CN114889157A

CN114889157A - Engine shell and spray pipe integrated structure and preparation method thereof

Info

Publication number: CN114889157A
Application number: CN202210490177.9A
Authority: CN
Inventors: 王国平; 宫瑞君; 刘端娜; 王凯; 苏醒
Original assignee: Weihai Guangsheng Aerospace Technology Co ltd
Current assignee: Weihai Guangsheng Aerospace Technology Co ltd
Priority date: 2022-05-03
Filing date: 2022-05-03
Publication date: 2022-08-12

Abstract

The invention discloses an engine shell and spray pipe integrated structure and a preparation method thereof. The invention relates to the technical field of aerospace. The engine shell and spray pipe integrated structure and the preparation method thereof solve the problems of high passive weight, high emission cost reduction, small range, and low reliability and maneuverability of the conventional engine.

Description

Engine shell and spray pipe integrated structure and preparation method thereof

Technical Field

The invention relates to the technical field of aerospace, in particular to an engine shell and spray pipe integrated structure and a preparation method thereof.

Background

Since the 80's of the 20 th century, solid engine housings for various tactical missiles such as the trident submarine missile channel missile, the russian "SS-25" intercontinental missile, the japanese "M-5" rocket, the european "ali 5" and french "M51" intercontinental missiles, etc., began to use fiber reinforced composites, the housings being connected to metal flanges on the nozzle by metal joints. The strong aerospace countries, as represented by the united states, russia, etc., have turned to composite engine case jet integration technology and have high performance weapon systems with case jet integration engines that continue to reduce their passive weight by 10% over traditional composite engine cases, into the 21 st century.

Because of international blockade, the application of carbon fiber composite materials in China is late, in recent years, a fast boat No. eleven solid carrier rocket and a giant-wave 3 submarine missile are successfully developed and launched, engine shells of the fast boat No. eleven solid carrier rocket and the giant-wave 3 submarine missile both adopt a high-performance carbon fiber composite material winding technology, but still adopt a traditional metal connection mode, and the domestic carbon fiber composite material shell spray pipe integration technology is not broken through in exploration. Compared with the traditional shell and spray pipe split type structure, the shell and spray pipe integrated structure can reduce the passive weight, increase the range and improve the reliability and the maneuverability.

Disclosure of Invention

Technical problem to be solved

Aiming at the defects of the prior art, the invention provides an integrated structure of an engine shell and a spray pipe and a preparation method thereof, and solves the problems of higher passive weight, higher emission cost reduction, small range, and lower reliability and maneuverability of the conventional engine.

(II) technical scheme

In order to achieve the purpose, the invention is realized by the following technical scheme: the utility model provides an engine housing and spray tube integral structure and preparation method thereof, comprises front cover, winding layer, back skirt, back head, spray tube and shaft section heat insulation layer, the winding layer is main pressure-bearing structure, is located the front cover, the shaft section heat insulation layer and the back head outside, back skirt is located the engine afterbody, connects the tail section, the back head is the mould pressing structure, mainly used thermal insulation and installation spray tube, the spray tube is installed on the back head, shaft section heat insulation layer is located the casing inboard.

Preferably, the front end enclosure is of a rubber metal sandwich structure, the sandwich is a titanium alloy machining joint, and blind hole threads connected with an igniter are arranged on the joint.

Preferably, the winding layer is made of carbon fiber epoxy resin composite material, a core mold is used as a mold,

and (4) winding by a wet method, and heating, curing and molding by an oven.

Preferably, the rear skirt is composed of a composite skirt body and a metal corner box.

Preferably, the rear end socket consists of a heat insulation bottom layer, an adhesive layer, an isolation layer and a manual release layer, wherein the heat insulation bottom layer, the adhesive layer and the manual release layer are made of ethylene propylene diene monomer, and the isolation layer is made of polytetrafluoroethylene release cloth.

Preferably, the nozzle consists of a convergent section, a backing, a throat insert and an expansion section, wherein the convergent section, the backing and the expansion section are made of carbon/phenolic aldehyde composite materials, and the throat insert is made of C/C composite materials.

