CN218577044U

CN218577044U - Engine housing and spray pipe integrated structure

Info

Publication number: CN218577044U
Application number: CN202221055998.1U
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: 2023-03-07
Anticipated expiration: 2032-05-03

Abstract

The utility model discloses an engine housing and spray tube integral structure comprises preceding head, winding layer, back skirt, back head, spray tube and shaft section heat insulation layer, the winding layer is main bearing structure, is located the preceding head, shaft section heat insulation layer and the back head outside, the back skirt is located the engine afterbody, connects the tail section, the back head is the mould pressing structure for adiabatic and installation spray tube, spray tube installation are on the back head. The utility model relates to an aerospace field technical field, this engine housing and spray tube integral structure have solved the problem that the negative weight of current engine is higher, drop emission cost is higher, the range is little, reliability and mobility are lower.

Description

Engine housing and spray pipe integrated structure

Technical Field

The utility model relates to an aerospace field technical field specifically is an engine housing and spray tube integral structure.

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 the french "M51" intercontinental missile, etc., began to use fiber reinforced composites, the housings being connected to a metal flange on the nozzle by metal joints. The strong aerospace nation, represented by the united states, russia, etc., has turned to composite engine case jet-pipe integration technology and has a high-performance weapon system with case jet-pipe integrated engines in multiple models, with a negative weight that continues to drop by 10% over the traditional composite engine cases, into the 21 st century.

In recent years, the fast boat No. eleven solid carrier rocket and the billow 3 submerged missile are successfully developed and launched, the engine shells of the fast boat No. eleven solid carrier rocket and the billow 3 submerged missile both adopt the high-performance carbon fiber composite material winding technology, but still adopt the traditional metal connection mode, and the domestic carbon fiber composite material shell spray pipe integration technology is not broken through in search. 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.

SUMMERY OF THE UTILITY MODEL

Technical problem to be solved

The utility model provides a not enough to prior art, the utility model provides an engine housing and spray tube integral structure has solved the problem that the negative weight of current engine is higher, it is higher to fall emission cost, the range is little, reliability and mobility are lower.

(II) technical scheme

In order to achieve the above purpose, the utility model discloses a following technical scheme realizes: the utility model provides an engine housing and spray tube integral structure, comprises preceding head, 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 preceding head, shaft section heat insulation layer and the back head outside, the back skirt is located the engine afterbody, connects the back end, the back head is the mould pressing structure for adiabatic and installation spray tube, the spray tube is installed on the back head, shaft section heat insulation layer is located the casing inboardly.

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 materials, a core mold is used as a mold, and the winding layer is wound by a wet method and heated and cured 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 debonding layer, wherein the heat insulation bottom layer, the adhesive layer and the manual debonding layer are made of ethylene propylene diene monomer, and the isolation layer is made of polytetrafluoroethylene demolding 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 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 rubber, 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.

Advantageous effects

The utility model provides an engine housing and spray tube integral structure. The method has the following beneficial effects:

(1) The engine shell and the spray pipe are of an integrated structure, 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) This engine housing and spray tube integral structure, the reliability of this application is higher. 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 sectional view of the present invention with the housing and the nozzle integrated.

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: the utility model provides an engine housing and spray tube integral structure, by preceding head 1, winding layer 2, back skirt 3, back head 4, spray tube 5 and barrel section heat insulation layer 6 constitute, winding layer 2 is main pressure-bearing structure, be located preceding head 1, barrel section heat insulation layer 6 and the 4 outsides of back head, back skirt 3 is located the engine afterbody, connect the tail section, back head 4 is the mould pressing structure, be used for thermal insulation and installation spray tube 5, spray tube 5 installs on back head 4, barrel section heat insulation layer 6 is located the casing inboard. 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, and the core mold is wound by a wet method and heated and cured by 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 forming 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 stopping 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 taken as an insert and integrally formed with the convergent section 5-1, the backing 5-2 and the divergent section 5-4 again.

When the igniter works, the igniter is installed on the front end socket, the explosive column is filled in the shell, the spray pipe is installed on the rear end socket, 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. The utility model provides an engine housing and spray tube integral structure which 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 tail portion, connect the tail section, back head (4) are the mould pressing structure for adiabatic 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. An engine housing and nozzle integrated structure 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. An engine housing and nozzle integrated structure as claimed in claim 1, wherein: 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. An engine housing and nozzle integrated structure 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. An engine housing and nozzle integrated structure as claimed in claim 1, wherein: the rear end socket (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 made of ethylene propylene diene monomer, and the isolation layer (4-3) is made of polytetrafluoroethylene demolding cloth.

6. An engine housing and nozzle integrated structure 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. An engine housing and nozzle integrated structure as claimed in claim 1, wherein: the heat insulating layer (6) of the barrel body section is ethylene propylene diene monomer rubber, and the filler is asbestos or silica.

8. The integrated engine housing and nozzle structure of claim 4, 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 arrest groove (3-2).

9. An engine housing and nozzle integrated structure 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 molded with the convergent section (5-1), the backing (5-2) and the divergent section (5-4) again.