CN110103378B - Nested grain forming system and method for solid-liquid rocket engine - Google Patents
Nested grain forming system and method for solid-liquid rocket engine Download PDFInfo
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- CN110103378B CN110103378B CN201910300568.8A CN201910300568A CN110103378B CN 110103378 B CN110103378 B CN 110103378B CN 201910300568 A CN201910300568 A CN 201910300568A CN 110103378 B CN110103378 B CN 110103378B
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Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C41/00—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor
- B29C41/02—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor for making articles of definite length, i.e. discrete articles
- B29C41/04—Rotational or centrifugal casting, i.e. coating the inside of a mould by rotating the mould
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C41/00—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor
- B29C41/02—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor for making articles of definite length, i.e. discrete articles
- B29C41/20—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor for making articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. moulding inserts or for coating articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C41/00—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor
- B29C41/34—Component parts, details or accessories; Auxiliary operations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C41/00—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor
- B29C41/34—Component parts, details or accessories; Auxiliary operations
- B29C41/52—Measuring, controlling or regulating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/20—Fuel-blocks, e.g. nuclear fuel elements
Abstract
The invention discloses a nested grain forming method of a solid-liquid rocket engine, which comprises the following steps: designing and printing a 3D nested type grain structure substrate; preparing a grain fuel, and mixing and melting the grain filling fuel according to the proportion; assembling a mould, and loading the nested grain structure matrix into a shaping mould; centrifugally nesting and molding, namely pouring the explosive column fuel into a mold, and rotationally molding by using a centrifugal machine; post-treating the explosive column, polishing and trimming the head end and the tail end of the explosive column; the nested grain forming system comprises a 3D matrix printing module, a fuel melting stirrer, a constant-temperature conveying pipeline, a grain mold and a centrifugal forming machine, wherein a grain structural matrix printed by the 3D matrix printing module is loaded into the grain mold, the fuel melting stirrer heats and melts fuel, the molten fuel enters the grain mold through the constant-temperature conveying pipeline and generates required grains under the rotation action of the centrifugal forming machine; can realize the rapid molding of the nested type grain, and has low cost and high efficiency.
Description
Technical Field
The invention relates to the field of rocket engines, in particular to a nested grain forming system and a method of a solid-liquid rocket engine.
Background
The rocket engine can be used for propelling a spacecraft and can also be used for flying a missile and the like in the atmosphere. With the continuous innovation of aerospace technology and the continuous development of aerospace market, rocket engines pay more attention to the development directions of low cost, environmental protection, high safety, high thrust and the like. Wherein, the advantages of the solid-liquid rocket engine are obvious. First, the solid-liquid rocket engine uses solid fuel and liquid oxidizer to separate stored propellant (the fuel is usually inert substance and does not contain oxidizer), and has higher safety in the processes of production, storage, transportation, test and work. And the solid-liquid rocket engine can realize thrust adjustment and multiple starting by controlling the flow of the oxidant. In addition, compared with a solid rocket engine, the solid propellant grain of the solid rocket engine is insensitive to cracks and defects and has higher reliability. Finally, the cost of solid-liquid propulsion systems is much lower than that of solid and liquid propulsion systems.
Compared with solid and liquid rocket engines, the existing solid-liquid rocket engine technology still has some defects, for example, the terminal hydroxyl polybutadiene fuel used in the traditional solid-liquid rocket engine has low recession rate, and in order to apply the solid-liquid rocket engine to a rocket engine with larger thrust, the fuel combustion surface area of the traditional low recession rate grain needs to be increased to improve the thrust of the engine. By the end of the 20 th century, Arif, Cantwell and the like of Stanford discovered that due to the phenomenon of liquid drop entrainment, the combustion moving back rate of the paraffin-containing fuel is far higher than that of the traditional fuel, the paraffin-containing fuel has wide sources and low price, and the technical development of the solid-liquid rocket engine has a new development opportunity.
However, with the further research on the paraffin fuel, many problems of the paraffin fuel are gradually exposed, for example, the expansion with heat and contraction with cold of the paraffin are very obvious, which leads to the complicated precise control of the size during the preparation of the explosive column, and the internal part of the explosive column may be cracked due to the cooling shrinkage, thereby affecting the overall performance of the explosive column. In addition, the poor mechanical property of the pure paraffin wax leads the structural strength of the pure paraffin wax grain after being formed to be too low, and the pure paraffin wax grain is easy to collapse under the excitation action of airflow, heat and external force in the normal combustion process no matter in a porous structure or a single-hole structure, thereby seriously influencing the safety and reliability of the solid-liquid rocket engine in working. These problems have restricted further development of solid-liquid rocket engines. Therefore, in response to these problems, researchers have proposed and tested a charge column designed in different structures based on a nested structure by using a plurality of materials, so that the performance of the charge column is improved.
