CN112521239A - Additive manufacturing method and device for composite solid propellant formed by separating metal fuel and oxidant - Google Patents
Additive manufacturing method and device for composite solid propellant formed by separating metal fuel and oxidant Download PDFInfo
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- CN112521239A CN112521239A CN202011419052.4A CN202011419052A CN112521239A CN 112521239 A CN112521239 A CN 112521239A CN 202011419052 A CN202011419052 A CN 202011419052A CN 112521239 A CN112521239 A CN 112521239A
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B47/00—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
- C06B47/02—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
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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
- B33Y30/00—Apparatus for additive manufacturing; Details thereof or accessories therefor
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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
- B33Y70/10—Composites of different types of material, e.g. mixtures of ceramics and polymers or mixtures of metals and biomaterials
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
- C06B21/0033—Shaping the mixture
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Abstract
The invention discloses a method and a device for additive manufacturing of a composite solid propellant formed by isolating a metal fuel and an oxidant, belonging to the technical field of composite solid propellant manufacturing. The method omits the step of mixing the oxidizer and the metal fuel in the traditional process, and can design different ingredient proportions and structures of the oxidizer and the metal fuel according to different performance requirements of the solid rocket engine, thereby not only ensuring the safety of the manufacturing process, but also manufacturing the composite solid propellant with a complex structure.
Description
Technical Field
The invention belongs to the technical field of solid rocket engine manufacturing, and particularly relates to a material additive manufacturing method and device for a composite solid propellant formed by isolating a metal fuel and an oxidant.
Background
The composite solid propellant is the core of the solid rocket engine, provides energy and working medium for the engine to obtain thrust, and determines the thrust performance of the solid rocket engine.
The traditional process for manufacturing the composite solid propellant comprises the steps of preparing an oxidizer, preparing and premixing fuel, mixing, casting, curing, demoulding and shaping. However, in the premixing and mixing, the oxidant is in direct contact with the metal fuel, which is a potential safety hazard in the whole manufacturing process, and the traditional manufacturing process cannot be adapted to the composite solid propellant with a complex structure.
Disclosure of Invention
Aiming at the safety problem caused by mixing of an oxidizer and a metal fuel in the traditional manufacturing process of the composite solid propellant, the invention discloses a method and a device for additive manufacturing of the composite solid propellant formed by separating the metal fuel and the oxidizer, and provides a method for separating additive manufacturing, so that the safety of the oxidizer and the metal fuel of a solid rocket engine in the manufacturing process is ensured, and the composite solid propellant with a complex structure can be manufactured.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
the invention discloses a material increase manufacturing method of a high-safety composite solid propellant formed by isolating metal fuel and an oxidant.
The additive manufacturing method of the high-safety composite solid propellant formed by separating the metal fuel and the oxidizer comprises the following steps of:
s1: designing the component proportion of an oxidant and a metal fuel in the composite solid propellant according to the actually required performance requirement of the solid rocket engine, and designing the accumulation mode of an oxidant and metal fuel forming unit in the composite solid propellant according to the component proportion;
s2: planning a forming path and technological parameters for isolated forming additive manufacturing according to the structure of the composite solid propellant grain, and importing the data obtained by planning into isolated additive manufacturing equipment;
s3: respectively preparing oxidant slurry and metal fuel slurry according to the component proportion of the oxidant and the metal fuel designed by S1, and preparing a photosensitive prepolymer;
s4: when the isolated additive manufacturing equipment is used for printing, the metal fuel slurry and the photosensitive prepolymer are coaxially fed and extruded in a coaxial extrusion mode, the oxidant slurry is independently extruded, and after one metal fuel line unit or oxidant line unit is printed, photocuring forming treatment is carried out to form an isolated interface between the metal fuel line unit and the oxidant line unit;
s5: and (5) repeating the printing treatment of the step S4 in a layer-by-layer stacking mode until the structure of the designed composite solid propellant is printed, so as to prepare the high-safety composite solid propellant.