Preferably, the heat insulating layer of the barrel section is ethylene propylene diene monomer, and the filler is asbestos or silica.

Preferably, the composite skirt body is made of carbon fiber epoxy resin composite materials, a metal mold is used, vacuum autoclave molding is adopted, the corner box is formed by adding a titanium alloy machine, and the composite skirt body is provided with a cable through hole and a crack stopping groove.

Preferably, the nozzle is firstly molded by compression, and then the throat insert is taken as an insert and is integrally molded with the convergent section, the backing and the divergent section again.

Preferably, the manufacturing process and preparation method are as follows:

step one, front end enclosure: adding a joint by using a titanium alloy machine on the front end socket 1 by using a TC4 forging machine, and then using the joint as an insert to be integrally molded with the ethylene propylene diene monomer;

step two, skirt backing:

d. laying carbon fiber and epoxy resin composite prepreg on the metal male die according to the designed number and angle of the layers, curing and molding the composite skirt body at high temperature by a vacuum bag autoclave, and machining a crack-stopping groove and a cable through hole;

e. using a TC4 plate machine to angle the box;

f. assembling the composite skirt body and the corner box through the assembling jig;

step three, sealing the head; ethylene propylene diene monomer is used as the materials of the heat insulation bottom layer, the bonding layer, the isolation layer and the manual debonding layer, polytetrafluoroethylene demolding cloth is used as the material of the isolation layer, and the materials are subjected to compression molding by a steel combined die;

step four, spraying a pipe: using a prefabricated body of the carbon fiber woven throat insert, carrying out multiple times of dipping, curing and solid phase cracking on phenolic resin, and finally carrying out heat treatment to form the C/C composite throat insert with the preset density; then, the throat liner is used as an insert, and carbon/phenolic aldehyde composite material prepreg is used as a molding material tablet of the convergent section, the back lining and the expansion section, and the whole body is molded and formed again;

step five, winding for the first time: paving demoulding cloth on a core mould, installing a front end socket, a rear end socket and a spray pipe on the core mould, paving a heat insulating layer on a barrel body section by using ethylene propylene diene monomer rubber, winding an inner winding layer by using carbon fiber and epoxy resin through a wet method, alternately performing annular winding and spiral winding, and curing the inner winding layer by using an oven after winding is finished;

step six, dress skirt: installing the rear skirt by using a skirt positioning tool;

step seven, winding for the second time: using carbon fiber and epoxy resin to circumferentially wind the outer winding layer by a wet method, and curing the outer winding layer by an oven after the winding is finished;

the whole machine is added: and (3) adding the end face of the skirt body made of the composite material and the mounting hole machine of the corner box to the dimensional accuracy required by the design by using a machine tool.

Advantageous effects

The invention provides an engine shell and spray pipe integrated structure and a preparation method thereof. The method has the following beneficial effects:

(1) the engine shell and spray pipe integrated structure and the preparation method thereof have the advantages that the passive weight is less, and the reflection cost is reduced. Weight is reduced by more than 50% relative to the steel shell; compared with a split structure of the composite material shell and the spray pipe, the weight is reduced by more than 7%. The reduction of passive weight can greatly reduce the launching cost of rockets or missiles, increase the range and improve the maneuverability.

(2) The engine shell and spray pipe integrated structure and the preparation method thereof have higher reliability. The utility model provides a part is small in quantity, fuses back head and spray tube as an organic whole, has reduced mechanical connection, has eliminated the active surface that needs seal, has reduced the pressure release risk, and the reliability is higher, and this application is by combined material engine housing and spray tube integral structure, can reduce passive weight, reduce emission cost, increase the range, improve reliability and mobility.

Drawings

FIG. 1 is an isometric view of the present invention;

FIG. 2 is a cross-sectional view of the present invention;

FIG. 3 is a side view of the rear skirt shaft of the present invention;

FIG. 4 is a partial cross-sectional view of the housing of the present invention integrated with the spout.

