CN111559948B - Formula of 3D printing solid propellant/heat insulating layer and integrated preparation method thereof - Google Patents
Formula of 3D printing solid propellant/heat insulating layer and integrated preparation method thereof Download PDFInfo
- Publication number
- CN111559948B CN111559948B CN202010430934.4A CN202010430934A CN111559948B CN 111559948 B CN111559948 B CN 111559948B CN 202010430934 A CN202010430934 A CN 202010430934A CN 111559948 B CN111559948 B CN 111559948B
- Authority
- CN
- China
- Prior art keywords
- propellant
- printing
- insulation layer
- solid
- insulating layer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
- C06B33/06—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 the material being an inorganic oxygen-halogen salt
-
- 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
- C06B33/12—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 the material being two or more oxygen-yielding compounds
-
- 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
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L75/00—Compositions of polyureas or polyurethanes; Compositions of derivatives of such polymers
- C08L75/04—Polyurethanes
- C08L75/14—Polyurethanes having carbon-to-carbon unsaturated bonds
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K3/00—Use of inorganic substances as compounding ingredients
- C08K3/18—Oxygen-containing compounds, e.g. metal carbonyls
- C08K3/20—Oxides; Hydroxides
- C08K3/22—Oxides; Hydroxides of metals
- C08K2003/2296—Oxides; Hydroxides of metals of zinc
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L2205/00—Polymer mixtures characterised by other features
- C08L2205/02—Polymer mixtures characterised by other features containing two or more polymers of the same C08L -group
- C08L2205/025—Polymer mixtures characterised by other features containing two or more polymers of the same C08L -group containing two or more polymers of the same hierarchy C08L, and differing only in parameters such as density, comonomer content, molecular weight, structure
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L2205/00—Polymer mixtures characterised by other features
- C08L2205/03—Polymer mixtures characterised by other features containing three or more polymers in a blend
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L2205/00—Polymer mixtures characterised by other features
- C08L2205/14—Polymer mixtures characterised by other features containing polymeric additives characterised by shape
- C08L2205/16—Fibres; Fibrils
Abstract
The invention discloses a formula of a 3D printing solid propellant/heat insulating layer and a preparation method thereofAThe preparation method comprises the following steps of: 15-25% of photosensitive resin prepolymer, 10-20% of active diluent monomer, 1-3% of photoinitiator, 1-4% of cross-linking agent, 50-65% of oxidant, 5-10% of metal fuel and 1% of functional assistant: 1% -3%; in the heat insulating layer, 20-40% of photosensitive resin prepolymer, 10-30% of active diluent monomer, 2-5% of photoinitiator, 1-4% of cross-linking agent, 30-40% of heat insulating ablation-resistant solid-phase filler and 2% of functional auxiliary agent: 5% -10%. The propellant/heat insulating layer formula adopts the same light-cured resin adhesive system, improves the interface bonding quality of the propellant and the heat insulating layer, improves the interface bonding strength, avoids potential safety hazards caused by the problems of infirm interface bonding and the like in a solid engine, realizes the 3D printing and forming of the integration of the propellant and the heat insulating layer internal and external structures, and is a solid engineMachine fabrication provides a new approach to solution.
Description
Technical Field
The invention relates to the technical field of composite solid propellants, in particular to a formula of a 3D printing solid propellant/heat insulating layer and an integrated preparation method thereof.
Background
With the development of missile weapon technology, the charge design of a solid engine is more and more complex, the defects and the limitations of the traditional charge process in the manufacture of a complex-drug type solid engine are more and more prominent, and the charge process is mainly embodied in the following two aspects: (1) for the explosive column with a complex internal combustion surface structure, the manufacturing and processing difficulty is high due to the limitation of the design and removal of a core mold; (2) the heat insulation layer and the propellant complete charging in a formula after step forming, the assembly surface is bonded by the lining, the interface debonding condition cannot be completely avoided, and great potential safety hazards exist.
