CN113913804A - Method for manufacturing liquid rocket case, and liquid rocket - Google Patents
Method for manufacturing liquid rocket case, and liquid rocket Download PDFInfo
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- CN113913804A CN113913804A CN202111186341.9A CN202111186341A CN113913804A CN 113913804 A CN113913804 A CN 113913804A CN 202111186341 A CN202111186341 A CN 202111186341A CN 113913804 A CN113913804 A CN 113913804A
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
- B23K20/1215—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding for other purposes than joining, e.g. built-up welding
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Abstract
The invention discloses a manufacturing method of a liquid rocket shell, the liquid rocket shell and a liquid rocket, and relates to the technical field of aviation. The manufacturing method of the liquid rocket shell comprises the following steps: aluminum alloy powder is deposited on the surface of a model matrix by adopting a gas dynamic particle spraying method, and a rotor of friction stir welding is used for stirring a deposition body formed by gas dynamic particle spraying while the gas dynamic particle spraying is carried out. The method is characterized in that a friction stir welding assisted gas dynamic particle spraying process is adopted, aluminum alloy powder is used as a raw material to be deposited to form a rocket shell, a rotor of friction stir welding is used for stirring a deposition body formed by gas dynamic particle spraying while the gas dynamic particle spraying is carried out, so that powder particles with weaker interface bonding in the deposition body are subjected to plastic deformation, the interface bonding among stacked particles is optimized, the mechanical properties such as the strength of the material are improved, the rocket shell formed by deposition is an integral rocket shell, the manufacturing size is not limited, and the quality of each part is uniform.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a manufacturing method of a liquid rocket shell, the liquid rocket shell and a liquid rocket.
Background
In the process of high-speed movement of the rocket, the shell is subjected to high-speed friction with the atmosphere, and the shell needs to bear the action of gas friction, so that the shell needs to have good wear resistance and heat insulation effect. In addition, since the rocket needs to fly quickly, the weight of the casing needs to be reduced as much as possible, the casing is generally made of light materials, and the materials are required to have high strength and hardness and good toughness and plasticity.
Because of the advantages of small density, high strength, good forming performance and the like, the aviation aluminum and the aluminum alloy are widely applied to manufacturing of aerospace vehicle parts. Because the rocket shell is thin and large, when the shell is manufactured by using the traditional processing and preparation technology, small pieces of skin are manufactured, and then a large number of rivets are used for connection, so that the preparation process of the rocket shell becomes complicated and tedious, and the preparation period and the cost are increased; moreover, the mass of the obtained rocket shell structure is difficult to control, and the shell formed by connecting small blocks has poor stability compared with the integral rocket shell.
Therefore, it is needed to provide a method for forming an integrated liquid rocket shell structure with better mechanical properties, high manufacturing efficiency and low cost, so as to solve the above problems in the prior art.
Disclosure of Invention
The invention aims to provide a manufacturing method of an integrated liquid rocket shell, which aims to remarkably improve the preparation efficiency of the rocket shell and improve the mechanical property of materials and the bearing capacity of products.
The invention also aims to provide an integrated liquid rocket shell and a liquid rocket, which have better bonding strength and mechanical property.
The invention is realized by the following steps:
in a first aspect, the present invention provides a method of manufacturing an integrated liquid rocket case, comprising: aluminum alloy powder is deposited on the surface of a model matrix by adopting a gas dynamic particle spraying method, and then a deposition body formed by gas dynamic particle spraying is processed by utilizing a friction stir welding method.
In a second aspect, the present invention provides a liquid rocket case manufactured by the manufacturing method in the foregoing embodiment.
In a third aspect, the present invention provides a liquid rocket comprising the liquid rocket case of the previous embodiments.
The invention has the following beneficial effects: the inventor improves the preparation process of the liquid rocket shell, adopts the process of friction stir welding assisted with gas power particle spraying, takes aluminum alloy powder as a raw material to deposit and form the rocket shell, utilizes a rotor of friction stir welding to stir a deposition body formed by gas power spraying while spraying the gas power particles, leads the interface in the deposition body to be plastically deformed relative to weaker powder particles, so as to optimize the interface combination, improve the mechanical properties of the material, such as strength, and the like, and the rocket shell formed by deposition is an integrated rocket shell, and the quality of each part is uniform.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic diagram of a method for manufacturing a liquid rocket case structure according to an embodiment of the present disclosure;
FIG. 2 is a comparison of micro-topography before and after friction stir welding processing of aerodynamic particles spray deposited bodies;
FIG. 3 is a schematic illustration of a process for making a liquid rocket case structure provided in an embodiment of the present application;
FIG. 4 is a view of the configuration of a liquid rocket case according to an embodiment of the present application.