In the figure: 1. a front end enclosure; 2. a winding layer; 2-1, outer winding layer; 2-2, inner winding layer; 3. a rear skirt; 3-1, a composite skirt body; 3-2, a crack arrest groove; 3-3, cable through holes; 3-4, corner boxes; 4-1, a heat insulating bottom layer; 4-2, an adhesive layer; 4-3, an isolation layer; 4-4, manually removing the adhesive layer; 5-1, a convergence section; 5-2, backing; 5-3, a throat liner; 5-4, an expansion section; 6. a heat insulating layer on the barrel section.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

Referring to fig. 1-4, the present invention provides a technical solution:

the first embodiment is as follows: an engine shell and spray pipe integrated structure and a preparation method thereof are disclosed, the structure is composed of a front seal head 1, a winding layer 2, a rear skirt 3, a rear seal head 4, a spray pipe 5 and a barrel section heat insulation layer 6, wherein the winding layer 2 is a main pressure bearing structure and is positioned on the outer sides of the front seal head 1, the barrel section heat insulation layer 6 and the rear seal head 4, the rear skirt 3 is positioned at the tail part of an engine and is connected with a tail section, the rear seal head 4 is a mould pressing structure and is mainly used for heat insulation and installation of the spray pipe 5, the spray pipe 5 is installed on the rear seal head 4, and the barrel section heat insulation layer 6 is positioned on the inner side of the shell. The front seal head 1 is of a rubber metal sandwich structure, the sandwich is a titanium alloy machine-added joint, and blind hole threads connected with an igniter are arranged on the joint. The winding layer 2 is made of carbon fiber epoxy resin composite materials, a core mold is used as a mold, wet winding is carried out, and heating and curing molding are carried out in an oven. The rear skirt 3 consists of a composite skirt body 3-1 and a metal corner box 3-4. The rear end enclosure 4 consists of a heat insulation bottom layer 4-1, an adhesive layer 4-2, an isolation layer 4-3 and a manual debonding layer 4-4, wherein the heat insulation bottom layer 4-1, the adhesive layer 4-2 and the manual debonding layer 4-4 are ethylene propylene diene monomer, and the isolation layer 4-3 is polytetrafluoroethylene demolding cloth.

Example two: the difference between the embodiment and the first embodiment is that the nozzle 5 consists of a convergent section 5-1, a back lining 5-2, a throat insert 5-3 and an expansion section 5-4, wherein the convergent section 5-1, the back lining 5-2 and the expansion section 5-4 are made of carbon/phenolic composite materials, and the throat insert 5-3 is made of C/C composite materials. The heat insulating layer 6 of the barrel body section is ethylene propylene diene monomer rubber, and the filler is asbestos or silicon dioxide. The composite skirt body 3-1 is made of carbon fiber epoxy resin composite materials, a metal mold is used, vacuum autoclave molding is adopted, the corner box 3-4 is formed by titanium alloy machining, and the composite skirt body 3-1 is provided with a cable through hole 3-3 and a crack arrest groove 3-2. And the nozzle 5 is formed by compression molding the throat insert 5-3, and then the throat insert 5-3 is used as an insert and is integrally formed with the convergent section 5-1, the backing 5-2 and the divergent section 5-4 again. The manufacturing process and the preparation method are as follows:

step one, a front end enclosure 1: adding a joint by using a titanium alloy machine on the front end socket 1 by using a TC4 forging machine, and then using the joint as an insert to be integrally molded with the ethylene propylene diene monomer;

step two, the rear skirt 3:

g. laying carbon fiber epoxy resin composite material prepreg on a metal male die according to the designed number and angle of layers, curing and molding a composite material skirt body 3-1 at high temperature through a vacuum bag autoclave, and then machining a crack arrest groove 3-2 and a cable through hole 3-3;

h. using a TC4 plate machine to make a corner box 3-4;

i. assembling the skirt body 3-1 and the corner box 3-4 made of the composite material through an assembling jig;

step three, a rear end socket 4; ethylene propylene diene monomer is used as the material of the heat insulation bottom layer 4-1, the adhesive layer 4-2, the isolation layer 4-3 and the manual release layer 4-4, polytetrafluoroethylene release cloth is used as the material of the isolation layer 4-3, and the materials are subjected to compression molding by a steel combined die;