At present, 3D printing photocuring molding data of a propellant in the technical field of solid propellants is published, but the information related to the integrated molding of the solid propellant/a heat insulating layer is not published temporarily, and the main reasons are that the photocuring adhesive matrix material systems required by photocuring formulas suitable for two materials are different, the requirements on parameters such as the diameter, the wavelength and the like of an ultraviolet light source are different, the molding shrinkage of the formulas are different, and interface defects are easily generated, so that the interface bonding force of the two materials is not firm and the like.
Disclosure of Invention
The invention provides a formula and an integrated preparation method of a 3D printing solid propellant/heat insulating layer, which can realize the integrated 3D printing and manufacturing of the propellant/heat insulating layer and solve the problems of insecure interface bonding, easy debonding and the like between the propellant and the heat insulating layer in the existing production process.
The technical scheme of the invention is that a solid propellant/heat insulating layer formula is printed in a 3D mode, and raw materials of the solid propellant/heat insulating layer formula comprise a propellant and a heat insulating layer raw material; wherein the content of the first and second substances,
the propellant comprises the following raw materials in parts by mass: prepolymer of photosensitive resin: 15% -25%, reactive diluent monomer: 10% -20%, photoinitiator: 1% -3%, cross-linking agent: 1% -4%, oxidant: 50% -65%, metal fuel: 5-10%, functional assistant 1: 1% -3%;
the heat insulation layer comprises the following raw materials in mass fraction: prepolymer of photosensitive resin: 20 to 40 percent; reactive diluent monomer: 10% -30%; photoinitiator (2): 2% -5%; a crosslinking agent: 1% -4%; heat-insulating ablation-resistant solid-phase filler: 30% -40%; functional auxiliary agent 2: 5% -10%;
the functional assistant 1 comprises a leveling agent, a burning rate catalyst and a bonding agent; the functional assistant 2 mainly comprises a leveling agent, a plasticizer and a process assistant.
Further, the photosensitive resin prepolymer is one or a combination of polyether urethane acrylate and polyester urethane acrylate.
Further, the reactive diluent monomer is one or a combination of more of 6-hexanediol diacrylate, low molecular aliphatic urethane acrylate and cyclotrimethylolpropane formal acrylate.
Further, the photoinitiator is one or a combination of 2-hydroxy-2-methyl-1-phenyl-1-acetone, 2,4, 6-trimethylbenzoyl-diphenylphosphine oxide and 1-hydroxycyclohexyl phenyl ketone.
Further, the cross-linking agent is one or a combination of several of ethoxylated trimethylolpropane triacrylate, ethoxylated pentaerythritol tetraacrylate and trimethylolpropane triacrylate.
Further, the oxidant is one or a combination of more of spherical ammonium perchlorate, potassium perchlorate and 1, 1-dihydroxy-5, 5-bitetrazole diamine salt; the metal fuel is spherical aluminum powder.
Further, the functional assistant 1 is one or a combination of a plurality of polyacrylate, octoxin, oxamide, tris-1- (2-Methyl Aziridine) Phosphine Oxide (MAPO) and an alcohol amine bonding agent (LBA-303). The functional assistant 2 is one or a combination of a plurality of polyacrylate, dibutyl phthalate, diisooctyl sebacate, methyl stearate and chlorinated paraffin.
Further, the heat-insulating ablation-resistant solid-phase filler is one or a combination of aramid pulp, asbestos, zinc oxide and white carbon black.