And thus, the method for molding the grain of powder provides challenges, various materials with different properties are molded in a nesting mode, and if a general casting molding mode is adopted, the precision controllability is low and the preparation efficiency is low. Moreover, for the grains with different materials and complex structures, the traditional forming method often requires a great deal of time, materials and equipment cost. The formed explosive column is directly attached to the mold through the inner hole and the outer hole, so that the demolding difficulty of the explosive column is greatly increased, and the ignition difficulty of the explosive column can be increased due to the fact that the demolding agent is attached to or mixed with the inner hole and the outer hole of the formed explosive column even if the explosive column is taken out of the mold through the demolding agent.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a nested grain forming system and a nested grain forming method for a solid-liquid rocket engine, which can realize the rapid forming of nested grains, ensure that the size and the performance of grains meet the design requirements, have low cost and high efficiency, and can effectively solve the problems in the background art.
The technical scheme adopted by the invention for solving the technical problems is as follows: a nested grain forming method of a solid-liquid rocket engine comprises the following steps:
step 100, designing and printing a 3D nested type grain structure substrate;
step 200, preparing a grain fuel, and mixing and melting grain filling fuel according to a ratio;
step 300, assembling a mold, namely, loading the nested grain structure matrix into a shaping mold;
step 400, performing centrifugal nesting molding, namely driving a mold to rotate by using a centrifugal machine, and pouring grain fuel into the mold;
and 500, post-treating the explosive columns, and polishing and trimming the head and tail ends of the explosive columns.
In the invention, preferably, in step 100, the nested grain structure substrate finished product is implemented by the following steps:
step 101, determining parameters of a grain structure matrix by using three-dimensional drawing software, and designing a grain nested structure matrix with a sawtooth-shaped section;
step 102, importing the designed nested structural matrix three-dimensional graph file into a slicing program for slicing;
step 103, importing the printing file generated after slicing into a 3D printer, and starting matrix printing after setting printing parameters.
In the present invention, preferably, in step 200, the preparation process of the cartridge fuel is specifically as follows:
step 201, preparing raw materials into grain fuel according to a proportion;
step 202, introducing the prepared fuel into a melting stirrer, and setting a melting temperature to stir and melt the fuel;
step 203, after the fuel is completely melted, raising the temperature, reducing the stirring speed to the minimum, and removing bubbles in the molten fuel;
and step 204, reducing the temperature of the melting stirrer for a period of time before the fuel is poured until the temperature of the fuel reaches the pouring temperature of the explosive column.
In the present invention, preferably, in step 300, the specific installation steps of the assembly mold are:
301, uniformly coating a release agent on the inner wall of the shaping mold;
step 302, loading the printed tooth-shaped nested type grain structure matrix into a shaping mold;
and 303, packaging the two end faces of the shaping mold by using heat insulation sheets.
In the present invention, it is preferable that the step 400 completes the centrifugal nesting molding by the specific steps of:
step 401, loading the assembled mould into a centrifuge;
step 402, heating a transport tank constant-temperature transport pipeline until the temperature of the pipeline also reaches the pouring temperature of the grain fuel;
step 403, opening a valve of the constant-temperature conveying pipeline for pouring, and simultaneously operating the centrifuge at the rotating speed of 1400 r/min;
and step 404, pouring the molten fuel into the mold for four times until the inner diameter of the grain is consistent with that of the nested structure grain.
In the present invention, it is preferable that the specific process of four pours of the molten fuel in step 404 is:
after 1/4 molten fuel required by the grain is poured, closing the constant-temperature conveying pipeline, waiting for 40-60 min until the temperature of the grain in the mould is reduced to room temperature and the fuel is completely contracted;
and opening the constant-temperature conveying pipeline to continue pouring, and repeating the steps after pouring a certain amount of 1/4 molten fuel until the fuel completely fills the mold.