Icon: 001-substrate; 002-stirring head; 003-deposited body; 004-aerodynamic particle spraying apparatus.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below. The examples, in which specific conditions are not specified, were conducted under conventional conditions or conditions recommended by the manufacturer. The reagents or instruments used are not indicated by the manufacturer, and are all conventional products available commercially.
The shell of the liquid rocket is a framework structure of the rocket, and the rocket is subjected to the action of atmospheric friction and gas pressure in the high-speed flight process, so that the shell of the rocket needs high strength and hardness and has good high-temperature resistance in order to protect the internal structure from being damaged. Meanwhile, the rocket needs high running speed, so that light materials are selected as much as possible. However, the traditional process for manufacturing the rocket shell has the problems of long manufacturing period and high cost, and the splicing of the multi-ring parts is easy to cause the reduction of the product performance.
The inventor well solves the problems by improving the manufacturing method of the rocket shell and adopting the process of friction stir welding assisted with gas power particle spraying.
The embodiment of the invention provides a manufacturing method of an integrated liquid rocket shell, which comprises the following steps: aluminum alloy powder is deposited on the surface of a model matrix by adopting a gas dynamic particle spraying method, and then a deposition body formed by gas dynamic particle spraying is processed by utilizing a friction stir welding method.
The oxidation and the phase change of the deposition body can not be caused by feeding powder by utilizing a gas dynamic particle spraying technology, and the deposited deposition body is stirred by utilizing a friction stir welding rotor, so that the powder particles with weaker interface combination in the deposition body are subjected to plastic deformation to optimize the interface combination, and the integrated rocket shell structure with high hardness and high strength is prepared. The aviation aluminum and the aluminum alloy are very suitable to be used as raw materials of rocket shells due to the advantages of small density, high strength, good forming performance and the like.
Referring to fig. 1, aluminum alloy powder is deposited on the surface of a substrate 001 by a gas dynamic particle spraying apparatus 004, and a stirring process is performed on a deposition body 003 by a stirring head 002.
It is to be noted that the friction stir welding assisted gas dynamic particle spray deposition technology is divided into two steps: firstly, accelerating powder particles through an atmosphere environment to reach supersonic speed, and depositing the powder particles on the surface of a substrate in a powder solid state by a stacking compaction effect; the deposited deposit is then agitated by a friction stir welding rotor to plastically deform the powder particles within the deposit having a relatively weak interface bond to optimize the interface bond. Through the organic combination of two technologies, the gas dynamic particle spraying is favorable to improving deposition efficiency, because the temperature of deposition process is low, can not cause oxidation and the phase transition of sample raw and other materials, and friction stir welding is favorable to improving the bonding strength of the deposit body, and the quality is more even. The method for assisting the spraying and deposition of the gas dynamic particles through friction stir welding is beneficial to improving the hardness and strength of a prepared sample, can directly carry out solid deposition on powder particles, does not need excessive pretreatment and aftertreatment, and has simple preparation process and low preparation cost.
Referring to fig. 2, the left is the microstructure of the section of the gas dynamic particle spraying deposition body, and the right is the microstructure of the section of the friction stir welding treatment. The rocket shell formed by deposition in the manufacturing method in the embodiment of the application is an integrated rocket shell, and the mass of each part is uniform, so that the structure is more compact, the strength is higher and the efficiency is higher compared with the general gas dynamic particle spraying technology.
In the actual operation process, referring to fig. 3 and 4, a rocket case structure is formed on the surface of the model substrate by deposition, and then the model substrate is removed to obtain a tubular rocket case product. The specific dimensions of the rocket case are not limited to those shown in fig. 4, and the model may be established as needed before the aerodynamic particle spraying by which an aluminum alloy case of a specified size is formed.
In some embodiments, the mold base is a tubular structure, the specific dimensions of which may be determined by the specific dimensions of the rocket case, and the outer diameter of the mold base is the inner diameter of the rocket case, and the two are equal in length. The material of the model substrate is at least one selected from metal, ceramic and plastic.