The invention also relates to a method for the integrated preparation of a propellant/thermal insulation layer according to the 3D printed solid propellant/thermal insulation layer formulation, comprising the following steps:
(1) placing the photosensitive resin prepolymer, the reactive diluent monomer, the photoinitiator and the cross-linking agent into a stirring container according to the formula proportion, stirring at the temperature of 30-40 ℃ and the rotating speed of 100-200 r/min, starting stirring to uniformly mix the components, and defoaming in vacuum to form a photocuring adhesive matrix material;
(2) adding an oxidant, a metal fuel and a functional additive 1 into a container according to the formula requirement of a propellant, and uniformly mixing to form photocuring propellant slurry;
(3) preparing a photocuring adhesive matrix material according to the method in the step (1), adding a heat-insulating ablation-resistant solid-phase filler and a functional auxiliary agent 2 into the photocuring adhesive matrix material, and uniformly mixing the materials to form photocuring heat-insulating layer slurry;
(4) respectively placing the photocuring propellant slurry and the heat insulation layer slurry which are uniformly mixed in the step (2) and the step (3) into two charging barrels of a 3D printer, discharging through different extrusion nozzles, adjusting printing parameters, controlling the discharging sequence and the discharging amount of the two extrusion nozzles, and realizing synchronous printing of the inside and the outside of the propellant/the heat insulation layer by layer;
(5) and (5) after printing is finished, cleaning the sample piece by adopting ethyl acetate to obtain a printing sample of the outer heat insulation layer and the inner propellant.
Further, when 3D printing is carried out in the step (4), the wavelength of an ultraviolet light source is selected to be 200-350 microns, the diameter of an extrusion nozzle of photocuring propellant slurry is 1-2 mm, the diameter of an extrusion nozzle of photocuring heat insulation layer slurry is 2-3 mm, discharging is carried out through different extrusion nozzles, the layer-by-layer printing speed is set to be 10-20 s/layer, the discharging sequence and the discharging amount of the two extrusion nozzles are controlled, discharging and curing of the nozzles are carried out synchronously, and synchronous printing of the inner layer and the outer layer of the propellant/heat insulation layer sample piece is achieved.
The invention has the following beneficial effects:
(1) the propellant/heat insulation layer sample piece is prepared in a 3D printing mode, so that remote production control is realized, man-machine isolation is realized, personnel safety is guaranteed to a greater extent, and the manufacturing cost is saved.
(2) The formula of the propellant and the heat insulating layer adopts a photocuring matrix material system, and the interface between the propellant and the heat insulating layer is tightly adhered without using a lining, so that the passive quality of a solid engine is reduced, and the missile range is improved.
(3) The invention adopts the same light-cured adhesive matrix material in the propellant/heat-insulating layer formula, can carry out light-cured 3D printing integrated manufacturing, solves the problem of auxiliary agent migration caused by the compatibility of formula components, concentration difference and the like between the propellant and the heat-insulating layer in the production of the existing solid engine grain, has good improvement effect on the problems of interface bonding performance reduction of the heat-insulating layer and the propellant, debonding caused by the interface bonding insecurity and the like in the solid engine, and avoids potential safety hazards caused by the problems of interface bonding insecure and the like in the solid engine.
(4) The solid propellant/heat-insulating layer photocuring 3D printing integrated manufacturing process realizes synchronous printing of the heat-insulating layer and the propellant, the propellant and the heat-insulating layer adopt the same photocuring adhesive base material, namely photosensitive resin pre-polymerized monomer, active diluent monomer and photoinitiator, the pre-polymerized monomer in the propellant and the photosensitive resin or the active monomer in the heat-insulating layer perform photocuring reaction under the action of the photoinitiator, the interface is combined in a chemical bond mode, the two materials are tightly combined from a linear unit, the interface bonding firmness of the two materials is finally ensured, the pursuit of the integrated manufacturing of the inner layer and the outer layer of an engine grain is realized, and a new solution is provided for the manufacturing of a solid engine.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to examples, but those skilled in the art will appreciate that the following examples are only illustrative of the present invention and should not be construed as limiting the scope of the present invention.
Example 1:
3D printing solid propellant/heat insulating layer formula and integrated preparation method thereof, wherein the formula composition of the propellant/heat insulating layer material is shown in the following table 1.
