阅读说明：本技术 一种适用于铝合金长尾喷管固体火箭发动机的绝热层组件 (Heat insulation layer assembly suitable for aluminum alloy long-tail nozzle solid rocket engine ) 是由 邢鹏涛 王中 马宇 舒慧明 朱佳佳 李瑞锋 古呈辉 李宏岩 时艺娟 许云志 刘萌 于 2019-11-15 设计创作，主要内容包括：本发明公开了一种适用于铝合金长尾喷管固体火箭发动机的绝热层组件,包括前封头绝热层、燃烧室绝热层、喷管绝热层、喉衬、扩张段绝热层等部分,绝热层组件整体为刚性全包覆式结构形式,前封头绝热层与燃烧室绝热层之间采用“L”形搭接结构连接,燃烧室绝热层与喷管绝热层之间采用“L”形搭接结构连接,喷管绝热层与扩张段绝热层之间采用“L”形搭接结构连接。本发明绝热层组件通过应用刚性全包覆式绝热层组件,提高了火箭发动机的冲量质量比和工作可靠性,缩短了绝热层组件的制备时间,减轻了火箭发动机的冗余质量,易于进行批量化生产,质量一致性好,只需1名装配人员便可完成装配,适用于Φ200.0mm直径以内、长尾喷管长度在150.0mm以内的铝合金固体火箭发动机。(The invention discloses an insulating layer assembly suitable for an aluminum alloy long-tail nozzle solid rocket engine, which comprises a front end socket insulating layer, a combustion chamber insulating layer, a nozzle insulating layer, a throat liner, an expansion section insulating layer and the like, wherein the whole insulating layer assembly is in a rigid full-coating structural form, the front end socket insulating layer is connected with the combustion chamber insulating layer by adopting an L-shaped lap joint structure, the combustion chamber insulating layer is connected with the nozzle insulating layer by adopting an L-shaped lap joint structure, and the nozzle insulating layer is connected with the expansion section insulating layer by adopting an L-shaped lap joint structure. The heat insulation layer assembly improves the impulse mass ratio and the working reliability of the rocket engine by applying the rigid full-coating heat insulation layer assembly, shortens the preparation time of the heat insulation layer assembly, reduces the redundant quality of the rocket engine, is easy to carry out batch production, has good quality consistency, can be assembled by only 1 assembler, and is suitable for the aluminum alloy solid rocket engine with the diameter of phi 200.0mm and the length of a long tail nozzle within 150.0 mm.)

1. The utility model provides an insulating layer subassembly suitable for long tail nozzle solid rocket engine of aluminum alloy, includes preceding head heat insulation layer (1), combustion chamber heat insulation layer (2), spray tube heat insulation layer (3), throat liner (4), expansion section heat insulation layer (5), its characterized in that: the front end socket heat insulation layer (1) is connected with the combustion chamber heat insulation layer (2) through an L-shaped lap joint structure, the combustion chamber heat insulation layer (2) is connected with the spray pipe heat insulation layer (3) through an L-shaped lap joint structure, the spray pipe heat insulation layer (3) is connected with the expansion section heat insulation layer (5) through an L-shaped lap joint structure, and the throat liner (4) is connected with the spray pipe heat insulation layer (3) and the expansion section heat insulation layer (5) through an embedded mode.

2. The insulation layer assembly for an aluminum alloy long tail nozzle solid rocket engine according to claim 1, wherein: the front end enclosure heat insulation layer (1), the combustion chamber heat insulation layer (2), the spray pipe heat insulation layer (3) and the expansion section heat insulation layer (5) are all made of die pressing high silica fiber/phenolic aldehyde or die pressing carbon fiber/phenolic aldehyde materials.

3. An insulation layer assembly suitable for use in an aluminum alloy long tail nozzle solid rocket engine according to claim 1 or 2, wherein: the geometrical structure of the front end outer contour of the front end socket heat insulation layer (1) can be a three-center dish-shaped pattern, a flat plate-shaped pattern, an ellipsoid-shaped pattern or a spherical pattern.

4. An insulation layer assembly suitable for use in an aluminum alloy long tail nozzle solid rocket engine according to claim 1 or 2, wherein: the external contour geometrical structure of the rear end of the heat insulating layer (2) of the combustion chamber can be in a three-center dish shape mode, a flat plate shape mode, an ellipsoid shape mode or a spherical shape mode.

5. The insulation layer assembly for an aluminum alloy long tail nozzle solid rocket engine according to claim 1, wherein: the length of the L-shaped lap joint structure between the front end socket heat insulation layer (1) and the combustion chamber heat insulation layer (2) is 10.0 mm-20.0 mm.

6. The insulation layer assembly for an aluminum alloy long tail nozzle solid rocket engine according to claim 1, wherein: the length of the L-shaped lap joint structure between the combustion chamber heat insulation layer (2) and the spray pipe heat insulation layer (3) is 5.0 mm-10.0 mm.

