member 2 are rubberized.

Thirdly, bonding: the rubber part 2 is plugged into the metal shell 1; a special air bag 3 is plugged into the inner cavity of the rubber part 1, one end of an opening of the air bag 3 is provided with a flange ring 5 and an end cover 7, the flange ring 5 and the end cover 7 are fastened into a whole by a screw 10 and are provided with air tightness between a sealing ring 6 and a sealing ring, and the contact section of the air bag 3 and the flange ring 5 is coated with sealant and is pressed by an elastic retainer ring 10;

fastening a flange ring connected to the airbag 3 to the open end of the housing 1 with screws 10;

the interior of the shell 1 outside the air bag is vacuumized through an air pipe 11; introducing high-pressure air into the air bag 3 to expand the air bag 3 and fully press the outer surface of the rubber part 2 and the inner cavity surface of the metal shell 1; heating for a certain time to cure the adhesive.

When the air bag is manufactured sporadically, a plastic film can be used as an air-tight layer material, and the shell 1 filled with the air bag 3 is wholly wrapped up and inserted with a pipe for air suction.