TABLE 1
The preparation method comprises the following steps:
placing the photosensitive resin prepolymer, the active diluent monomer, the photoinitiator and the cross-linking agent in a stirring container according to the mass ratio, stirring at the temperature of 30-40 ℃ and at the rotating speed of 100-200 r/min to uniformly mix, and defoaming in vacuum to form the photocuring matrix adhesive; adding an oxidant, a metal fuel and a functional assistant 1 into a container, and slowly stirring to uniformly mix the components to form photocuring propellant slurry; preparing light-cured heat insulating layer slurry in another container according to the same method; respectively placing the uniformly mixed photocuring propellant slurry and heat insulation layer slurry into two charging barrels of a printer, discharging by different extrusion nozzles, adjusting printing parameters, controlling the discharging sequence and the discharging amount of the two extrusion nozzles, and synchronously printing the inside and the outside of the propellant/heat insulation layer by layer; and (5) after printing is finished, cleaning the sample piece by adopting ethyl acetate to obtain a printing sample of the outer heat insulation layer and the inner propellant. The relevant performance test data are shown in table 1.
Example 2:
a solid propellant/thermal insulation layer formulation for 3D printing and an integrated method for making the same, wherein the composition and related properties of the propellant/thermal insulation layer material formulation are shown in table 2 below, and the method is the same as in example 1.
TABLE 2
Example 3:
a 3D printed solid propellant/insulation layer formulation and an integrated process for the preparation thereof, wherein the propellant/insulation layer material formulation composition and associated properties are given in table 3 below, the process being the same as in example 1.
TABLE 3
Claims (6)
1. The solid propellant/thermal insulation layer material for 3D integrated printing is characterized in that raw materials comprise a propellant and a thermal insulation layer raw material; wherein the content of the first and second substances,
the propellant comprises the following raw materials in parts by mass: prepolymer of photosensitive resin: 15% -25%, reactive diluent monomer: 10-20%, photoinitiator: 1% -3%, crosslinking agent: 1% -4%, oxidant: 50% -65%, metal fuel: 5-10%, functional additive 1: 1% -3%;
the heat insulation layer comprises the following raw materials in mass fraction: prepolymer of photosensitive resin: 20% -40%; reactive diluent monomer: 10% -30%; photoinitiator (2): 2% -5%; a crosslinking agent: 1% -4%; heat-insulating ablation-resistant solid-phase filler: 30% -40%; functional auxiliary agent 2: 5% -10%;
the functional assistant 1 comprises a leveling agent, a burning rate catalyst and a bonding agent; the functional assistant 2 mainly comprises a flatting agent, a plasticizer and a process assistant;
the photosensitive resin prepolymer is one or two of polyether type polyurethane acrylate and polyester type polyurethane acrylate;
the cross-linking agent is one or a combination of more of ethoxylated trimethylolpropane triacrylate, ethoxylated pentaerythritol tetraacrylate and trimethylolpropane triacrylate;
when the 3D printing integrated solid propellant/heat insulation layer material is prepared, the method comprises the following steps:
(1) placing the photosensitive resin prepolymer, the reactive diluent monomer, the photoinitiator and the cross-linking agent into a stirring container according to the formula proportion requirement, stirring at the temperature of 30-40 ℃ and at the rotating speed of 100-200 r/min, starting stirring to uniformly mix the components, and defoaming in vacuum to form a photocuring adhesive matrix material;
(2) adding an oxidant, a metal fuel and a functional additive 1 into a container according to the formula requirement of a propellant, and uniformly mixing to form photocuring propellant slurry;
(3) preparing a photocuring adhesive matrix material according to the method in the step (1), adding a heat-insulating ablation-resistant solid-phase filler and a functional auxiliary agent 2 into the photocuring adhesive matrix material, and uniformly mixing the materials to form photocuring heat-insulating layer slurry;
(4) respectively placing the photocuring propellant slurry and the heat insulation layer slurry which are uniformly mixed in the step (2) and the step (3) into two charging barrels of a 3D printer, discharging through different extrusion nozzles, adjusting printing parameters, controlling the discharging sequence and the discharging amount of the two extrusion nozzles, and realizing synchronous printing of the inside and the outside of the propellant/the heat insulation layer by layer; when 3D printing is carried out, the wavelength of an ultraviolet light source is selected to be 200 nm-350 nm, the diameter of an extrusion nozzle of photo-curing propellant slurry is 1 mm-2 mm, the diameter of an extrusion nozzle of photo-curing heat insulation layer slurry is 2 mm-3 mm, discharging is carried out through different extrusion nozzles, the layer-by-layer printing speed is set to be 10 s-20 s/layer, the discharging sequence and the discharging amount of the two extrusion nozzles are controlled, discharging and curing of the nozzles are carried out synchronously, and synchronous printing of the inside and the outside of a propellant/heat insulation layer sample piece layer by layer is realized;
(5) and (5) after printing is finished, cleaning the sample piece by adopting ethyl acetate to obtain a printing sample of the outer heat insulation layer and the inner propellant.