Preferably, the metal fuel slurry is formed by mixing micron aluminum powder serving as a solute and a resin binder serving as a solvent; the oxidant slurry is prepared by dispersing and mixing an oxidant material into a photosensitive prepolymer.
More preferably, the resin binder is a hydroxyl terminated butadiene or the like resin binder.
Preferably, the solid content of the metal fuel in the metal fuel slurry is 2-20%; the solid phase content in the oxidant slurry is 70-95%.
Preferably, the photosensitive prepolymer is a modified binder having photocuring properties. The effects include the following two points: firstly, under the action of light emitted by a light curing system, the photosensitive prepolymer can be rapidly cured; and secondly, as the outer interface of the coaxial storage unit, after the coaxial storage unit is laid coaxially and photocured, the coaxial storage unit is isolated from the oxidant line unit.
Preferably, the oxidant material is ammonium perchlorate crystals at least containing four ammonium perchlorate crystals with the particle size range of 1-150 mu m, and the adjacent particle size ratio of the particle size of the at least four ammonium perchlorate crystals from small to large is more than 2.
Preferably, in S1, the packing pattern of the oxidizer and metal fuel forming units in the composite solid propellant is an alternating packing or stacked packing.
Preferably, the method of isolated additive manufacturing includes, but is not limited to, direct write molding, fused deposition, and like additive manufacturing techniques.
The invention also discloses an isolated additive manufacturing device for realizing the additive manufacturing method of the high-safety composite solid propellant for the isolated forming of the metal fuel and the oxidant, which comprises the following steps: feeding system, printing system, photocuring system and shaping platform:
the feeding system is used for providing printing materials for the printing system and comprises a coaxial feeding charging barrel and an oxidant charging barrel, wherein a coaxial storage unit of photosensitive prepolymer coated metal fuel slurry is arranged in the coaxial feeding charging barrel;
the printing system is used for forming the oxidant and the metal fuel in the composite solid propellant, and the printing system of the metal fuel adopts a coaxial extrusion working mode and comprises a metal fuel printing nozzle and an oxidant printing nozzle;
the metal fuel printing nozzle is connected with the coaxial feed cylinder, and the oxidant printing nozzle is connected with the oxidant cylinder;
the light curing system is used for curing the oxidant and the metal fuel in the formed composite solid propellant, and comprises at least two ultraviolet light curing devices which are distributed on two sides of the forming platform;
during printing, the metal fuel printing nozzle and the oxidant printing nozzle move to the designated area of the forming platform according to the planned printing path, quantitatively extrude slurry, and complete photopolymerization under the action of the ultraviolet curing device.
Preferably, the coaxial storage unit for the photosensitive prepolymer coated metal fuel slurry is prepared by putting a metal fuel preform rod prepared by a freeze casting method into a coaxial feed cylinder filled with the photosensitive prepolymer.
Preferably, the printing system is of a plunger-extrusion type, a pneumatic-extrusion type or a screw-extrusion type.
Compared with the prior art, the invention has the following beneficial effects:
aiming at the potential safety hazard existing in the process of firstly mixing and then manufacturing the oxidizer and the metal fuel in the traditional composite solid propellant, the invention innovatively provides the additive manufacturing method and the additive manufacturing device of the composite solid propellant formed by separating the metal fuel and the oxidizer. The method saves the step of mixing the oxidizer and the metal fuel, ensures the safety of the manufacturing process of the composite solid propellant, and simultaneously improves the processing flexibility of the composite solid propellant. The innovation points of the invention are represented by three points:
1. the method adopts the isolation additive manufacturing, the oxidant and the metal fuel are separately isolated and formed, and an isolation interface between the oxidant and the metal fuel is constructed, so that the step of mixing the oxidant and the metal fuel in the traditional manufacturing process is omitted, and the safety of the manufacturing process of the composite solid propellant is ensured;
2. based on a direct-writing forming technology, double nozzles are adopted to respectively print an oxidant and a metal fuel, wherein one nozzle directly prints high solid-phase oxidant slurry, the other nozzle coaxially extrudes the metal fuel prefabricated fuel, and after forming is completed, ultraviolet light is used for curing the formed oxidant and the formed metal fuel;
3. in the coaxial feed cylinder, a coaxial storage unit is prepared for coaxial extrusion, and a physical isolation interface is constructed between the oxidant and the metal fuel by using a coaxial method during printing.