In addition, the invention also provides a nested grain forming system of the solid-liquid rocket engine, which comprises a 3D matrix printing module, a fuel melting stirrer, a constant-temperature conveying pipeline, a grain mold and a centrifugal forming machine, wherein a grain structure matrix printed by the 3D matrix printing module can be loaded into the grain mold, heat insulating sheets are arranged at two ends of the grain mold, the size of each heat insulating sheet is determined by the size of the required grain and the size of the grain mold, the other end of the constant-temperature conveying pipeline penetrates through the heat insulating sheets at the side edges of the grain mold, a rotating flange sleeved on the outer surface of the constant-temperature conveying pipeline is arranged on each heat insulating sheet, and an output sleeve shaft of the centrifugal forming machine is fixedly installed with the heat insulating sheets at the other side edges of the grain mold through an end cover.
In the invention, preferably, the end cover is provided with a timing lock catch, the inner side edge of the heat insulation sheet connected with the end cover is provided with a plurality of T-shaped clamping plates which are uniformly distributed, and the edge of the grain die is provided with a limiting clamping groove corresponding to the T-shaped clamping plates.
In the invention, preferably, a limiting track is arranged at the lower end of the centrifugal forming machine, a push-pull displacement pump is arranged on the side edge of the centrifugal forming machine, and the push-pull displacement pump drives the centrifugal forming machine to move along the limiting track.
In the invention, preferably, a control valve is arranged at the connecting end of the constant-temperature conveying pipeline and the fuel melting stirrer, a heating belt is wrapped and wound on the outer surface of the constant-temperature conveying pipeline, a thermocouple is arranged in the heating belt, a temperature sensor for measuring the temperature of the constant-temperature conveying pipeline is arranged on the heating belt, the temperature sensor is connected with a controller and is connected with the input end of the controller, the thermocouple is connected with the output end of the controller, a timer is further arranged at the input end of the controller, and the control valve is also connected with the output end of the controller.
Compared with the prior art, the invention has the beneficial effects that:
(1) the mould disclosed by the invention is combined with a 3D printing technology, a medicine column nested structure matrix is designed and printed, and the medicine columns are filled in the matrix, so that the medicine columns with different shapes and different sizes can be produced, the flexibility of the finished product of the medicine columns is improved, the problem that the traditional forming method is not suitable for forming the medicine columns with complex structures is solved, a large amount of working time and material waste are reduced, and the flexibility of the structure design of the medicine columns is further improved;
(2) the method for manufacturing the explosive column adopts a centrifugal molding mode, has low requirement on equipment, can repeatedly use a mold, greatly reduces the processing and manufacturing cost of the explosive column, and has simple process and easy realization;
(3) the invention has wide application range, is not only suitable for the production of the grain, but also can rapidly form different casting materials by adopting a mode of material increase manufacturing and centrifugal forming.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of a delivery temperature flow control structure of the present invention;
FIG. 3 is a schematic view of the installation structure of the heat shield of the present invention;
FIG. 4 is a flow chart of nested grain forming of the solid-liquid rocket engine of the present invention;
FIG. 5 is a schematic diagram showing the steps of the nested grain forming method of the solid-liquid rocket engine.
Reference numbers in the figures:
1-3D substrate printing module; 2-fuel melt mixer; 3-a constant temperature transport pipeline; 4-a grain mold; 5-a centrifugal forming machine; 6-heat insulation sheet; 7-rotating the flange; 8-end cap; 9-T-shaped clamping plates; 10-a limit slot; 11-a limit track; 12-a push-pull displacement pump; 13-control valve; 14-a heating belt; 15-a thermocouple; 16-a temperature sensor; 17-a controller; 18-flow monitor meter.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
As shown in fig. 1 and 4, the invention provides a nested grain molding system of a solid-liquid rocket engine, which comprises a 3D matrix printing module 1, a fuel melting stirrer 2, a constant-temperature conveying pipeline 3, a grain mold 4 and a centrifugal molding machine 5, wherein a grain structural matrix printed by the 3D matrix printing module 1 can be loaded into the grain mold 4, the fuel melting stirrer 2 heats and melts fuel and performs variable-speed stirring according to the fuel melting condition, the melted fuel enters the grain mold through the constant-temperature conveying pipeline 3, under the rotation action of the centrifugal molding machine 5, a required grain is generated by cooperation of the grain structural matrix and the grain mold body, the grain mold 4 adopts a shaping mold in the embodiment, the length and the inner diameter are matched with the size of the required grain, and the outer diameter of the mold is matched with the inner diameter of a sleeve of a centrifuge.
It should be added that, the 3D base printing module includes a computer and a 3D printer, the computer is used for three-dimensional file slicing processing of the nested structure base, and the 3D printer prints and forms the structure base.
The powder column mould 4 is combined with a 3D printing technology, a powder column nested structure matrix is designed and printed, the problem that a traditional forming method is not suitable for forming powder columns with complex structures is solved, a large amount of working time and material waste are reduced, and the flexibility of the powder column structural design is improved.
As shown in fig. 1 and 2, a control valve 13 is arranged at the connecting end of the constant-temperature transportation pipeline 3 and the fuel melting mixer 2, a heating belt 14 is wrapped and wound on the outer surface of the constant-temperature transportation pipeline 3, a thermocouple 15 is arranged inside the heating belt 14, a temperature sensor 16 used for measuring the temperature of the constant-temperature transportation pipeline 3 is arranged on the heating belt 14, the temperature sensor 16 is connected with a controller 17 and is connected with the input end of the controller 17, and the thermocouple 15 is connected with the output end of the controller 17. The temperature change is measured in real time by the temperature sensor 16 and compared with the set constant temperature, the controller 17 automatically turns on or off the power supply of the heating belt, and the temperature of the constant-temperature conveying pipeline 3 is kept constant.
It should be particularly noted that a flow monitor 18 is further disposed on the constant-temperature transportation pipeline 3, the flow monitor 18 is connected to an input end of the controller 17, the control valve 13 is also connected to an output end of the controller 17, the flow monitor 18 mainly monitors the flux of the molten fuel in the constant-temperature transportation pipeline 3, in this embodiment, the molten fuel is fed into the grain mold 4 for batch casting four times, after a single time of feeding a certain amount of molten fuel, the controller 17 controls the control valve 13 to close, and the molten fuel is shaped in the grain mold 4 for several times until the manufacturing of the grain is completed.
Both ends of the grain mold 4 are provided with heat insulating sheets 6, the size of each heat insulating sheet 6 is determined by the size of the required grain and the size of the grain mold 4, the heat insulating sheets 6 are made of polymer heat insulating materials such as polytetrafluoroethylene, and the main function of the heat insulating sheets is to prevent the molten fuel from entering the grain mold 4 and cooling due to low temperature, so that the port of the grain mold 4 is effectively prevented from being blocked due to fuel accumulation, and the quality of the grain product is improved.
As shown in fig. 1 and 3, the other end of the constant-temperature transportation pipeline 3 passes through the heat insulation sheet 6 on the side of the grain mold 4, the heat insulation sheet 6 is provided with a rotating flange 7 sleeved on the outer surface of the constant-temperature transportation pipeline 3, an output sleeve shaft of the centrifugal forming machine 5 is fixedly installed with the heat insulation sheet 6 on the other side of the grain mold 4 through an end cover 8, and the centrifugal forming machine 5 rotates and shapes the grain mold 4 by driving the grain mold 4, so that the grain mold 4 rotates around the constant-temperature transportation pipeline 3 through the rotating flange 7, the integral synchronous rotation of the constant-temperature transportation pipeline 3 and the grain mold 4 is avoided, and the leakage of molten liquid fuel is prevented.
When the powder column is shaped, the centrifugal forming mode is adopted, the requirement on equipment is low, the die can be repeatedly used, the processing and manufacturing cost of the powder column is greatly reduced, the process is simple, and the implementation is very easy.
The lower end of the centrifugal forming machine 5 is provided with a limiting rail 11, the side edge of the centrifugal forming machine 5 is provided with a push-pull displacement pump 12, the push-pull displacement pump 12 drives the centrifugal forming machine 5 to move along the limiting rail 11, after the shaped explosive column is formed, the push-pull displacement pump 12 pulls the centrifugal forming machine 5 to move outwards along the limiting rail 11, the end cover 8 pulls the heat insulation sheet 6 to be separated from the explosive column mold 4, and the demolding operation of the explosive column is realized.
Example 2
In this embodiment, as shown in fig. 5, the invention further provides a nested grain forming method for a solid-liquid rocket engine, which includes the following steps:
and step 100, designing and printing a 3D nested type grain structure substrate.