2. The solid propellant/thermal insulation layer material for 3D monolithic printing according to claim 1, characterized in that: the reactive diluent monomer is one or a combination of more of 1, 6-hexanediol diacrylate, low molecular aliphatic urethane acrylate and cyclotrimethylolpropane formal acrylate.
3. The solid propellant/thermal insulation layer material for 3D monolithic printing according to claim 1, characterized in that: the photoinitiator is one or a combination of 2-hydroxy-2-methyl-1-phenyl-1-acetone, 2,4, 6-trimethylbenzoyl-diphenylphosphine oxide and 1-hydroxycyclohexyl phenyl ketone.
4. The solid propellant/thermal insulation layer material for 3D monolithic printing according to claim 1, characterized in that: the oxidant is one or a combination of more of spherical ammonium perchlorate, potassium perchlorate and 1, 1-dihydroxy-5, 5-bitetrazole dihydroxylamine; the metal fuel is spherical aluminum powder.
5. The solid propellant/thermal insulation layer material for 3D monolithic printing according to claim 1, characterized in that: the functional additive 1 is one or a combination of a plurality of polyacrylate, octoxin, oxamide, tris-1- (2-methyl aziridine) phosphine oxide and alcamines bonding agent; the functional assistant 2 is one or a combination of a plurality of polyacrylate, dibutyl phthalate, diisooctyl sebacate, methyl stearate and chlorinated paraffin.
6. The solid propellant/thermal insulation layer material for 3D monolithic printing according to claim 1, characterized in that: the heat-insulating ablation-resistant solid-phase filler is one or a combination of aramid pulp, asbestos, zinc oxide and white carbon black.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010430934.4A CN111559948B (en) | 2020-05-20 | 2020-05-20 | Formula of 3D printing solid propellant/heat insulating layer and integrated preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010430934.4A CN111559948B (en) | 2020-05-20 | 2020-05-20 | Formula of 3D printing solid propellant/heat insulating layer and integrated preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111559948A CN111559948A (en) | 2020-08-21 |
| CN111559948B true CN111559948B (en) | 2022-03-04 |
Family
ID=72074811
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010430934.4A Active CN111559948B (en) | 2020-05-20 | 2020-05-20 | Formula of 3D printing solid propellant/heat insulating layer and integrated preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111559948B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112094164B (en) * | 2020-09-16 | 2022-05-17 | 湖北三江航天江河化工科技有限公司 | Photocuring propellant and preparation method thereof |
| CN113354494B (en) * | 2021-06-10 | 2022-07-29 | 湖北航天化学技术研究所 | High-density specific impulse propellant and preparation method thereof |
| CN114014738B (en) * | 2021-10-18 | 2022-08-19 | 西安近代化学研究所 | Combustible cartridge/box slurry formula and preparation method of combustible cartridge/box |
| 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 |
| CN115304435B (en) * | 2022-06-30 | 2023-11-10 | 湖北航天化学技术研究所 | Rapid additive manufacturing method for solid propellant grains |
| CN115286477A (en) * | 2022-06-30 | 2022-11-04 | 湖北航天化学技术研究所 | Solid propellant/coating layer integrated additive manufacturing interface structure |
| CN115677440A (en) * | 2022-11-16 | 2023-02-03 | 北方斯伦贝谢油田技术（西安）有限公司 | Water-resistant acid-corrosion-resistant solid propellant, and preparation method and application thereof |
| CN115806456A (en) * | 2022-11-23 | 2023-03-17 | 西安近代化学研究所 | Co-MOF-added photocuring powder and preparation method thereof |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4956397A (en) * | 1989-07-17 | 1990-09-11 | The United States Of America As Represented By The Secretary Of The Air Force | Insulating liner for solid rocket motor containing vulcanizable elastomer and a bond promoter which is a novolac epoxy or a resole treated cellulose |