step four, spraying a pipe 5: weaving a prefabricated body of the throat insert 5-3 by using carbon fibers, carrying out multiple times of impregnation, curing and solid phase cracking on phenolic resin, and finally carrying out heat treatment to form the throat insert 5-3 made of the C/C composite material with the preset density; then, integrally molding and forming the throat liner 5-3 serving as an insert and carbon/phenolic aldehyde composite prepreg serving as molding material sheets of the convergent section 5-1, the backing 5-2 and the divergent section 5-4;

step five, winding for the first time: paving demolding cloth on a core mold, installing a front end enclosure 1, a rear end enclosure 4 and a spray pipe 5 on the core mold, paving a barrel body section heat insulation layer 6 by using ethylene propylene diene monomer rubber, winding an inner side winding layer 2-2 by using carbon fiber and epoxy resin through a wet method, alternately performing annular winding and spiral winding, and curing the inner side winding layer 2-2 by using an oven after winding is finished;

step six, dress skirt: installing the rear skirt 3 by using a skirt positioning tool;

step seven, winding for the second time: using carbon fiber and epoxy resin to circumferentially wind the outer winding layer 2-1 by a wet method, and curing the outer winding layer 2-1 by an oven after winding;

the whole machine is added: the end face of the composite skirt 3-1 and the mounting hole machine of the angle box 3-4 are added to the dimensional accuracy required for the design using a machine tool.

When the igniter works, the igniter is installed on the front end enclosure, the explosive column is filled in the shell, the spray pipe is installed on the rear end enclosure, and the tail section is connected with the rear skirt. The front end enclosure, the barrel body section heat insulation layer and the rear end enclosure form the inner heat insulation of the shell together, the inner heat insulation has the characteristics of small heat conductivity coefficient and heat diffusion coefficient, large specific heat capacity, high effective ablation heat and the like, and the shell is protected through heat insulation and an ablation mechanism; the manual de-bonding layer is arranged on the end socket, so that the stress concentration level at two ends of the engine under the temperature load can be reduced; the winding layer is a main pressure-bearing structure and mainly bears loads such as high pressure, thrust, inertia force, thermal stress, impact vibration and the like; the jet pipe has good heat insulation performance, can bear ablation and scouring of high-temperature and high-speed airflow, and has enough heat intensity to generate thrust.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions.

Claims

1. An engine shell and spray pipe integrated structure and a preparation method thereof are characterized in that: constitute by preceding head (1), winding layer (2), back skirt (3), back head (4), spray tube (5) and shaft section heat insulation layer (6), winding layer (2) are main bearing structure, are located preceding head (1), shaft section heat insulation layer (6) and back head (4) outside, back skirt (3) are located the engine afterbody, connect the tail section, back head (4) are the mould pressing structure, mainly used thermal insulation and installation spray tube (5), install on back head (4) spray tube (5), shaft section heat insulation layer (6) are located the casing inboardly.

2. The integrated structure of the engine shell and the spray pipe and the preparation method thereof as claimed in claim 1, wherein: the front seal head (1) is of a rubber metal sandwich structure, the sandwich is a titanium alloy machine-added joint, and blind hole threads connected with an igniter are arranged on the joint.

3. The integrated structure of the engine shell and the nozzle and the preparation method thereof according to claim 1, characterized in that: the winding layer (2) is made of carbon fiber epoxy resin composite materials, a core mold is used as a mold, wet winding is carried out, and heating and curing molding are carried out in an oven.

4. The integrated structure of the engine shell and the spray pipe and the preparation method thereof as claimed in claim 1, wherein: the rear skirt (3) is composed of a composite skirt body (3-1) and a metal corner box (3-4).

5. The integrated structure of the engine shell and the spray pipe and the preparation method thereof as claimed in claim 1, wherein: the rear end enclosure (4) is composed of a heat insulation bottom layer (4-1), an adhesive layer (4-2), an isolation layer (4-3) and a manual debonding layer (4-4), the heat insulation bottom layer (4-1), the adhesive layer (4-2) and the manual debonding layer (4-4) are ethylene propylene diene monomer, and the isolation layer (4-3) is made of polytetrafluoroethylene demolding cloth.