The particle size range of the aluminum alloy powder has a great influence on the properties of the prepared sample, and the inventors have found that it is preferable to use an aluminum alloy powder having a particle size of 5 to 70 μm, preferably 10 to 50 μm. Because the powder is accelerated to a higher speed in the deposition process and impacts the matrix for deposition in a solid state, the acceleration effect is too poor due to the overlarge size of the powder, and the powder cannot be effectively deposited; the powder is too small in size, affected by the compression shock wave, and cannot be efficiently deposited. The hardness and strength of the prepared samples can be increased only when the powder has the proper particle size, the powder is continuously tamped to impact the matrix and the previously deposited powder particles, the particle volume shrinks, and the compactness of the prepared samples is increased.
Alternatively, the particle size of the aluminum alloy powder may be 10 μm, 15 μm, 20 μm, 25 μm, 30 μm, 35 μm, 40 μm, 45 μm, 50 μm, or the like, or may be any value between the above adjacent particle size values.
In a preferred embodiment, the aluminum alloy powder particles are preheated and then deposited; the temperature of the preheating treatment is 80-100 ℃. The preheating treatment is beneficial to reducing the moisture in the powder, increasing the fluidity of the powder and improving the deposition efficiency. Specifically, the temperature of the preheating treatment is 80 ℃, 85 ℃, 90 ℃, 95 ℃, 100 ℃ or the like.
Further, in the process of spraying the aerodynamic particles, the distance between the nozzle and the matrix of the model is controlled to be 30-50 mm. The spraying distance is controlled so that the metal powder sprayed from the nozzle can form a compact and low-porosity sample on the substrate. If the spraying distance is too small, the acting force of the sprayed metal powder impacting on the substrate is large, the nozzle is easy to damage, and the maximum deposition speed cannot be reached; if the spraying distance is too large, the speed of the sprayed metal powder impacting on the substrate is low, and the sample cannot be effectively deposited.
Alternatively, the distance from the nozzle to the mold base may be 30mm, 40mm, 50mm, or the like, or may be any value between the above adjacent distance values.
Further, in the process of spraying the aerodynamic particles, the scanning speed of the nozzle is controlled to be 400-900mm/s, and the powder feeding amount in the deposition process is 50-300 g/min. Through the control of the spraying distance, the nozzle scanning speed and the powder feeding amount, the effect of spraying the metal powder to the surface of the substrate can be improved, the deposition efficiency is improved, and the strength of the prepared product is improved.
Alternatively, the scanning speed of the nozzle is 400mm/s, 500mm/s, 600mm/s, 700mm/s, 800mm/s, 900mm/s, etc., and the powder feeding amount is 50g/min, 100g/min, 200g/min, 300g/min, etc.
In the preferred embodiment, the distance between the nozzle and the model substrate is controlled to be 10-40mm during the pneumatic particle spraying process, the scanning speed of the nozzle is 5-100mm/s, and the powder feeding amount during the deposition process is 50-300 g/min. By further optimizing the spraying distance, the nozzle scanning speed and the powder feeding amount, the strength and the mechanical property of the product can be further improved.
Further, in the friction stir welding process, the rotating speed of a main shaft of the friction stir welding is controlled to be 700-900rpm, the diameter of a stirring pin is 4-5mm, the diameter of a shaft shoulder is 10-12mm, and the moving speed is 5-100 mm/s. The process conditions are matched with the gas dynamic particle spraying process conditions, so that the bonding strength of the gas dynamic particle spraying sediment body can be improved, and the quality of a sample is more uniform.
Alternatively, the rotational speed of the spindle of friction stir welding is 700rpm, 800rpm, 900rpm, etc., the pin diameter is 4mm, 4.5mm, 5mm, etc., and the shoulder diameter is 10mm, 11mm, 12mm, etc.
The embodiment of the invention also provides the liquid rocket shell which is manufactured by the manufacturing method of the liquid rocket shell, the manufacturing period is short, the cost is low, and more importantly, the strength and the bonding force of the shell are more ideal.
The embodiment of the invention also provides a liquid rocket, which comprises the liquid rocket shell, and the strength of the shell is improved through the improvement of the shell manufacturing process, so that the performance of the whole liquid rocket is improved.
The features and properties of the present invention are described in further detail below with reference to examples.
Example 1
The present embodiment provides a method for manufacturing an integrated liquid rocket case, please refer to fig. 1, fig. 3 and fig. 4, including: modeling is carried out according to the size of the rocket shell, and the process of spraying the aerodynamic particles is guided; tubular aluminum metal is used as a model matrix, aluminum alloy powder is deposited on the surface of the model matrix by a gas dynamic particle spraying method, and a rotor of friction stir welding is used for stirring a deposition body formed by gas dynamic particle spraying while the gas dynamic particle spraying is carried out. The method comprises the steps of firstly forming a rocket shell structure on the surface of a model matrix through the friction stir welding assisted gas dynamic particle spraying process, and then removing the model matrix to obtain a tubular rocket shell product.