Therefore, the invention can realize the isolated additive manufacturing of the oxidizer and the metal fuel, can effectively ensure the safety of the manufacturing process of the composite solid propellant, and can realize the manufacturing of the composite solid propellant with a complex structure.
Drawings
FIG. 1 is a schematic diagram of an isolated additive manufacturing apparatus according to the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1;
FIG. 3 is an enlarged view of a portion B of FIG. 1;
FIG. 4 is a schematic diagram of a stack-up configuration of the present invention;
FIG. 5 is a schematic structural diagram of an alternate stacking method according to the present invention.
Wherein: 1-a metallic fuel cartridge; 2-an oxidant cartridge; 3-metal fuel printing nozzle; 4-an oxidant printing nozzle; 5-ultraviolet curing device; 6-forming a platform; 7-metal fuel line unit; 8-a core-shell mechanism formed by the photosensitive prepolymer and the metal fuel line unit; 9-oxidant line unit.
Detailed Description
In order to make the technical solutions of the present invention better understood, 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.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
The invention is described in further detail below with reference to the accompanying drawings:
referring to fig. 1, 2 and 3, an isolated additive manufacturing apparatus for a high safety propellant additive manufacturing method capable of achieving isolated formation of a metal fuel and an oxidizer; the method comprises the following steps: a feeding system, a printing system, a light curing system and a forming platform 6;
the feeding system is used for providing printing materials for the printing system and comprises a coaxial feeding material cylinder 1 and an oxidant material cylinder 2, wherein a coaxial storage unit of photosensitive prepolymer coated metal fuel slurry is arranged in the coaxial feeding material cylinder 1;
the printing system is used for forming the oxidant and the metal fuel in the composite solid propellant, adopts a coaxial extrusion working mode and comprises a metal fuel printing nozzle 3 and an oxidant printing nozzle 4;
the coaxial feed material cylinder 1 is connected with the metal fuel printing nozzle 3, the oxidant material cylinder 2 is connected with the oxidant printing nozzle 4, and the two printing nozzles are matched with the forming platform 6 for use during printing.
The light curing system is used for curing the oxidant and the metal fuel in the formed composite solid propellant, and comprises at least two ultraviolet light curing devices 5, wherein two or more ultraviolet light curing devices 5 are symmetrically distributed on two sides of a forming platform 6;
preferably, the uv curing light may be an LED uv curing lamp;
during printing, the printing nozzle moves to the designated position of the forming platform 6, quantitatively extrudes slurry, and completes photopolymerization reaction under the action of the ultraviolet curing device 5.
When the three-dimensional solid model depositing machine works, two kinds of spray heads are respectively called to deposit liquid materials in a designated area according to the distribution condition of two-dimensional sheet layer materials in the three-dimensional solid model. And in the process of depositing the liquid material, irradiating the liquid material in real time through a light curing system to enable the liquid material to be cured and shaped, so that the formation of a single-layer interface is completed, and the steps are repeated in a circulating manner until the manufacture of the final part is realized.
Further, the stacking mode of the oxidizer and metal fuel forming units in the composite solid propellant can be stacking or alternating stacking. Metal fuel and oxidizer stacked structure using stacked mode as shown in fig. 4, the ratio of metal fuel to oxidizer is determined according to the performance requirement of the solid rocket, in the stacked structure, the ratio of printing layer is the same as the ratio of metal fuel to oxidizer in the vertical direction, and only one material of metal fuel or oxidizer is in the same printing layer.
