CN111233593A - Vertical additive manufacturing method of solid propellant - Google Patents
Vertical additive manufacturing method of solid propellant Download PDFInfo
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- CN111233593A CN111233593A CN202010177946.0A CN202010177946A CN111233593A CN 111233593 A CN111233593 A CN 111233593A CN 202010177946 A CN202010177946 A CN 202010177946A CN 111233593 A CN111233593 A CN 111233593A
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
- C06B33/02—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide with an organic non-explosive or an organic non-thermic component
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y70/00—Materials specially adapted for additive manufacturing
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
- C06B23/001—Fillers, gelling and thickening agents (e.g. fibres), absorbents for nitroglycerine
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
- C06B23/007—Ballistic modifiers, burning rate catalysts, burning rate depressing agents, e.g. for gas generating
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
- C06B45/04—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive
- C06B45/06—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component
- C06B45/10—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component the organic component containing a resin
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
- C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
- C06D5/06—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more solids
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- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Health & Medical Sciences (AREA)
- Metallurgy (AREA)
- Life Sciences & Earth Sciences (AREA)
- Dispersion Chemistry (AREA)
- Molecular Biology (AREA)
- Crystallography & Structural Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Combustion & Propulsion (AREA)
- Powder Metallurgy (AREA)
Abstract
The invention provides a vertical additive manufacturing method of a solid propellant, belonging to the technical field of solid propellant preparation, comprising the following steps: respectively processing a metal additive and an oxidant in a premixing system by adopting at least two groups of equipment, premixing the metal additive and an adhesive as main materials, and premixing the oxidant and a curing agent as slurry; isocyanate is used in the curing agent; mixing the main material and the slurry in a mixer to obtain a propellant raw material; conveying propellant raw materials into a channel of a propellant printing nozzle, and adjusting the output flow of the propellant printing nozzle according to the requirement; the propellant printing nozzle is driven by the actuating mechanism to move in three degrees of freedom in the vertically arranged propellant combustion chamber, and propellant raw materials are sprayed out by the propellant printing nozzle, so that the propellant raw materials are piled up layer by layer in the propellant combustion chamber for forming. The three-dimensional additive manufacturing of the invention can accelerate the prototype manufacturing of the solid propellant, does not need a complex combined core mould, and is simple and rapid to form.
Description
Technical Field
The invention relates to the technical field of preparation of solid propellants, in particular to a vertical additive manufacturing method of a solid propellant.
Background
The solid propellant is composed of curing agent, metal fuel, oxidant, energetic material and the like. In the preparation process of the solid propellant, the components of the solid propellant need to be uniformly mixed to form slurry, and then the slurry is conveyed to a forming device for solidification and forming. The traditional propellant wall-adhering pouring process needs a combined core mold, and has poor mechanical property of a powder column, low forming precision of the powder column, complex process, long period and high cost.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defects of low forming precision, complex process and long period of the solid propellant in the prior art, so that the vertical additive manufacturing method of the solid propellant with simple process is provided.
In order to solve the technical problem, the vertical additive manufacturing method of the solid propellant provided by the invention comprises the following steps:
respectively processing a metal additive and an oxidant in a premixing system by adopting at least two groups of equipment, premixing the metal additive and an adhesive as main materials, and premixing the oxidant and a curing agent as slurry; wherein the curing agent is isocyanate;
mixing the main material and the slurry in a mixer to obtain a propellant raw material;
conveying propellant raw materials into a channel of a propellant printing nozzle, and adjusting the output flow of the propellant printing nozzle according to the requirement;
the propellant printing nozzle is driven by the actuating mechanism to move in three degrees of freedom in the vertically arranged propellant combustion chamber, and propellant raw materials are sprayed out by the propellant printing nozzle, so that the propellant raw materials are piled up layer by layer in the propellant combustion chamber for forming.
Preferably, the method further comprises the following steps:
after the propellant raw materials are sprayed out of the channel of the propellant printing nozzle, the propellant raw materials are solidified and molded by heating.
Preferably, the method further comprises the following steps:
and in the process of outputting the propellant raw material by the propellant printing nozzle, outputting a sand mold support by the sand mold printing nozzle.
Preferably, the propellant print head has a plurality of channels of different diameters therein.
Preferably, the plurality of channels in the propellant print head are arranged concentrically.