The technical process and parameters are as follows: selecting aluminum alloy powder with the grain diameter of 10-50 mu m, preheating the aluminum alloy powder at the temperature of 80 ℃, starting a spraying device, scanning back and forth on a model substrate, and depositing to form a rocket shell structure. Wherein, the distance from the nozzle to the substrate is set to be 30mm during the gas dynamic particle spraying, the scanning speed is 400mm/s, and the powder feeding amount is 100 g/min. The rotation speed of a main shaft of the friction stir welding is 700rpm, the diameter of a stirring pin is 4mm, the diameter of a shaft shoulder is 10mm, and the moving speed is 20 mm/s.
Example 2
The embodiment provides a manufacturing method of an integrated liquid rocket shell, which is different from the embodiment 1 only in parameter control, and specifically comprises the following steps:
selecting aluminum alloy powder with the particle size range of 10-50 mu m, preheating the aluminum alloy powder at 90 ℃, starting a spraying device, scanning back and forth on a model substrate, and depositing to form a rocket shell structure. Wherein, the distance from the nozzle to the substrate is set to be 30mm during the gas dynamic particle spraying, the scanning speed is 500mm/s, and the powder feeding amount is 200 g/min. The rotation speed of a main shaft of the friction stir welding is 800rpm, the diameter of a stirring pin is 4mm, the diameter of a shaft shoulder is 10mm, and the moving speed is 20 mm/s.
Example 3
The embodiment provides a manufacturing method of an integrated liquid rocket shell, which is different from the embodiment 1 only in parameter control, and specifically comprises the following steps:
selecting aluminum alloy powder with the particle size range of 10-50 mu m, preheating the aluminum alloy powder at 100 ℃, starting a spraying device, scanning back and forth on a model substrate, and depositing to form a rocket shell structure. Wherein, the distance from the nozzle to the substrate is set to be 40mm during the gas dynamic particle spraying, the scanning speed is 400mm/s, and the powder feeding amount is 300 g/min. The rotation speed of a main shaft of the friction stir welding is 900rpm, the diameter of a stirring pin is 4mm, the diameter of a shaft shoulder is 10mm, and the moving speed is 40 mm/s.
Example 4
The embodiment provides a manufacturing method of an integrated liquid rocket shell, which is different from the embodiment 1 only in parameter control, and specifically comprises the following steps:
selecting aluminum alloy powder with the particle size range of 10-50 mu m, preheating the aluminum alloy powder at 100 ℃, starting a spraying device, scanning back and forth on a model substrate, and depositing to form a rocket shell structure. Wherein, the distance from the nozzle to the substrate is set to be 40mm during the gas dynamic particle spraying, the scanning speed is 500mm/s, and the powder feeding amount is 300 g/min. The rotation speed of a main shaft of the friction stir welding is 900rpm, the diameter of a stirring pin is 4mm, the diameter of a shaft shoulder is 11mm, and the moving speed is 50 mm/s.
Example 5
The embodiment provides a manufacturing method of an integrated liquid rocket shell, which is different from the embodiment 1 only in parameter control, and specifically comprises the following steps:
selecting aluminum alloy powder with the particle size range of 10-50 mu m, preheating the aluminum alloy powder at 100 ℃, starting a spraying device, scanning back and forth on a model substrate, and depositing to form a rocket shell structure. Wherein, the distance from the nozzle to the substrate is set to be 40mm during the gas dynamic particle spraying, the scanning speed is 600mm/s, and the powder feeding amount is 300 g/min. The rotation speed of a main shaft of the friction stir welding is 900rpm, the diameter of a stirring pin is 5mm, the diameter of a shaft shoulder is 11mm, and the moving speed is 50 mm/s.
Example 6
The embodiment provides a manufacturing method of an integrated liquid rocket shell, which is different from the embodiment 1 only in parameter control, and specifically comprises the following steps:
selecting aluminum alloy powder with the particle size range of 10-50 mu m, preheating the aluminum alloy powder at 100 ℃, starting a spraying device, scanning back and forth on a model substrate, and depositing to form a rocket shell structure. Wherein, the distance from the nozzle to the substrate is set to be 40mm during the gas dynamic particle spraying, the scanning speed is 600mm/s, and the powder feeding amount is 300 g/min. The rotation speed of a main shaft of the friction stir welding is 900rpm, the diameter of a stirring pin is 5mm, the diameter of a shaft shoulder is 12mm, and the moving speed is 50 mm/s.