The alternate stacking structure of the metal fuel and the oxidant in the alternate stacking mode is shown in fig. 5, the ratio of the metal fuel to the oxidant is determined according to the performance requirement of the solid rocket, and the metal fuel and the oxidant are arranged according to the ratio in the same printing layer.
The invention discloses a high-safety propellant additive manufacturing method for the isolated forming of metal fuel and an oxidant, which comprises the steps of designing the component proportion of the oxidant and the metal fuel in a composite solid propellant according to the performance requirement required by a solid rocket engine, designing the accumulation mode of an oxidant and metal fuel forming unit in the composite solid propellant according to the component proportion of the oxidant and the metal fuel in the composite solid propellant, planning a forming path and technological parameters for the isolated additive manufacturing according to the grain structure of the composite solid propellant, and introducing data into isolated additive manufacturing equipment; the method of preparing a metal fuel for use in isolated additive manufacturing comprises: mixing the solute and the solvent with micron aluminum powder as the solute and resin adhesives such as hydroxyl-terminated butadiene as the solvent to prepare metal fuel, and then preparing the metal fuel prefabricated fuel; the method of preparing an oxidizer material in isolated additive manufacturing comprises: and dispersing the oxidant material into the photosensitive prepolymer, and mixing the two to obtain the high solid-phase oxidant slurry. The method comprises the steps of putting metal fuel slurry and photosensitive prepolymer into a coaxial feeding cylinder, putting prepared high solid-phase oxidant slurry into an oxidant cylinder, laying the metal fuel slurry with the inner layer wrapped by the photosensitive prepolymer in the outer layer in the coaxial feeding cylinder on a substrate in a coaxial extrusion mode by an isolation additive manufacturing device according to a forming path and process parameters, directly printing the high solid-phase oxidant slurry in the oxidant cylinder on the substrate, starting a light curing system to cure a formed line unit after printing of a metal fuel line unit or an oxidant line unit is finished, and rapidly shaping the metal fuel line unit and the oxidant line unit to form an isolation interface of the two materials. And finally, repeating the printing process of the step S5 in a layer-by-layer stacking mode until the structure of the composite solid propellant is printed.
The following describes an operation of printing by using the additive manufacturing method of the composite solid propellant formed by isolating the metal fuel and the oxidizer, in a specific embodiment, the specific flow is as follows:
and S1, isolating and additively manufacturing the composite solid propellant by adopting a pneumatic extrusion type direct-writing forming additive manufacturing technology.
S2, in the embodiment, according to the performance requirement of the solid rocket engine, the propellant is a cylinder, the diameter of the propellant is 1000mm, the component proportion of the oxidizer and the metal fuel in the composite solid propellant is designed to be 1:2, the structural accumulation mode of the composite solid propellant is designed to be alternate accumulation, the forming path of the isolated additive manufacturing is 45 degrees, the size of a nozzle is 1mm, the extrusion speed and the nozzle moving speed are both 10mm/S, the initial layer thickness is 1mm, the printing layer thickness is 0.8mm, the printing interval is 0.9mm, the air pressure value is set to be 0.3MPa, and data are led into the isolated additive manufacturing equipment.
S3, preparing metal fuel slurry by using aluminum powder with the particle size of 20 microns as a solute and hydroxyl-terminated butadiene as a solvent in a ball milling mixing mode, and preparing a metal fuel prefabricated core rod by using a freeze casting method; selecting ammonium perchlorate crystal powder with four particle sizes of 15 microns, 30 microns, 60 microns and 120 microns, designing the proportion of the particles with the four particle sizes by adopting a mathematical model Funk-Dinger formula of closest solid particle accumulation, weighing oxidant powder with each particle size according to the proportion, dispersing the oxidant powder into photosensitive resin, and mixing by using a double-paddle planetary vertical mixer to prepare oxidant slurry with the solid content of 80%.
