CN106050477B - Combined throat insert spray pipe of solid rocket engine and manufacturing method - Google Patents
Combined throat insert spray pipe of solid rocket engine and manufacturing method Download PDFInfo
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- CN106050477B CN106050477B CN201610623732.5A CN201610623732A CN106050477B CN 106050477 B CN106050477 B CN 106050477B CN 201610623732 A CN201610623732 A CN 201610623732A CN 106050477 B CN106050477 B CN 106050477B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/974—Nozzle- linings; Ablative coatings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/50—Building or constructing in particular ways
- F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
Abstract
The invention discloses a combined throat insert nozzle of a solid rocket engine and a manufacturing method thereof, wherein the nozzle comprises an axisymmetric solid of revolution structure part: the nozzle comprises a converging section heat insulation layer, a throat liner, a back lining, a diffusing section heat insulation layer and a nozzle shell, wherein all the parts are mutually connected and sealed by steps formed by axial cylindrical surfaces and end surfaces to form the nozzle, the throat liner is a combined throat liner and is formed by combining a plurality of throat filler blocks in a step-type connection and sealing mode. The throat insert is divided into a plurality of throat insert blocks with specific structural forms by the integral throat insert, every two throat insert blocks are connected and sealed by an assembling process to form a combined throat insert, and then the combined throat insert and other axisymmetric solid structure parts of the nozzle are assembled into the nozzle according to the existing corresponding assembling mode. The raw materials can be effectively saved, and the process preparation and processing cost can be reduced; meanwhile, the size of the independent throat insert is reduced, the thickness is reduced, so that the carburization is uniform, and the quality consistency of the product is easier to guarantee.
Description
Technical Field
The invention belongs to the field of solid rocket engines, and particularly relates to a combined throat insert spray pipe of a solid rocket engine and a manufacturing method thereof.
Background
The throat diameter of the corresponding spray pipe of the existing large-diameter solid rocket engine is large, namely the throat lining of the spray pipe is also large, the throat lining of the spray pipe is generally an integral throat lining, the integral production and machining molding are carried out, the structure is an axisymmetric solid-of-revolution structure, the inner molded surface of the throat lining is a first convergent and then divergent molded surface, the end surface of the outer molded surface is connected with other axisymmetric solid-of-revolution structure components of the spray pipe, the parts comprise a convergent section heat insulation layer, a back lining, a divergent section heat insulation layer and a spray pipe shell, the steps formed by axial cylindrical surfaces and end surfaces are mutually connected and sealed to assemble the spray pipe, and the back wall surface of the outer.
For the large-size integral throat insert, due to the limitation of a manufacturing process and equipment, when the throat insert reaches the size of a certain bottleneck, the process difficulty and complexity are greatly increased, the quality consistency of a formed product is poor, the defects of nonuniform carburization, more carbon-rich areas, large material strength dispersion and the like may exist, and the consistency is difficult to guarantee anyway. Meanwhile, along with the increase of the size, the production equipment and the processing equipment are modified and invested, and high cost is caused.
Disclosure of Invention
The invention aims to provide a combined throat insert nozzle of a solid rocket engine and a manufacturing method thereof. The size of the single throat lining block is small, and the quality consistency of the throat lining block can be ensured by the conventional processing technology.
In order to achieve the above object, the present invention provides a combined throat insert nozzle of a solid rocket engine, comprising axisymmetric solid of revolution structural components: convergent section heat insulation layer, throat insert, back lining, diffuser section heat insulation layer, spray tube casing, the step that constitutes with axial cylinder face and terminal surface links up each other between each parts and seals up and assemble into the spray tube, its characterized in that: the throat insert is a combined throat insert and is formed by combining a plurality of throat insert blocks in a step-type connection and sealing mode.
Optionally, the throat pad block is an axial throat pad block divided along the axial direction, and an L-shaped step turning and bending gap is adopted between the axial throat pad blocks, and the turning is not less than 3 times.
Optionally, the throat pad is a radial throat pad divided in the radial direction, and the radial throat pads are connected and sealed by an "L" -shaped step turning gap, and the turning is not less than 3 times.
Preferably, the throat filler blocks are divided into two directional throat filler blocks in the axial direction and the radial direction, the gap between the two directional throat filler blocks is designed into a zigzag turning gap with an L-shaped step, the butt joint gaps of the matching surfaces are not in the same generatrix direction, and are staggered by a certain angle theta in the radial direction, and the angle theta is more than or equal to 0 degrees and less than or equal to 90 degrees, so that the two directional throat filler blocks are connected and sealed.
The invention provides a manufacturing method of a combined throat insert nozzle of a solid rocket engine, which comprises the step of mutually connecting and sealing structures formed by axial cylindrical surfaces and end surfaces among a heat insulating layer of a convergent section, a throat insert, a back lining, a heat insulating layer of a divergent section and a nozzle shell of an axisymmetric revolving body structure part, and is characterized by also comprising the following steps of,
manufacturing the throat filler block: designing and manufacturing a plurality of throat filler blocks, determining the specific structural forms of the plurality of throat filler blocks through the analysis of the ablation performance of the throat liners, the structural sealing reliability, the thermal stress of the throat liners and the interface contact stress among the throat liner blocks in various aspects, and manufacturing the plurality of throat filler blocks by utilizing the existing process;
assembling the throat insert: and assembling a plurality of throat lining blocks into a throat lining in a stepped connection and sealing manner.
Optionally, the step of fabricating the plurality of throat insert blocks comprises,
manufacturing an axial throat filler block: designing and manufacturing a plurality of throat filler blocks, determining that the specific structural form of the plurality of throat filler blocks is an axial throat filler block which is axially divided through the analysis of the ablation performance of the throat filler, the structural sealing reliability, the thermal stress of the throat filler and the interface contact stress between the throat filler blocks in various aspects, wherein L-shaped step turning and bending gaps are adopted among the axial throat filler blocks, the reserved value a of the gaps is determined through the thermal stress analysis, the number of turns is not less than 3, and the plurality of throat filler blocks are manufactured by utilizing the conventional process;
assembling the throat insert: the axial throat lining blocks are all arranged in L-shaped step turning and bending gaps, the turning is not less than 3 times, ablation-resistant sealant is filled in the gaps, and a special tool is adopted to pressurize, join and seal to assemble the throat lining.
Optionally, the step of fabricating the plurality of throat insert blocks comprises,
manufacturing a radial throat filler block: designing and manufacturing a plurality of throat filler blocks, determining that the specific structural form of the throat filler blocks is radial throat filler blocks which are divided along the radial direction through the analysis of the ablation performance of the throat liners, the structural sealing reliability, the thermal stress of the throat liners and the interface contact stress between the throat liner blocks in various aspects, performing joint sealing between the radial throat filler blocks by adopting L-shaped step turning gaps, determining a gap reserved value a through the thermal stress analysis, turning for not less than 3 times, and manufacturing the plurality of throat filler blocks by utilizing the conventional process;
assembling the throat insert: the radial throat lining blocks are all arranged in L-shaped step turning and bending gaps, the turning is not less than 3 times, ablation-resistant sealant is filled in the gaps, and special tools are adopted to pressurize, join and seal to form the throat lining.
Preferably, the manufacturing steps of the throat insert blocks comprise,
the manufacturing method of the two-way laryngeal lining block comprises the following steps: designing and manufacturing a plurality of throat filler blocks, determining that the specific structural form of the plurality of throat filler blocks is divided into two-way throat filler blocks along the axial direction and the radial direction through the analysis of the ablation performance of the throat liners, the structural sealing reliability, the thermal stress of the throat liners and the interface contact stress between the throat liner blocks in various aspects, designing the gap between the two-way throat filler blocks into a zigzag turning gap of an L-shaped step, staggering a certain angle theta along the radial direction when the butt gap of matching surfaces is not in the same bus direction, and determining a clearance reserved value a through the thermal stress analysis by utilizing the existing process;
assembling the throat insert: the gap between two directional throat filler blocks is designed into a zigzag turning gap of an L-shaped step, the butt joint gaps of the matching surfaces are not in the same bus direction, a certain angle theta is staggered along the radial direction, the reserved value a of the gap is determined by thermal stress analysis, ablation-resistant sealant is filled in the gap, and the throat lining is assembled by adopting a special tool to pressurize, join and seal.
The throat insert is divided into a plurality of throat insert blocks with specific structural forms by the original integral throat insert, every two throat insert blocks are connected and sealed by an assembling process to form a combined throat insert, and then the combined throat insert and other axisymmetric solid structure parts of the nozzle are assembled into the nozzle according to the existing corresponding assembling mode. The volume of the single throat liner block is reduced, so that the production and processing difficulty of the throat liner is effectively reduced; because the requirement on the size of the blank is also reduced, the raw materials can be effectively saved, and the process preparation and processing cost is also reduced; meanwhile, the size of the independent throat insert is reduced, the thickness is reduced, so that the carburization is uniform, and the quality consistency of the product is easier to guarantee.
Drawings
FIG. 1 is a schematic view of the construction of a modular throat insert nozzle of the solid rocket engine of the present invention;
FIG. 2 is a schematic structural view of a throat insert composed of axial throat insert blocks;
FIG. 3 is a schematic view of the cross-sectional structure of FIG. 2;
FIG. 4 is a schematic diagram of a throat insert explosion structure composed of axial throat insert blocks;
FIG. 5 is a schematic diagram of a throat insert structure composed of radial throat insert blocks;
FIG. 6 is a schematic view of FIG. 5 taken along line B;
FIG. 7 is a schematic diagram of a throat insert explosion structure composed of radial throat insert blocks;
FIG. 8 is a schematic view of a throat insert structure composed of two directional throat insert blocks;
FIG. 9 is a schematic diagram of a throat insert explosion structure composed of two-way throat insert blocks;
in the figure: 1-a heat insulating layer of a convergent section; 2-throat liner; 21-larynx lining block; 211-axial throat mass; 212-radial throat block; 213-two-way laryngeal pad; 3-backing; 4-diffusion section heat insulating layer; 5-a shell; 9-step; 10-gap.
Detailed Description
The following further describes embodiments of the present invention with reference to the drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Embodiment 1, as shown in fig. 1, 2, 3, and 4, a composite throat insert nozzle for a solid rocket engine includes an axisymmetric solid of revolution structural member: the nozzle comprises a convergence section heat insulation layer (1), a throat liner (2), a back lining (3), a diffusion section heat insulation layer (4) and a nozzle shell (5), wherein the parts are mutually connected and sealed to form the nozzle through steps (9) formed by axial cylindrical surfaces and end surfaces, the throat liner (2) is a combined throat liner and is formed by combining a plurality of throat filler blocks (21) in a step (9) type connection and sealing mode.
In the embodiment, the throat pads (21) are axial throat pads (211) divided along the axial direction, and the specific number of the throat pads (21) can be adjusted according to the actual size and the capacity condition of the product equipment, and is 3 in the embodiment; the L-shaped step bending zigzag gaps 10 are adopted among the axial throat pads (211) for less than 3 times. The gas direction of clearance 10 is perpendicular or deviates from the gas direction for the gas stream can not directly get into clearance 10, even the gas gets into clearance 10, leads to the fact "dead zone" through tortuous clearance 10, can avoid appearing wearing the fire phenomenon, with the sealed reliable after guaranteeing the throat lining piecemeal.
The gap 10 has a certain width value, i.e. a gap reserve a.
In the embodiment, the throat blocks (21) are radial throat blocks (212) which are divided along the radial direction, and the specific number of the throat blocks (21) can be adjusted according to the actual size and the capacity condition of the product equipment, and the number is 3 in the embodiment; the radial throat filler blocks (212) are connected and sealed by adopting L-shaped step turning gaps, and the turning is not less than 3 times. The direction of the gap 10 is perpendicular to the direction of the gas or deviates from the direction of the gas, so that the gas flow can not directly enter the gap 10, even if the gas enters the gap 10, a 'dead zone' is caused by the zigzag gap 10, the fire penetrating phenomenon can be avoided, and the throat insert is sealed and reliable after being partitioned.
The gap 10 has a certain width value, i.e. a gap reserve a.
In the embodiment, the throat pads (21) are divided into two directional throat pads (213) along the axial direction and the radial direction, the specific number of the throat pads (21) can be adjusted according to the actual size and the capacity of the product and equipment, the number of the throat pads is 9 in the embodiment, the throat pads are divided into 3 sections along the axial direction, and the throat pads are divided into 3 sections along the radial direction; the gap 10 between the two-way throat filler blocks (213) is designed into a zigzag gap 10 with an L-shaped step, in the embodiment, the matching surfaces, including M surfaces, N surfaces and 0 surfaces, of the butt joint gap 10 are not in the same generatrix direction, and are staggered by a certain angle theta along the radial direction, wherein theta is more than or equal to 0 degrees and less than or equal to 90 degrees, specifically theta is 30 degrees, so that the two-way throat filler blocks (213) are connected and sealed.
The gap 10 has a certain width value, i.e. a gap reserve a.
the manufacturing method of the throat filler block (21) comprises the following steps: designing and manufacturing a plurality of throat filler blocks (21), determining the specific structural form of the plurality of throat filler blocks (21) through the analysis of the ablation performance of the throat liners, the structural sealing reliability, the thermal stress of the throat liners and the interface contact stress among the throat liner blocks in various aspects, and manufacturing the plurality of throat filler blocks (21) by utilizing the existing process;
assembling the throat insert (2): and a plurality of throat filler blocks (21) are assembled into the throat liner (2) in a step-type connection and sealing mode.
an axial throat pad (211) manufacturing step: designing and manufacturing a plurality of throat filler blocks (21), determining that the specific structural form of the throat filler blocks (21) is an axial throat filler block (211) divided along the axial direction through the analysis of the ablation performance of the throat liners, the structural sealing reliability, the thermal stress of the throat liners and the interface contact stress among all the throat filler blocks in various aspects, wherein L-shaped step turning zigzag gaps 10 are adopted among the axial throat filler blocks (211), the clearance reservation value a of the A, B, D, E, F surface of a matching surface between the throat filler blocks (211) is determined through the thermal stress analysis, the turning is not less than 3 times, and the throat filler blocks (21) are manufactured by utilizing the existing process;
assembling the throat insert (2): l-shaped step bending gaps 10 are adopted among the axial throat filler blocks (211), the bending is not less than 3 times, the gaps 10 of the matching surfaces A, B, D, E, F are filled with ablation-resistant sealant D03 ablation-resistant sealing putty, and the assembly in place is based on the fact that the putty is extruded from the gaps. The surface G, H of the back lining 2 is coated with the iron anchor 101 glue to prevent the combined laryngeal pad 1 from falling off. The throat liner (2) is assembled by adopting a special tool to pressurize, join and seal.
Embodiment 6, a method for manufacturing a combined throat insert nozzle of a solid rocket motor corresponding to embodiment 2, comprising the step of assembling a sealing structure in which axial cylindrical surfaces and end surfaces form steps to be connected with each other between a heat insulating layer (1) at a convergent section, a throat insert (2), a backing (3), a heat insulating layer (4) at a divergent section and a nozzle shell (5) of an axisymmetric solid-of-revolution structure component, further comprising,
the manufacturing steps of the radial throat block (212) are as follows: designing and manufacturing a plurality of throat pads (21), determining that the specific structural form of the throat pads (21) is a radial throat pad (212) divided along the axial direction through various comparison analyses including throat lining ablation performance, structural sealing reliability, throat lining thermal stress and interface contact stress analysis among all throat pad blocks, wherein L-shaped step turning zigzag gaps 10 are adopted among the radial throat pads (212), a gap reserved value a of a matching surface A, B, D, E surface among all the radial throat pads (212) is determined through thermal stress analysis, turning is not less than 3 times, and manufacturing the plurality of throat pads (21) by utilizing the existing process;
assembling the throat insert (2): the radial throat filler blocks (212) are all provided with L-shaped step bending gaps 10, the bending is not less than 3 times, the gaps 10 of the matching surfaces J, L are filled with ablation-resistant sealant D03 ablation-resistant sealing putty, and the assembling in place is based on the fact that the putty is extruded from the gaps. And (3) attaching the surface K of the axial matching surface, and coating an iron anchor-101 adhesive. The throat liner (2) is assembled by adopting a special tool to pressurize, join and seal.
Embodiment 7, which corresponds to embodiment 3, is a method for manufacturing a combined throat insert nozzle of a solid rocket engine, comprising an assembling step of mutually connecting and sealing structures by steps formed by axial cylindrical surfaces and end surfaces among a heat insulating layer (1) at a convergent section, a throat insert (2), a backing (3), a heat insulating layer (4) at a divergent section and a nozzle shell (5) of axisymmetric solid-of-revolution structural components, and further comprising,
the manufacturing method of the two-way laryngeal pad (213) comprises the following steps: designing and manufacturing a plurality of throat pads (21), determining that the specific structural form of the plurality of throat pads (21) is divided into two-way throat pads (213) along the axial direction and the radial direction through the multi-aspect comparison analysis of the ablation performance of the throat lining, the structural sealing reliability, the thermal stress of the throat lining and the interface contact stress analysis between the two-way throat pads (213), wherein the two-way throat pads (213) are all provided with L-shaped step turning zigzag gaps 10, the matching surfaces between the two-way throat pads (213), the butt joint gaps 10 comprising M surfaces, N surfaces and O surfaces are not in the same bus direction, the angles theta are staggered in the radial direction by a certain angle theta, the theta is more than or equal to 0 degree and less than or equal to 90 degrees, the theta is specifically 30 degrees, the reserved gap value a is determined by the thermal stress analysis, the turning is not less than 3 times, and manufacturing the plurality of throat pads (21) by utilizing the;
assembling the throat insert (2): the radial throat filler blocks (213) are all provided with L-shaped step bending gaps 10, the bending is not less than 3 times, the gaps 10 between the matching surfaces M, N and 0 surface are filled with ablation-resistant sealant D03 ablation-resistant sealing putty, and the assembly in place is based on the fact that the putty is extruded from the gaps. The axial matching surfaces are jointed and coated with an iron anchor-101 adhesive. The throat liner (2) is assembled by adopting a special tool to pressurize, join and seal.
In the jet pipe of the solid rocket engine of a certain type in the embodiment, the maximum working pressure of the engine is 7.4MPa, and the working time is 72 s.
The throat diameter of the throat liner (2) is 325mm, the inner diameter of the outlet of the thermal insulation layer (4) of the diffuser section of the nozzle is 2150mm, and the expansion ratio is 43.8. The total length of the nozzle is 2180 mm.
The maximum outer diameter of the throat insert (2) is 585mm, and the specific structure form of the throat pad (21) adopts a two-way throat pad (213) which is divided along the axial direction and the radial direction and is shown in figures 8 and 9.
In order to determine the optimal value of a clearance reserved value a between two-way throat filler blocks (213), a finite element analysis model of two-way throat liner blocks (213) of the nozzle is established by adopting finite element simulation analysis software MSC.Patran/Nastran, a one-dimensional gap unit is adopted to simulate a clearance 10 between throat liner bonding interfaces, external load and temperature boundary conditions of the nozzle are applied, firstly, transient heat transfer analysis is carried out on a temperature field of the nozzle in 72s working time, a heat transfer analysis result is used as a temperature load of thermal stress analysis, thermal stress of the nozzle and a contact stress value of the throat liner clearance 10 are analyzed, and the thermal stress value is compared with a stress value of the integral throat liner (2), so that the clearance reserved value a between the two-way throat filler blocks (213) is determined to be (0.10-0.15) mm, and a certain radial angle theta is staggered to be 30 degrees.
Claims (4)
1. A combined throat insert nozzle for a solid rocket engine, comprising an axisymmetric solid of revolution structural member: convergent section heat insulation layer (1), throat insert (2), backing (3), diffuser heat insulation layer (4), spray tube casing (5), step (9) that constitute with axial cylinder face and terminal surface link up each other between each part and seal assembly become the spray tube, its characterized in that: the throat insert (2) is a combined throat insert and is formed by combining a plurality of throat insert blocks (21) in a step (9) type connection and sealing mode;
the throat filler block (21) is an axial throat filler block (211) divided along the axial direction, L-shaped step turning zigzag gaps are adopted among the axial throat filler blocks (211), and the turning is not less than 3 times.
2. The solid rocket engine modular throat insert nozzle of claim 1 wherein: the throat filler block (21) is divided into two directional throat filler blocks (213) along the axial direction and the radial direction, a gap between the two directional throat filler blocks (213) is designed into a zigzag gap of an L-shaped step, a butt joint gap of a matching surface is not in the same generatrix direction, and a certain angle theta is staggered along the radial direction, wherein the theta is more than or equal to 0 degree and less than or equal to 90 degrees, so that the two directional throat filler blocks (213) are connected and sealed.
3. A manufacturing method of a combined throat liner spray pipe of a solid rocket engine comprises a heat insulation layer (1) of a convergent section of an axisymmetric revolution body structure component, a throat liner (2), a back lining (3), a heat insulation layer (4) of a diffusion section and a spray pipe shell (5), wherein the components are mutually connected and sealed to assemble the spray pipe by steps formed by axial cylindrical surfaces and end surfaces,
the manufacturing method of the throat filler block (21) comprises the following steps: designing and manufacturing a plurality of throat filler blocks (21), determining the specific structural form of the plurality of throat filler blocks (21) through the analysis of the ablation performance of the throat liners, the structural sealing reliability, the thermal stress of the throat liners and the interface contact stress among the throat liner blocks in various aspects, and manufacturing the plurality of throat filler blocks (21) by utilizing the existing process;
assembling the throat insert (2): a plurality of throat filler blocks (21) are assembled into a throat liner (2) in a step-type connection and sealing mode;
the block throat block (21) manufacturing step includes,
an axial throat pad (211) manufacturing step: designing and manufacturing a plurality of throat filler blocks (21), determining that the specific structural form of the throat filler blocks (21) is an axial throat filler block (211) divided along the axial direction through the analysis of the ablation performance of the throat liners, the structural sealing reliability, the thermal stress of the throat liners and the interface contact stress among all the throat liner blocks in various aspects, wherein L-shaped step turning zigzag gaps are adopted among the axial throat filler blocks (211), the reserved value a of the gaps is determined through the thermal stress analysis, the turning is not less than 3 times, and the plurality of throat filler blocks (21) are manufactured by utilizing the existing process;
assembling the throat insert (2): l-shaped step turning zigzag gaps are adopted among the axial throat filler blocks (211), the turning is not less than 3 times, ablation-resistant sealant is filled in the gaps, and special tools are adopted to pressurize, join and seal to assemble the throat lining (2).
4. A method of manufacturing a combined throat insert nozzle for a solid rocket engine according to claim 3 wherein the throat insert (21) manufacturing step comprises,
the manufacturing method of the two-way laryngeal pad (213) comprises the following steps: designing and manufacturing a plurality of throat filler blocks (21), determining that the specific structural form of the plurality of throat filler blocks (21) is a two-way throat filler block (213) which is divided along the axial direction and the radial direction through the analysis of the ablation performance of the throat liners, the structural sealing reliability, the thermal stress of the throat liners and the interface contact stress among the throat filler blocks in multiple aspects, designing the gap between the two-way throat filler blocks (213) into a zigzag gap with an L-shaped step, wherein the butt joint gap of the matching surfaces is not in the same bus direction, and is staggered by a certain angle theta along the radial direction, the reserved value a of the gap is determined by the thermal stress analysis, and the plurality of throat filler blocks (21) are manufactured by utilizing the existing process;
assembling the throat insert (2): the clearance between the two-way throat filler blocks (213) is designed into a zigzag clearance of an L-shaped step, the butt joint clearance of the matching surfaces is not in the same bus direction, a certain angle theta is staggered along the radial direction, theta is more than or equal to 0 degree and less than or equal to 90 degrees, the clearance reservation value a is determined by thermal stress analysis, ablation-resistant sealant is filled in the clearance, and the throat lining (2) is assembled by adopting a special tool to pressurize, join and seal.
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| CN201610623732.5A CN106050477B (en) | 2016-07-28 | 2016-07-28 | Combined throat insert spray pipe of solid rocket engine and manufacturing method |
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|---|---|---|---|---|
| CN202360245U (en) * | 2011-11-21 | 2012-08-01 | 湖北航天技术研究院总体设计所 | Simplified combined nozzle structure of engine |
| CN202596924U (en) * | 2012-04-18 | 2012-12-12 | 湖北航天技术研究院总体设计所 | Sectioned long exhaust nozzle structure for solid rocket engine |
| CN104612858B (en) * | 2015-01-29 | 2016-09-21 | 南京理工大学 | Adjustable Double pulse solid rocket motor nozzle test device |
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2016
- 2016-07-28 CN CN201610623732.5A patent/CN106050477B/en active Active
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| Publication number | Publication date |
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| CN106050477A (en) | 2016-10-26 |
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