7. The insulation layer assembly for an aluminum alloy long tail nozzle solid rocket engine according to claim 1, wherein: the length of the L-shaped lap joint structure between the spray pipe heat insulation layer (3) and the expansion section heat insulation layer (5) is 8.0 mm-14.0 mm.

8. The insulation layer assembly for an aluminum alloy long tail nozzle solid rocket engine according to claim 1, wherein: the throat insert (4) is made of graphite, tungsten copper-infiltrated material or mould pressing carbon fiber/phenolic aldehyde material.

9. An insulation layer assembly suitable for use in an aluminum alloy long tail nozzle solid rocket engine according to claim 1 or 8, wherein: the length of the throat insert (4) is 25.0 mm-35.0 mm.

Technical Field

The invention belongs to the field of solid rocket engines, and relates to a rigid full-coating type heat insulating layer which is mainly applied to a thermal protection material of an aluminum alloy long-tail nozzle solid rocket engine.

Background

The thermal protection and heat insulation layer material of the solid rocket engine generally adopts elastic thermal protection materials, such as: nitrile rubber, ethylene propylene diene monomer, silicon rubber and other materials, wherein the ethylene propylene diene monomer has the advantages of low density, good heat insulation, excellent mechanical property and the like, and is a solid rocket engine heat insulation material widely used at home and abroad at present.

Because the mechanical property of the aluminum alloy material is very sensitive to the change of temperature, the requirement of the aluminum alloy solid rocket engine on the heat insulating layer is very high, once the defect of the local heat insulating layer occurs, the engine is burnt through slightly, and the engine is disintegrated and exploded if the defect occurs, the engine is exploded, and the heat insulating layer is broken through. At present, the aluminum alloy rocket engine generally adopts ethylene propylene diene monomer materials to manufacture the heat insulating layers of all structural components, is limited by the characteristics of elastic thermal protection materials, the connection among the heat insulating layers of all structural components is in a face-to-face mode, the sealing effect is poor, and when the engine works, the connection parts of the heat insulating layers of different parts are easily pressed and deformed under the action of high-temperature and high-pressure gas to cause the phenomenon of 'fire leaping', cause the sealing failure, and finally cause the abnormal work of the engine.

In order to solve the problem, the aluminum alloy solid rocket engine shell assembly is usually designed to be in an external thread connection mode, and the structure has good sealing performance and good manufacturability. But this increases the outer diameter of the engine, adding to the redundant mass of the engine. In addition, under the condition that the engine component is designed to be an internal thread connection structure, the component adopting the elastic thermal protection material to prepare the heat insulation layer has extremely unreliable sealing effect at the structural connection part, and the working reliability is greatly reduced.

In summary, the existing aluminum alloy solid rocket motor heat insulation layer assembly has the defects of narrow application range, low working reliability and the like, and an aluminum alloy solid rocket motor heat insulation layer assembly with high reliability and wide applicability is urgently needed.

Disclosure of Invention

In order to overcome the defects of the heat insulation layer assembly of the conventional aluminum alloy solid rocket engine, the invention provides a rigid full-coating type heat insulation layer assembly which can be widely applied to the field of heat protection of the aluminum alloy long-tail nozzle solid rocket engine.

In order to solve the technical problems, the scheme adopted by the invention is as follows:

the utility model provides an insulating layer subassembly suitable for long tail nozzle solid rocket engine of aluminum alloy, including preceding head heat insulation layer, the combustion chamber heat insulation layer, the spray tube heat insulation layer, the larynx lining, the expansion section heat insulation layer, adopt "L" shape overlap joint structural connection to reach sealed effect between preceding head heat insulation layer and the combustion chamber heat insulation layer, adopt "L" shape overlap joint structural connection to reach sealed effect between combustion chamber heat insulation layer and the spray tube heat insulation layer, adopt "L" shape overlap joint structural connection to reach sealed effect between spray tube heat insulation layer and the expansion section heat insulation layer, the larynx lining is connected with the expansion section heat insulation layer through embedded mode and spray tube heat insulation layer.

The heat insulating layer of the front end enclosure, the heat insulating layer of the combustion chamber, the heat insulating layer of the spray pipe and the heat insulating layer of the expansion section can be molded high silica fiber/phenolic aldehyde and also can be molded carbon fiber/phenolic aldehyde.

The throat lining material can be graphite, tungsten copper impregnated material, molded carbon fiber and phenolic aldehyde material.

The outer contour geometric structure of the front end of the heat insulating layer of the front end enclosure can be in a three-center dish-shaped mode, and can also be in a flat plate mode, an ellipsoid mode or a spherical mode and the like.

The outer contour geometric structure at the rear end of the heat insulating layer of the combustion chamber can be in a three-center dish-shaped mode, and can also be in a flat plate mode, an ellipsoid mode or a spherical mode and the like.

The length of the L-shaped lap joint structure between the heat insulating layer of the front end socket and the heat insulating layer of the combustion chamber is 10.0-20.0 mm.