The technical scheme of the invention has the following advantages:
1. according to the vertical additive manufacturing method of the solid propellant, provided by the invention, at least two groups of equipment are adopted in a premixing system to respectively process the metal additive and the oxidant, so that the contact between the metal additive and the oxidant can be reduced, and the danger of combustion and even explosion caused by friction static electricity and heat accumulation in mixed contact is avoided; propellant raw materials are conveyed into a channel of the propellant printing nozzle, the propellant printing nozzle is driven by the actuating mechanism to move in three degrees of freedom in the horizontally arranged charge combustion chamber, the propellant raw materials are sprayed out by the propellant printing nozzle, and are piled up and formed layer by layer in the charge combustion chamber, so that the prototype manufacture of solid propellant in the combustion chamber can be accelerated, a complex combined core mold is not needed, and the simple and rapid forming is realized.
2. According to the vertical additive manufacturing method of the solid propellant, the propellant raw materials are quickly solidified and molded by heating after being sprayed out of the channel of the propellant printing spray head.
3. According to the vertical additive manufacturing method of the solid propellant, provided by the invention, the sand mold support can temporarily block the perforation of the solid propellant and is taken out by hand after the solid propellant is printed; the central perforation is prevented from being blocked in the solid propellant printing process.
4. According to the vertical additive manufacturing method of the solid propellant, provided by the invention, the propellant printing nozzle is internally provided with a plurality of channels with different diameters, so that the vertical additive manufacturing method of the solid propellant can adapt to the printing of the solid propellant with different dimensional accuracy and speed requirements.
5. According to the vertical additive manufacturing method of the solid propellant, provided by the invention, the plurality of channels in the propellant printing nozzle are concentrically arranged, so that the adjustment of the position of the propellant printing nozzle during channel replacement is avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a front view of a vertical additive manufacturing system provided in the present invention.
Figure 2 is a top view of a propellant print head.
Fig. 3 is a front sectional view in the direction of a-a in fig. 2.
Fig. 4 is a front view of a vertical additive manufacturing system with a sand printing nozzle provided in the present invention.
Description of reference numerals:
1. carrying out grain treatment; 2. a combustion chamber; 3. supporting a sand mold; 4. a propellant print head; 5. a sand mould printing nozzle; 6. a front opening; 7. a tail port; 8. and supporting the platform.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. 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.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Example 1
The solid propellant of the embodiment is a grain 1 of a solid rocket engine, which is formed in a combustion chamber of the solid rocket engine and has a perforation in the center. The solid propellant comprises: metal additive, adhesive, oxidant, plasticizer and curing agent, and also includes neutral bonding agent, burning rate catalyst and curing catalyst. Wherein the curing agent is isocyanate. The curing agent comprises: at least one of toluene diisocyanate and isophorone diisocyanate.
The solid propellant of the embodiment is a ternary butylated hydroxytoluene propellant, and the ternary butylated hydroxytoluene propellant comprises the following components in percentage by mass: 69.5 percent of amine perchlorate, 18.5 percent of aluminum powder, 8.4 percent of hydroxyl-terminated polybutadiene, 3.5 percent of diisooctyl sebacate, 0.058 percent of toluene diisocyanate, 0.02 percent of isophthaloyl, 0.020 percent of ferric oxide and 0.002 percent of triphenyl bismuth.
Wherein, the amine perchlorate is taken as an oxidant, and accounts for 47 to 70 percent of the mass of the raw materials;
aluminum powder is used as a metal additive, and accounts for 18-19% of the raw materials by mass;
hydroxyl-terminated polybutadiene is used as an adhesive, and accounts for 7-9% of the raw materials by mass;
diisooctyl sebacate is used as a plasticizer, and accounts for 3-4% of the raw materials by mass;
toluene diisocyanate is taken as a curing agent, and accounts for about 0.05 to 0.06 percent of the raw materials by mass;
triphenyl bismuth is used as a curing catalyst and is added in a trace amount, and the triphenyl bismuth accounts for about 0.002 percent of the mass of the raw materials;
isophthaloyl dichloride is taken as a neutral bonding agent, and accounts for about 0.02 percent of the raw materials by mass;
the iron oxide is used as a burning rate catalyst and accounts for about 0.02 percent of the raw materials by mass.