S4, photosensitive resin is firstly put into the coaxial feeding material cylinder 1, then the metal fuel prefabricated core rod is inserted into the photosensitive resin, so that a coaxial material storage unit of metal fuel slurry wrapped by photosensitive prepolymer is prepared, the prepared high solid-phase oxidant slurry is put into the oxidant material cylinder 2, the metal fuel slurry of the coaxial feeding material cylinder 1 and the high solid-phase oxidant slurry in the oxidant material cylinder 2 are coaxially laid by the pneumatic direct-writing forming equipment according to the set forming path and the process parameters, after the printing of one metal fuel line unit or oxidant line unit is finished, the ultraviolet light curing device 5 is simultaneously started, and the formed line unit is cured.
And S5, repeating the printing treatment in the step 4 in a layer-by-layer stacking mode until the structure of the composite solid propellant is printed.
In summary, the invention provides a method for manufacturing a composite solid propellant grain by isolated additive based on an isolated forming technology, which prints the composite solid propellant by adopting a mode of coaxially laying a metal fuel slurry on one nozzle and directly printing an oxidant slurry on the other nozzle, and aims to wrap a photosensitive prepolymer outside a metal fuel by utilizing a coaxial method, wherein the cured photosensitive prepolymer is used as a physical isolation interface between the oxidant and the metal fuel, so that the safety of the manufacturing process of the composite solid propellant is ensured. The method omits the step of mixing the oxidizer and the metal fuel in the traditional process, and can design different ingredient proportions and structures of the oxidizer and the metal fuel according to different performance requirements of the solid rocket engine, thereby not only ensuring the safety of the manufacturing process, but also manufacturing the composite solid propellant with a complex structure.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (10)
1. The additive manufacturing method of the composite solid propellant formed by separating the metal fuel and the oxidizer is characterized in that the oxidizer and the metal fuel are manufactured by separately forming and additive manufacturing in the forming preparation process of a solid propellant grain, namely the oxidizer and the metal fuel are manufactured by separately forming and constructing and forming a separation interface between the oxidizer and the metal fuel, so that the composite solid propellant with a complex structure is manufactured.
2. The method of additive manufacturing of a metal fuel and oxidizer barrier formed composite solid propellant according to claim 1, comprising the steps of:
s1: designing a lean oxygen combustion stage and an oxygen-enriched combustion stage of the composite solid propellant according to the change requirement of the actually required thrust of the solid rocket engine, respectively designing the mass ratio of an oxidant to a metal fuel in the composite solid propellant in the lean oxygen combustion stage and the oxygen-enriched combustion stage, and designing the accumulation mode of a forming unit of the oxidant and the metal fuel in the composite solid propellant according to the mass ratio;
s2: planning a forming path and technological parameters for isolated forming additive manufacturing according to the structure of the composite solid propellant grain, and importing the data obtained by planning into isolated additive manufacturing equipment;
s3: respectively preparing oxidant slurry and metal fuel slurry according to the component proportion of the oxidant and the metal fuel designed by S1, and preparing a photosensitive prepolymer;
s4: printing by adopting an isolation additive manufacturing method, coaxially feeding metal fuel slurry and photosensitive prepolymer, extruding the metal fuel slurry and the photosensitive prepolymer in a coaxial extrusion mode, independently extruding oxidant slurry, and carrying out photocuring forming treatment after printing of one metal fuel line unit or oxidant line unit is finished to form an isolation interface between the metal fuel line unit and the oxidant line unit;
s5: and (5) repeating the printing treatment of the step S4 in a layer-by-layer stacking mode until the structure of the designed composite solid propellant is printed, so as to prepare the high-safety composite solid propellant.
3. The additive manufacturing method of the composite solid propellant formed by separating the metal fuel and the oxidizer according to claim 2, wherein the metal fuel slurry is formed by mixing micron aluminum powder as a solute and a resin binder as a solvent; the oxidant slurry is prepared by dispersing and mixing an oxidant material into a photosensitive prepolymer.