The embedded type grain structure substrate finished product comprises the following concrete implementation steps:
step 101, determining parameters of a grain structure matrix by using three-dimensional drawing software, and designing a grain nested structure matrix with a saw-tooth-shaped section or other arbitrary shapes, namely in the embodiment, the production shape of the grain is mainly determined by the shape of the grain structure matrix, so that grains with different shapes and sizes can be produced, and the production flexibility of the grain is improved.
And 102, importing the designed nested structural matrix three-dimensional graph file into a slicing program for slicing.
Step 103, importing the print file generated after slicing into a 3D printer, starting matrix printing after setting the printing parameters, selecting the printing material as an ABS material in this embodiment, and controlling the 3D printer to start printing after setting the printing parameters.
The design mould in this embodiment combines the structural matrix of 3D printing technique, has solved the shaping problem of complicated structure grain that traditional forming method is not suitable for, can produce the grain of different shape types according to the demand, has reduced a large amount of operating time and material waste, has more improved the flexibility of grain structural design.
It should be added that the ABS material is a terpolymer of three monomers of acrylonitrile (a), butadiene (B) and styrene (S), and the relative contents of the three monomers can be arbitrarily changed to make various resins. ABS has the common properties of three components, acrylonitrile makes it resistant to chemical corrosion and heat and has a certain surface hardness, butadiene makes it have high elasticity and toughness, and styrene makes it have the processing and forming characteristics of thermoplastic plastics and improves electrical properties. Therefore, the ABS plastic is a tough, hard and rigid material which has easily obtained raw materials, good comprehensive performance, low price and wide application, can be used as fuel of a solid-liquid rocket engine, and can be decomposed when the ignition temperature is higher than 270 ℃ without influencing the ignition of a explosive column. Due to the thermoplasticity, the material with different shapes can be conveniently printed in a 3D mode.
Step 200, preparing the fuel of the explosive column, and mixing and melting the fuel filled in the explosive column according to the proportion.
In step 200, the preparation process of the cartridge fuel specifically comprises:
step 201, preparing raw materials into a grain fuel according to a proportion, in the embodiment, selecting a paraffin-based fuel as a filling fuel, weighing 50-60 parts of No. 58 paraffin, 10-30 parts of PE wax, 5-15 parts of EVA, 5-15 parts of SA and 1-5 parts of carbon powder according to the proportion respectively, and then placing the materials into a vessel;
202, introducing the prepared fuel into a melting stirrer, setting the melting temperature to stir and melt the fuel, wherein the melting temperature is specifically 160 ℃, turning on a switch of the stirrer after the fuel is completely melted, uniformly stirring at a rotating speed of 50r/min, and the melting temperature of 160 ℃, so that on one hand, the normal melting of the fuel can be ensured, on the other hand, the fuel is prevented from being coked due to overhigh temperature, and the production quality of the explosive column is improved;
step 203, after the fuel is completely melted and no precipitation appears in the liquid medicine, raising the temperature to 200 ℃, simultaneously reducing the stirring speed to the lowest value, namely 10r/min, keeping the stirring speed unchanged, removing bubbles in the molten fuel, reducing air in the fuel, and avoiding air holes from being generated in the shaped grain, so as to influence the structural integrity of the grain and the working efficiency of an engine;
step 204, reducing the temperature of the melt mixer for a period of time before the fuel is poured until the fuel temperature reaches the pouring temperature of 120 ℃.
It should be added that the structural matrix in this embodiment has a wide application range, and can be used in the shaping production operation of the grains, and because the mold of this embodiment adopts an additive manufacturing method in combination with a centrifugal molding method, it can be quickly molded by using various materials, and not only can use common plastics, resins, wood-plastics and other materials, but also can realize the cast molding of metal materials by upgrading a 3D printer.
Step 300, assembling a mold, and placing the nested grain structure matrix into a shaping mold, wherein in this example, the nested grain structure matrix has a length of 125mm, an outer diameter of 70mm, and an inner diameter of 30mm, the shaping mold is a cylindrical mold, the material is polytetrafluoroethylene, the length of 125mm, and the outer diameter of the mold is 90mm and the inner diameter of 70mm, that is, the grain structure matrix is embedded into the shaping mold during nesting, and the grain molten material is shaped in the inner diameter and outer diameter spaces of the structure matrix to form an integral nested structure, so as to form a single-hole grain with an inner diameter of 70mm and an inner diameter of 30mm, although the grain structure of the grain structure matrix is different, grains with different shapes and structures can be produced, only one grain structure is listed in this embodiment.
The specific installation steps of the assembly die are as follows:
firstly, uniformly coating a release agent on the inner wall of a shaping mold, wherein the shaping mold is made of polytetrafluoroethylene, the shaping mold in the embodiment is specifically a cylindrical mold, and the shaping mold can be matched with molds in different shapes according to different requirements of grains;
then, uniformly coating a layer of release agent on the inner wall of the cylinder, and loading the printed tooth-shaped nested type grain structure matrix into a shaping mold;
and finally, packaging the two end faces of the shaping mold by using heat insulation sheets, wherein the heat insulation sheets are made of polytetrafluoroethylene, and the inner diameter of each heat insulation sheet is consistent with that of the explosive column.
It should be added that, the general explosive columns are solid explosive columns, the hollow part of the hollow cylinder made of propellant and a small amount of additive is a combustion surface, the cross section of the hollow cylinder is circular, star-shaped and the like, if the hollow surface of the explosive column is adhered with release agent, the ignition difficulty of the explosive column is increased, the combustion heat energy of fuel is seriously reduced, the generated thrust is small, and the working efficiency of the engine is low, so the forming process of the explosive column is one of the most critical links, and the performance of the solid engine is directly influenced.
Therefore, when the grain is produced, the inner surface of the grain is prevented from being adhered with substances which are difficult to ignite, in the grain production process of the embodiment, the 3D-printed tooth-shaped nested grain structure base body is fixed inside the cylinder mould, so when molten fuel is cast, the molten fuel is mainly concentrated in the inner diameter space of the tooth-shaped nested grain structure base body and is shaped in the cavity of the tooth-shaped nested grain structure base body, and therefore the structure base body serves as a protective shell, and the fact that release agents are not adhered to the surface of the whole outer surface of the grain can be guaranteed.
The igniter nozzle in the solid-liquid rocket engine is generally aligned to the inner diameter or the inner surface of the end face of the explosive column, so that the occupied area of the explosive column is small when the explosive column is ignited, the ignition difficulty of paraffin is very low, the ignition difficulty of the nested explosive column cannot be influenced, and after the ignition is finished, the combustion temperature of the explosive column is 2500-3500 degrees approximately, so that the 3D structural matrix and the explosive column can be combusted simultaneously, and the 3D structural matrix and the release agent on the surface of the 3D structural matrix do not influence subsequent combustion conditions.
And step 400, carrying out centrifugal nesting molding, wherein a centrifugal machine is used for driving the mold to rotate, and the grain fuel is poured in the mold.
The specific steps of completing the centrifugal nesting molding in the step 400 are as follows:
step 401, the assembled die is placed in a centrifuge, and an aluminum alloy end cover is used for clamping the die;
step 402, connecting a heating belt power supply wrapped outside the constant-temperature conveying pipeline, and heating the constant-temperature conveying pipeline until the temperature of the pipeline also reaches the pouring temperature of the explosive column fuel of 120 ℃;
step 403, opening a valve of the constant-temperature conveying pipeline for pouring, and simultaneously operating the centrifuge at the rotating speed of 1400 r/min;
and step 404, pouring the molten fuel into the mold for four times until the inner diameter of the grain is consistent with that of the nested structure grain.
The specific process of four times of pouring of the molten fuel is as follows:
after 1/4 molten fuel required by the grain is poured, closing the constant-temperature conveying pipeline, waiting for 40-60 min until the temperature of the grain in the mould is reduced to room temperature and the fuel is completely contracted;
opening the constant temperature and transporting the pipeline and continuing pouring, behind the molten fuel of pouring ration 1/4, repeating above-mentioned step, until the fuel fills the mould completely, can effectually prevent that paraffin expend with heat and contract with cold and lead to the explosive column crackle to produce, guarantee the structural integrity of explosive column, improve the volume filling coefficient, propellant volume and the effective volume ratio of combustion chamber inner chamber promptly.
And 500, post-treating the explosive columns, and polishing and trimming the head and tail ends of the explosive columns.
And when the temperature of the explosive columns is reduced to room temperature, closing the centrifugal machine, pushing and pulling the displacement pump to drive the centrifugal forming machine to move outwards along the limiting track, pulling the heat insulation sheet by the end cover to separate from the explosive column mould, dismantling the rotating flange, taking out the structural matrix and the explosive columns embedded in the matrix from the mould, and cutting and polishing the explosive columns according to specific requirements.
The powder column nestification of this embodiment production is inside the 3D prints the structure base member, consequently 3D prints structure base member direct contact release agent, the protection powder column surface does not receive the ignition influence of release agent, igniter spout generally aims at powder column terminal surface internal diameter or internal surface in the solid-liquid rocket engine, consequently when this powder column ignites, the powder column area occupied is little, the degree of difficulty of igniting of paraffin is very low, consequently the powder column after the nestification can not influence the degree of difficulty of igniting, that is to say the kitchen range of igniting lies in the fuel of nested powder column terminal surface, so do not have the problem of the degree of difficulty of igniting.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (10)
1. A nested grain forming method of a solid-liquid rocket engine is characterized by comprising the following steps:
step 100, designing and printing a 3D nested type grain structure substrate;
step 200, preparing a grain fuel, and mixing and melting grain filling fuel according to a ratio;
step 300, assembling a mold, namely, loading the nested grain structure matrix into a shaping mold;
step 400, performing centrifugal nesting molding, namely driving a mold to rotate by using a centrifugal machine, and pouring grain fuel into the mold;
and 500, post-treating the explosive columns, and polishing and trimming the head and tail ends of the explosive columns.
2. The method for forming the nested grain of the solid-liquid rocket engine according to claim 1, wherein in the step 100, the nested grain structure substrate finished product is realized by the following steps:
step 101, determining parameters of a grain structure matrix by using three-dimensional drawing software, and designing a grain nested structure matrix with a sawtooth-shaped section;
step 102, importing the designed nested structural matrix three-dimensional graph file into a slicing program for slicing;
step 103, importing the printing file generated after slicing into a 3D printer, and starting matrix printing after setting printing parameters.
3. The method for forming nested grain of a rocket motor according to claim 1, wherein in step 200, the preparation process of grain fuel is specifically as follows:
step 201, preparing raw materials into grain fuel according to a proportion;
step 202, introducing the prepared fuel into a melting stirrer, and setting a melting temperature to stir and melt the fuel;
step 203, after the fuel is completely melted, raising the temperature, reducing the stirring speed to 10r/min, and removing bubbles in the molten fuel;
and step 204, reducing the temperature of the melting stirrer for a period of time before the fuel is poured until the temperature of the fuel reaches the pouring temperature of the explosive column.
4. The method for forming nested grain of a rocket motor according to claim 1, wherein in step 300, the assembling mold is specifically installed by the following steps:
301, uniformly coating a release agent on the inner wall of the shaping mold;
step 302, loading the printed tooth-shaped nested type grain structure matrix into a shaping mold;
and 303, packaging the two end faces of the shaping mold by using heat insulation sheets.
5. The method for forming the nested grain of the hybrid rocket engine according to claim 1, wherein the step 400 of performing centrifugal nesting forming comprises the following specific steps:
step 401, loading the assembled mould into a centrifuge;
step 402, heating the constant-temperature transportation pipeline until the temperature of the pipeline reaches the pouring temperature of the grain fuel;
step 403, opening a valve of the constant-temperature conveying pipeline for pouring, and simultaneously operating the centrifuge at the rotating speed of 1400 r/min;
and step 404, pouring the molten fuel into the mold for four times until the inner diameter of the grain is consistent with that of the nested structure grain.
6. The method for forming nested grain of a rocket motor according to claim 5, wherein in step 404, the specific process of four times of pouring of the molten fuel is as follows:
after 1/4 molten fuel required by the grain is poured, closing the constant-temperature conveying pipeline, waiting for 40-60 min until the temperature of the grain in the mould is reduced to room temperature and the fuel is completely contracted;
and opening the constant-temperature conveying pipeline to continue pouring, and repeating the steps after pouring a certain amount of 1/4 molten fuel until the fuel completely fills the mold.
7. The utility model provides a nested formula grain molding system of solid-liquid rocket engine which characterized in that: comprises a 3D matrix printing module (1), a fuel melting stirrer (2), a constant-temperature conveying pipeline (3), a grain mold (4) and a centrifugal forming machine (5), the medicine column structure matrix printed by the 3D matrix printing module (1) can be arranged in a medicine column mould (4), the two ends of the grain die (4) are provided with heat insulation sheets (6), the size of the heat insulation sheets (6) is determined by the size of the required grain and the size of the grain die (4), the other end of the constant-temperature conveying pipeline (3) penetrates through a heat insulation sheet (6) on the side edge of the grain die (4), the heat insulation sheet (6) is provided with a rotary flange (7) sleeved on the outer surface of the constant-temperature conveying pipeline (3), an output sleeve shaft of the centrifugal forming machine (5) is fixedly arranged with a heat insulation sheet (6) on the other side edge of the grain die (4) through an end cover (8).
8. The nested grain molding system for a rocket motor according to claim 7, wherein: the end cover (8) is provided with a timing lock catch, the inner side edge of the heat insulation sheet (6) connected with the end cover (8) is provided with a plurality of T-shaped clamping plates (9) which are uniformly distributed, and the edge of the grain die (4) is provided with a limiting clamping groove (10) corresponding to the T-shaped clamping plates (9).
9. The nested grain molding system for a rocket motor according to claim 7, wherein: the lower end of the centrifugal forming machine (5) is provided with a limiting rail (11), the side edge of the centrifugal forming machine (5) is provided with a push-pull displacement pump (12), and the push-pull displacement pump (12) drives the centrifugal forming machine (5) to move along the limiting rail (11).
10. The nested grain molding system for a rocket motor according to claim 7, wherein: the utility model discloses a fuel melting and stirring device, including constant temperature transport pipeline (3), heating belt (14), thermocouple (15), temperature sensor (16) that are used for measuring constant temperature transport pipeline (3) temperature are equipped with on heating belt (14), temperature sensor (16) are connected with controller (17) and are connected with the input of controller (17), thermocouple (15) are connected with the output of controller (17), still be equipped with flow monitor (18) on constant temperature transport pipeline (3), flow monitor (18) are connected with the input of controller (17), control valve (13) also are connected with the output of controller (17).
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| CN111105503B (en) * | 2019-12-19 | 2021-07-02 | 中国人民解放军国防科技大学 | Method for determining explosive-loading combustion surface of solid rocket engine |
| CN111873405B (en) * | 2020-07-08 | 2021-11-19 | 西安交通大学 | Photo-curing technology-based heat-insulation and charge integrated additive manufacturing method, printing device and forming equipment |
| CN114311656B (en) * | 2021-12-31 | 2023-04-28 | 西安交通大学 | Method for preparing composite solid propellant based on 3D printing special-shaped high-combustion-speed die |
| CN114714545B (en) * | 2022-04-18 | 2023-02-14 | 大连理工大学 | Semi-dumbbell-shaped annular groove grain forming die and forming method for solid rocket engine |
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| GB788063A (en) * | 1954-10-06 | 1957-12-23 | Distillers Co Yeast Ltd | Moulding reinforced plastic tubes |
| US3283510A (en) * | 1964-08-03 | 1966-11-08 | Thiokol Chemical Corp | Throttlable solid propellant rocket motor |
| JP4398522B2 (en) * | 1997-05-22 | 2010-01-13 | バスフ・ヒュエル・セル・ゲーエムベーハー | Method for producing polymer electrolyte membrane for fuel cell and fuel cell |
| RU2359145C1 (en) * | 2007-12-29 | 2009-06-20 | Федеральное государственное унитарное предприятие "Исследовательский Центр имени М.В. Келдыша" | Hybrid rocket engine |
| CN202293147U (en) * | 2011-10-25 | 2012-07-04 | 天长市天广有机玻璃有限公司 | Centrifugal casting die |
| US10252449B1 (en) * | 2015-01-23 | 2019-04-09 | Centro, Inc. | Rotational molding with pre-formed shapes |
| CN105840344B (en) * | 2016-04-20 | 2017-12-08 | 哈尔滨工业大学 | A kind of solid propellant rocket internal bore burning powder column preparation and safely and fast releasing process |
| CN106194501A (en) * | 2016-07-08 | 2016-12-07 | 北京航空航天大学 | Spiral Types of Medicine solid-liquid rocket |
| CN206140986U (en) * | 2016-10-18 | 2017-05-03 | 泸州北方化学工业有限公司 | Casement shunt during solid powder column shaping is used |
| CN107461277A (en) * | 2017-10-11 | 2017-12-12 | 北京航空航天大学 | A kind of ground experiment modularization hybrid rocket engine |
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