When mixing, premixing an oxidant, a curing agent, a curing catalyst, a neutral bonding agent and a burning rate catalyst as a group; the metal additives, binders, plasticizers, etc. are pre-mixed as another group.
In the triplet butylated hydroxytoluene propellant, the particle size distribution of the ammonium perchlorate is as follows: 30% of particles having a particle diameter of 250 μm, 20% of particles having a particle diameter of 120 μm, 30% of particles having a particle diameter of 20 μm, and 20% of particles having a particle diameter of 1 μm; the grain size composition of the aluminum powder is as follows: the content of particles having a particle diameter of 165 μm was 50%, the content of particles having a particle diameter of 30 μm was 20%, and the content of particles having a particle diameter of 20 μm was 30%.
Example 2
The solid propellant of the embodiment is a quadruple hydroxyl propellant, and the quadruple hydroxyl propellant comprises the following components in percentage by mass: 47% of amine perchlorate, 18% of aluminum powder, 25% of octogen, 7% of hydroxyl-terminated polybutadiene, 2.83% of diisooctyl sebacate, 0.048% of toluene diisocyanate, 0.1% of isophthaloyl, 0.02% of ferric oxide and 0.002% of triphenyl bismuth.
In the four-tuple hydroxyl propellant, the particle size distribution of the amine perchlorate is as follows: 30% of particles having a particle diameter of 250 μm, 20% of particles having a particle diameter of 120 μm, 30% of particles having a particle diameter of 20 μm, and 20% of particles having a particle diameter of 1 μm; the grain size composition of the aluminum powder is as follows: the content of particles having a particle diameter of 165 μm was 50%, the content of particles having a particle diameter of 30 μm was 20%, and the content of particles having a particle diameter of 20 μm was 30%.
Example 3
The embodiment provides a vertical additive manufacturing method of a solid propellant, which comprises the following steps:
the method comprises the following steps: pre-mixing raw materials of the solid propellant into at least two groups, and treating the metal additive and the oxidant separately;
in the group where the metal additive is located, the adhesive and the metal additive are premixed to form a main material;
in the group of the oxidant, a curing agent and the like are premixed into slurry;
mixing the main material and the slurry in a mixer to obtain the propellant raw material.
Step two: feeding propellant raw material into the channels of the propellant print head 4; the output flow of the propellant printing nozzle 4 is adjusted according to the requirement; the propellant print head 4 has a plurality of concentric channels with different diameters, and the channels with corresponding diameters can be selected according to the required printing size and speed.
As shown in fig. 2 and 3, the propellant print head 4 is in a conical structure, each printing channel is concentrically arranged, the converted diameter of the cross section area of the propellant print head 4 is 5mm to 10mm, and the flow rate of the propellant print head 4 is 1m/s to 2 m/s.
Step three: the propellant printing nozzle 4 is driven by the actuating mechanism to move in three degrees of freedom in the transversely arranged combustion chamber 2, and is sprayed out by the propellant printing nozzle 4, so that the raw materials are piled up layer by layer in the combustion chamber 2 for forming. And in the process of outputting the propellant raw materials by the propellant printing nozzle 4, outputting the sand mold support 3 by the sand mold printing nozzle 5.
As shown in fig. 1, the combustion chamber 2 is provided with a front opening 6 and a tail opening 7, the combustion chamber 2 is vertically placed on a supporting platform 8, the tail opening 7 is supported at the upper surface of the supporting platform 8 in a contact mode, and a mechanical arm of an actuating mechanism drives the propellant printing nozzle 4 to enter the inner cavity of the combustion chamber 2; the method comprises the following steps that a three-degree-of-freedom CAD model of a grain 1 is designed in advance by software, and then the three-degree-of-freedom CAD model is converted into an additive printing coordinate system and a printing path which are suitable for a propellant printing nozzle 4 to move through a software control system; and the mechanical arm of the actuating mechanism drives the propellant printing nozzle 4 to move in three degrees of freedom from bottom to top in the inner cavity of the combustion chamber 2 according to the printing path.