4. The additive manufacturing method of the composite solid propellant formed by separating the metal fuel and the oxidizer according to claim 2 or 3, wherein the solid content of the metal fuel in the metal fuel slurry is 2-20%; the solid phase content in the oxidant slurry is 70-95%.
5. The additive manufacturing method of the composite solid propellant formed by separating the metal fuel and the oxidizer according to claim 2 or 3, wherein the photosensitive prepolymer is a modified adhesive with photocuring property.
6. The additive manufacturing method of the composite solid propellant formed by separating the metal fuel and the oxidizer according to claim 2 or 3, wherein the oxidizer material is at least four ammonium perchlorate crystals with the particle size ranging from 1 to 150 μm, and the adjacent particle size ratio of the at least four ammonium perchlorate crystals is more than 2 from small to large.
7. The additive manufacturing method for the metal fuel and oxidizer isolation formed composite solid propellant according to claim 2, wherein in S1, the stacking mode of the oxidizer and metal fuel forming units in the composite solid propellant is alternate stacking or stacked stacking.
8. An isolated additive manufacturing apparatus for realizing the additive manufacturing method of the composite solid propellant formed by isolating the metal fuel and the oxidizer according to any one of claims 1 to 7, the apparatus comprising: feeding system, printing system, photocuring system and forming platform (6):
the feeding system is used for providing printing materials for the printing system and comprises a coaxial feeding material cylinder (1) and an oxidant material cylinder (2), wherein a coaxial storage unit of photosensitive prepolymer coated metal fuel slurry is arranged in the coaxial feeding material cylinder (1);
the printing system is used for forming the oxidant and the metal fuel in the composite solid propellant, and the printing system of the metal fuel adopts a coaxial extrusion working mode and comprises a metal fuel printing nozzle (3) and an oxidant printing nozzle (4);
wherein, the metal fuel printing nozzle (3) is connected with the coaxial feed cylinder (1), and the oxidant printing nozzle (4) is connected with the oxidant cylinder (2);
the photocuring system is used for curing the oxidant and the metal fuel in the formed composite solid propellant and comprises at least two ultraviolet photocuring devices (5) which are distributed on two sides of a forming platform (6);
during printing, the metal fuel printing nozzle (3) and the oxidant printing nozzle (4) move to a designated area of the forming platform (6) according to a planned printing path, quantitatively extrude slurry, and complete photopolymerization under the action of an ultraviolet curing device.
9. The isolated additive manufacturing device according to claim 8, wherein the coaxial storage unit for the photosensitive prepolymer coated metal fuel slurry is obtained by a coaxial conveying method.
10. The isolated additive manufacturing apparatus of claim 8, wherein the printing system is plunger-extruded, air-extruded, or screw-extruded.
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| CN111575768A (en) * | 2020-05-25 | 2020-08-25 | 吉林大学 | Ceramic metal composite material dual-mode additive manufacturing device and printing method |
| CN111575768B (en) * | 2020-05-25 | 2022-02-01 | 吉林大学 | Ceramic metal composite material dual-mode additive manufacturing device and printing method |
| CN113354494A (en) * | 2021-06-10 | 2021-09-07 | 湖北航天化学技术研究所 | Novel high-density specific impulse propellant and preparation method thereof |
| CN114290662A (en) * | 2021-12-31 | 2022-04-08 | 西安交通大学 | Heat insulation/charge integrated additive manufacturing method for solid rocket engine |
| CN114290662B (en) * | 2021-12-31 | 2023-05-30 | 西安交通大学 | Heat insulation/charge integrated additive manufacturing method for solid rocket engine |
| CN114638138A (en) * | 2022-03-30 | 2022-06-17 | 中国科学院重庆绿色智能技术研究院 | Anisotropic composite propellant additive manufacturing path planning method |
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