6. The integrated structure of the engine shell and the spray pipe and the preparation method thereof as claimed in claim 1, wherein: the nozzle (5) consists of a convergent section (5-1), a backing (5-2), a throat insert (5-3) and an expansion section (5-4), wherein the convergent section (5-1), the backing (5-2) and the expansion section (5-4) are made of carbon/phenolic composite materials, and the throat insert (5-3) is made of C/C composite materials.

7. The integrated structure of the engine shell and the spray pipe and the preparation method thereof as claimed in claim 1, wherein: the heat insulation layer (6) of the barrel body section is ethylene propylene diene monomer rubber, and the filler is asbestos or silica.

8. The integrated structure of the engine shell and the spray pipe and the preparation method thereof as claimed in claim 1, wherein: the composite skirt body (3-1) is made of carbon fiber epoxy resin composite materials, a metal mold is used, vacuum autoclave molding is adopted, the corner box (3-4) is formed by adding a titanium alloy machine, and the composite skirt body (3-1) is provided with a cable through hole (3-3) and a crack stop groove (3-2).

9. The integrated structure of the engine shell and the spray pipe and the preparation method thereof as claimed in claim 6, wherein: the spray pipe (5) is formed by compression molding the throat insert (5-3), and then the throat insert (5-3) is used as an insert and integrally formed with the convergent section (5-1), the backing (5-2) and the divergent section (5-4) again.

10. An engine case and nozzle integrated structure and a manufacturing method thereof as claimed in claims 1 to 9, wherein:

the manufacturing process and the preparation method are as follows:

a front end socket (1): adding a joint by using a titanium alloy machine on the front end socket 1 by using a TC4 forging machine, and then using the joint as an insert to be integrally molded with the ethylene propylene diene monomer;

② rear skirt (3):

a. laying carbon fiber epoxy resin composite material prepreg on a metal male die according to the designed number and angle of layers, curing and molding a composite material skirt body (3-1) at high temperature through a vacuum bag autoclave, and then mechanically adding a crack stopping groove (3-2) and a cable through hole (3-3);

b. using a TC4 plate machine to make a corner box (3-4);

c. assembling the skirt body (3-1) and the corner box (3-4) made of the composite material through an assembling jig;

thirdly, a rear end enclosure (4); ethylene propylene diene monomer is used as the material of the heat insulation bottom layer (4-1), the bonding layer (4-2), the isolation layer (4-3) and the manual de-bonding layer (4-4), polytetrafluoroethylene demolding cloth is used as the material of the isolation layer (4-3), and the materials are subjected to compression molding by a steel combined die;

spray pipe (5): using a prefabricated body of the carbon fiber woven throat insert (5-3), carrying out multiple times of impregnation, solidification and solid phase cracking on phenolic resin, and finally carrying out heat treatment to form the C/C composite throat insert (5-3) with preset density; then, the throat liner (5-3) is used as an insert, and carbon/phenolic aldehyde composite material prepreg is used as a molding material sheet of the convergence section (5-1), the back lining (5-2) and the expansion section (5-4), and the whole body is molded and formed again;

winding for the first time: paving demolding cloth on a core mold, installing a front end socket (1), a rear end socket (4) and a spray pipe (5) on the core mold, paving a heat insulating layer (6) on a barrel body section by using ethylene propylene diene monomer, winding an inner side winding layer (2-2) by using carbon fiber and epoxy resin through a wet method, alternately performing annular winding and spiral winding, and curing the inner side winding layer (2-2) by using an oven after winding is finished;

sixthly, skirt installation: installing a rear skirt (3) by using a skirt positioning tool;

and seventh winding: using carbon fiber and epoxy resin to wind the outer winding layer (2-1) in a circumferential direction by a wet method, and curing the outer winding layer (2-1) by an oven after the winding is finished;

the whole machine is added: and (3) adding the end face of the skirt body (3-1) made of the composite material and the mounting hole machine of the corner box (3-4) to the dimensional accuracy required by the design by using a machine tool.