As shown in fig. 4, a sand printing nozzle 5 is added at the same time of solid propellant printing. The sand mold printing nozzle 5 and the propellant printing nozzle 4 jointly extend into the combustion chamber 2, the sand mold printing nozzle 5 is used for printing a sand mold support 3, and the printed sand mold support 3 is consistent with the shaft hole of the explosive column 1 in shape, so that the formation of a middle perforation of the solid propellant is ensured, and the blockage of the shaft hole in the printing process of the solid propellant is avoided; after the solid propellant is printed, the sand mold support 3 can be taken out by loosening the hand. In addition, as an alternative embodiment, the sand mold print head 5 may not be provided when the viscosity of the solid propellant material satisfies the requirement.
Step four: curing agent and heating to make the propellant material quickly cured and formed.
The working principle and the process are as follows:
a plane perpendicular to the axis of the combustion chamber 2 is defined as a YZ coordinate system, a direction parallel to the paper surface in fig. 1 is defined as a Y coordinate axis, and a direction perpendicular to the paper surface in fig. 1 is defined as a Z coordinate axis; in a coordinate system YZ, a motor drives a mechanical arm of an actuating mechanism to drive a propellant printing nozzle 4 to horizontally move along a Z coordinate axis, the propellant printing nozzle moves from one end to the other end, propellant liquid drops are simultaneously sprayed, and the liquid drops are quickly solidified and formed by a solidifying device; then the spray head is stopped after being moved along the Y coordinate axis by one step, the mechanical arm of the motor-driven executing mechanism drives the propellant printing spray head 4 to horizontally move along the Z coordinate axis, the propellant printing spray head returns to the starting end from one end, and simultaneously the propellant liquid drops are sprayed, so that the liquid drops are quickly solidified and formed; the above steps are repeated in a circulating way, and the spray head finishes the spraying, curing and forming of a layer of propellant on the YZ plane. Then, the mechanical arm of the motor-driven executing mechanism drives the propellant printing nozzle 4 to lift a layer of height along the vertical direction, the reciprocating printing process is repeated, and the propellants are overlapped layer by layer until the size design requirements of the explosive column 1 are met, so that the additive manufacturing process of horizontal plane bidirectional printing-vertical lifting is completed.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (5)
1. A vertical additive manufacturing method of a solid propellant is characterized by comprising the following steps:
respectively processing a metal additive and an oxidant in a premixing system by adopting at least two groups of equipment, premixing the metal additive and an adhesive as main materials, and premixing the oxidant and a curing agent as slurry; wherein the curing agent is isocyanate;
mixing the main material and the slurry in a mixer to obtain a propellant raw material;
conveying propellant raw materials to a channel of a propellant printing nozzle (4), and adjusting the output flow of the propellant printing nozzle (4) according to the requirement;
the propellant printing nozzle (4) is driven by the actuating mechanism to move in three degrees of freedom in the vertically arranged charge combustion chamber (2), and propellant raw materials are sprayed out by the propellant printing nozzle (4), so that the propellant raw materials are piled up layer by layer in the charge combustion chamber (2) for forming.
2. The vertical additive manufacturing process of a solid propellant according to claim 1, further comprising the steps of:
after the propellant raw materials are sprayed out from the channel of the propellant printing nozzle (4), the propellant raw materials are solidified and molded by heating.
3. The vertical additive manufacturing process of a solid propellant according to claim 1, further comprising:
and in the process of outputting the propellant raw materials by the propellant printing sprayer (4), outputting the sand mold support (3) by the sand mold printing sprayer (5).
4. Vertical additive manufacturing process of a solid propellant according to claim 1, characterized in that the propellant print head (4) has a plurality of channels with different diameters therein.
5. Vertical additive manufacturing process of a solid propellant according to claim 4, wherein the channels in the propellant print head (4) are arranged concentrically.
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| CN202010177946.0A CN111233593A (en) | 2020-03-13 | 2020-03-13 | Vertical additive manufacturing method of solid propellant |
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| CN202010177946.0A CN111233593A (en) | 2020-03-13 | 2020-03-13 | Vertical additive manufacturing method of solid propellant |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112341297A (en) * | 2020-11-09 | 2021-02-09 | 北京航空航天大学 | Safe and efficient forming method of energetic explosive column |
| CN112521239A (en) * | 2020-12-07 | 2021-03-19 | 西安交通大学 | Additive manufacturing method and device for composite solid propellant formed by separating metal fuel and oxidant |
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| CN112521239A (en) * | 2020-12-07 | 2021-03-19 | 西安交通大学 | Additive manufacturing method and device for composite solid propellant formed by separating metal fuel and oxidant |
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