The length of the L-shaped lap joint structure between the heat insulating layer of the combustion chamber and the heat insulating layer of the spray pipe is 5.0 mm-10.0 mm.

The length of the L-shaped lap joint structure between the thermal insulation layer of the spray pipe and the thermal insulation layer of the expansion section is 8.0-14.0 mm.

The length of the throat insert is 25.0 mm-35.0 mm.

The invention has the advantages that: (1) the heat insulation layer assembly is in a full-coating form, and high-temperature and high-pressure fuel gas is sealed in the heat insulation layer assembly, so that the direct contact between the fuel gas and the aluminum alloy shell is effectively avoided; (2) the heat insulation layer assembly is made of a rigid thermal protection material and can be subjected to high-precision machining; (3) the molding process of the heat insulation layer assembly is a mode of mould pressing and precise machining, batch and automatic production can be carried out, and all parts of the heat insulation layer assembly have good interchangeability; (4) the assembly manufacturability is good, only one assembling worker is needed at least, the rapid and accurate assembly can be realized, and the aluminum alloy solid rocket engine is suitable for aluminum alloy solid rocket engines with the diameter of phi 200.0mm and the length of the long tail nozzle within 150.0 mm.

Drawings

The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.

Fig. 1 is an assembly schematic of the present invention. In the figure, 1, a front seal head heat insulation layer, 2, a combustion chamber heat insulation layer, 3, a spray pipe heat insulation layer, 4, a throat liner and 5, an expansion section heat insulation layer are arranged.

Fig. 2 is a cross-sectional view of the header insulation layer.

FIG. 3 is a cross-sectional view of the combustion chamber insulation layer.

FIG. 4 is a cross-sectional view of the nozzle insulation layer.

Figure 5 is a cross-sectional view of the throat insert.

FIG. 6 is a cross-sectional view of the insulation layer of the expansion segment.

Detailed Description

The invention is further described below with reference to fig. 1 to 6.

FIG. 1 is a schematic view showing the assembly of an insulating layer assembly suitable for an aluminum alloy long tail nozzle solid rocket engine. The whole heat insulation layer assembly is in a rigid full-coating structure form, and comprises a front seal head heat insulation layer 1, a combustion chamber heat insulation layer 2, a spray pipe heat insulation layer 3, a throat liner 4, an expansion section heat insulation layer 5 and the like. Adopt "L" shape overlap joint structural connection to reach sealed effect between preceding head heat insulation layer 1 and the combustion chamber heat insulation layer 2, adopt "L" shape overlap joint structural connection to reach sealed effect between combustion chamber heat insulation layer 2 and the spray tube heat insulation layer 3, adopt "L" shape overlap joint structural connection to reach sealed effect between spray tube heat insulation layer 3 and the expansion section heat insulation layer 5. The throat insert 4 is connected with the spray pipe heat insulation layer 3 and the expansion section heat insulation layer 5 in an embedded mode

The preparation method comprises the following specific steps:

1) preparing a high-silica phenolic resin material by using a die pressing process;

2) roughly turning each part according to a drawing, wherein the roughly turned parts comprise: the heat insulation layer of the front seal head, the heat insulation layer of the combustion chamber, the heat insulation layer of the spray pipe, the throat liner, the heat insulation layer of the expansion section and the like ensure that the outer contour meets the technical requirements;

3) carrying out sand blasting on the bonding surface of the aluminum alloy shell;

4) bonding the heat insulating layer of the front end socket and the part of the front end socket into a front end socket assembly by using epoxy resin

5) Bonding the heat insulating layer of the combustion chamber and the combustion chamber part by using epoxy resin to form a combustion chamber component;

5) bonding the spray pipe heat insulation layer, the throat liner and the expansion section heat insulation layer into a whole by using environmental resin, and bonding the spray pipe heat insulation layer, the throat liner and the expansion section heat insulation layer with the spray pipe part to form a spray pipe assembly;

6) finely turning the bonded front seal head assembly, the combustion chamber assembly, the spray pipe assembly and the like according to a drawing so as to meet the technical requirements;

7) trial assembly is carried out on the bonded front seal head assembly, the combustion chamber assembly and the spray pipe assembly;

8) coating heat insulation putty on the L-shaped lapping surface of the spray pipe assembly, and then assembling the spray pipe assembly and the combustion chamber assembly;

9) and (3) coating heat insulation putty on the L-shaped lapping surface of the front end enclosure assembly, and then assembling the front end enclosure assembly with the combustion chamber assembly.

The invention is tested by a certain type of long-tail nozzle aluminum alloy engine, the working time is more than 3.0s, the design time is reached, the structure of the engine shell is complete after the work is finished, and the outer surface of the engine shell is not overheated.

The embodiments described in this specification are merely illustrative of implementations of the inventive concepts, which are intended for purposes of illustration only. The scope of the present invention should not be construed as being limited to the particular forms set forth in the examples, but rather as being defined by the claims and the equivalents thereof which can occur to those skilled in the art upon consideration of the present inventive concept.