Comparative example 1
This comparative example provides a method of manufacturing an integrated liquid rocket case, which differs from example 1 only in that friction stir welding is not used for assistance in the process.
Comparative example 2
The comparative example provides a manufacturing method of an integrated liquid rocket shell, a traditional forging method is adopted to prepare a rocket shell structure, and reference can be specifically made to the following documents: korean Qingbo, Li chapter, Mascara, etc. the processing method of the multi-joint rocket shell is CN110732844A [ P ] 2020.
Comparative example 3
The comparative example provides a manufacturing method of an integrated liquid rocket shell, which is different from the embodiment 1 only in parameter control and specifically comprises the following steps: the scanning speed in the deposition process is 700mm/s, the powder feeding amount is 50g/min, the rotating speed of a main shaft of the friction stir welding is 200rpm, and the moving speed is 200 mm/s.
Comparative example 4
The comparative example provides a manufacturing method of an integrated liquid rocket shell, which is different from the embodiment 1 only in parameter control and specifically comprises the following steps: the scanning speed in the deposition process is 700mm/s, the powder feeding amount is 600g/min, the rotating speed of a main shaft of the friction stir welding is 100rpm, and the moving speed is 400 mm/s.
Test example 1
The microscopic morphologies of the products obtained in example 1 and comparative example 1 were tested, and the results are shown in FIG. 2. It can be seen that the structure of the product is denser after the friction stir welding process.
Test example 2
The service performance of the examples and the comparative examples is tested, and the test method refers to GB/T35777-2017.
The results show that the service performance of the rocket shell provided by the examples 1-6 is obviously better than that of the comparative example, and the prepared sample of the liquid rocket shell structure prepared by the friction stir welding assisted gas dynamic particle spraying deposition technology has higher bonding strength, uniform quality, shorter manufacturing period and lower economic cost.
Test example 3
The comprehensive properties of the products obtained in the test examples and the comparative examples, such as strength and hardness, are tested according to the test method GB/T35777-2017, and the test results are shown in Table 1.
TABLE 1 rocket case Performance test results
As can be seen from Table 1, the rocket shell prepared by the method of the embodiment of the invention has more excellent comprehensive performance, which is obviously better than that of the comparative example.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A method of manufacturing an integrated liquid rocket case, comprising: aluminum alloy powder is deposited on the surface of a model matrix by adopting a gas dynamic particle spraying method, and then a deposition body formed by gas dynamic particle spraying is processed by utilizing a friction stir welding method.
2. The method of manufacturing according to claim 1, wherein the structure of the rocket case is formed by deposition on the surface of the mold base, and then the mold base is removed to obtain a tubular rocket case product.
3. The method of manufacturing of claim 2, wherein the mold base is a tubular structure.
4. The manufacturing method according to claim 3, wherein the material of the mold base is at least one selected from the group consisting of metal, ceramic, and plastic.
5. A manufacturing method according to any one of claims 1 to 4, characterized in that the particle size of the aluminum alloy powder is 5-70 μm, preferably 5-45 μm.
6. The manufacturing method according to claim 5, wherein the aluminum alloy powder particles are subjected to a preheating treatment and then to deposition;
preferably, the temperature of the preheating treatment is 80 to 100 ℃.
7. The manufacturing method as claimed in claim 5, wherein during the spraying of the aerodynamic particles, the distance from the nozzle to the model substrate is controlled to be 30-50mm, the scanning speed of the nozzle is 400-900mm/s, and the powder feeding amount during the deposition process is 50-300 g/min;
preferably, in the process of spraying the aerodynamic particles, the distance from the nozzle to the model substrate is controlled to be 10-40mm, the scanning speed of the nozzle is 5-100mm/s, and the powder feeding amount in the deposition process is 50-300 g/min.
8. The manufacturing method according to claim 5, wherein during the friction stir welding, the rotation speed of the spindle of the friction stir welding is controlled to 700-900rpm, the diameter of the stirring pin is 4-5mm, the diameter of the shoulder is 10-12mm, and the moving speed is 5-100 mm/s.
9. A liquid rocket case manufactured by the manufacturing method of any one of claims 1 to 8.
10. A liquid rocket comprising the liquid rocket case of claim 9.
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