| CN107283826A (en) * | 2017-06-28 | 2017-10-24 | 南京理工大学 | A kind of solid propellant 3D printing forming method solidified based on ultraviolet light |
| CN109503299A (en) * | 2018-12-18 | 2019-03-22 | 辽宁省轻工科学研究院有限公司 | Photo-cured solid propellant slurry and preparation method thereof and forming method |
| CN110425056A (en) * | 2019-07-16 | 2019-11-08 | 西北工业大学 | One kind promoting array structure based on 3D printing technique miniature solid |
| CN110467704A (en) * | 2019-08-02 | 2019-11-19 | 济南赢科新材料科技有限公司 | A kind of 3D printing LED light solidification flexible photosensitive resin and preparation method thereof |
-
2020
- 2020-05-20 CN CN202010430934.4A patent/CN111559948B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN111559948A (en) | 2020-08-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111559948B (en) | Formula of 3D printing solid propellant/heat insulating layer and integrated preparation method thereof | |
| CN109627133B (en) | Thermoplastic composite solid propellant and preparation method thereof | |
| CN109438149B (en) | Thermosetting composite solid propellant and preparation method thereof | |
| CN106831279B (en) | Room temperature curing propellant | |
| CN107867961B (en) | Method for improving mechanical property of butylated hydroxytoluene propellant and butylated hydroxytoluene propellant prepared by same | |
| CN103711609B (en) | For improving the method for EPDM heat insulation layer, HTPB lining and NEPE propellant agent interfacial adhesion | |
| CN106631644B (en) | A kind of azide propellant and preparation method thereof having superior low-temperature adaptability | |
| CN109232848B (en) | DDI lining layer for solid rocket engine medicine loading and application method thereof | |
| CN113683473B (en) | Polyether-based composite solid propellant 3D printing ink and preparation method thereof | |
| CN112898106B (en) | High-burning-rate propellant for platform combustion and preparation method thereof | |
| CN112250529A (en) | High-energy propellant for variable thrust solid rocket engine and preparation process thereof | |
| CN108129248B (en) | Method for solving post-curing problem of room-temperature cured butyl hydroxyl propellant and prepared product | |
| CN109486201B (en) | Self-crosslinking type silicon-boron-containing high polymer-based ablation-resistant heat-insulating material and preparation method thereof | |
| CN103351459B (en) | The tackiness agent of a kind of ester class plasticising and preparation method | |
| CN110423184A (en) | A kind of solid propellant rocket propellant and preparation method thereof | |
| CN109628053B (en) | Formula and manufacturing method of combustible lining | |
| CN113683994A (en) | Modified cyanate ester-based adhesive and preparation method thereof | |
| US20060144555A1 (en) | Method for producing molds for lost wax precision casting | |
| CN112094164B (en) | Photocuring propellant and preparation method thereof | |
| CN111560155A (en) | Epoxy resin system compatible with liquid oxygen for prepreg and preparation method thereof | |
| KR101974125B1 (en) | Solid propellant composition and manufacturing method thereof | |
| CN109824852A (en) | A kind of polyurethane curing agent | |
| CN110746854B (en) | Room temperature fast curing coating with high infrared radiation coating as cured product and preparation method thereof | |
| CN111233594A (en) | A is prepared from3Plasticized propynyl-terminated polybutadiene composite propellant and preparation method thereof | |
| CN111333474A (en) | Solid propellant and horizontal additive manufacturing method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |