CN115403433B - Interface binder for combined charge of solid propellant and preparation process of charge - Google Patents
Interface binder for combined charge of solid propellant and preparation process of charge Download PDFInfo
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- CN115403433B CN115403433B CN202210978417.XA CN202210978417A CN115403433B CN 115403433 B CN115403433 B CN 115403433B CN 202210978417 A CN202210978417 A CN 202210978417A CN 115403433 B CN115403433 B CN 115403433B
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- 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
- 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
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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 an interface binder for combined charge of a solid propellant and a charge preparation process, wherein the interface binder comprises hydroxypropyl emulsion, aliphatic polyisocyanate, polyurethane water-removing agent and polyurethane defoamer; the weight percentage of the hydroxypropyl emulsion is 72.0 percent, the aliphatic polyisocyanate is 24.5 percent, the polyurethane water scavenger is 3.0 percent, and the polyurethane defoamer is 0.5 percent. The invention solves the problems of weak mechanical property and the like of the interface of the solid propellant combined charge, provides the solid propellant combined charge interface adhesive which has simple process, stable structure and firm interface adhesion, and simultaneously provides a preparation process of the charge.
Description
Technical Field
The invention belongs to the technical field of solid propellants, and mainly relates to an interface binder for combined charge of a solid propellant and a charge preparation process.
Background
In order to improve the maneuverability, the sudden-prevention capability and the hit precision of the missile, the rocket engine as a power device needs to have the capability of controllable thrust and multiple starting, namely, the energy output mode of the rocket engine needs to be managed. The design scheme of the multistage thrust engine mainly comprises a multistage engine and a single-chamber multi-thrust engine, and particularly the single-chamber multi-thrust engine technology has been applied to rocket missiles and tactical missiles due to the advantages of simple structure, convenient thrust adjustment, excellent comprehensive performance of the engine and the like. The integrated propellant combined grain made of different propellant grains through the interface bonding technology is applied to a single-chamber variable-thrust missile engine, so that the missile engine can realize flexible output and reliable conversion of multi-stage complex thrust such as launching, speed increasing, cruising, tail end accelerating and the like, and has the advantages of simplifying the engine structure, facilitating thrust adjustment, flexible energy output and the like, and the comprehensive performance of the engine can be remarkably improved. In order to ensure the stable operation of the single-chamber variable-thrust missile engine, the reliable transfer of thrust output is important, this is directly related to the interfacial adhesion properties between the multi-stage propellant grains in the engine. Interface mechanical properties of solid propellant combined grain, explosives and powders journal, 2014, 37 (1): 74-77, wherein the interfacial mechanical property of a combined grain is disclosed, the maximum tensile strength of the interface is 3.68MPa (20 ℃), and the use requirement of the existing weapon cannot be met.
Disclosure of Invention
The invention aims to provide an interface binder for combined charge of a solid propellant and a charge preparation process.
In order to achieve the above object, the present invention provides a technical solution comprising:
an interface binder for a solid propellant composite charge comprises a hydroxypropyl emulsion, aliphatic polyisocyanate, a polyurethane water scavenger and a polyurethane defoamer; the weight percentage of the hydroxypropyl emulsion is 72.0 percent, the aliphatic polyisocyanate is 24.5 percent, the polyurethane water scavenger is 3.0 percent, and the polyurethane defoamer is 0.5 percent.
Optionally, the preparation steps are as follows:
(1) Uniformly mixing the hydroxypropyl emulsion and the polyurethane dehydrator according to the formula amount, and then carrying out vacuum standing at 60 ℃ to dehydrate the hydroxypropyl emulsion;
(2) Uniformly mixing the dehydrated hydroxypropyl emulsion, aliphatic polyisocyanate and polyurethane defoamer, and then standing in vacuum at 30 ℃ to obtain the polyurethane foam.
Optionally, the standing time in the step (1) is 4 hours;
the standing time in the step (2) is 30min.
The solid propellant combined charge is formed by stacking multiple stages of grains, and adjacent grains are bonded by adopting the interfacial adhesive of any solid propellant combined charge.
Optionally, the solid propellant combinationThe amount of interfacial adhesive used in the powder charge is calculated by the application area, the mass of the adhesive is M (g) = (0.12-0.24) S, S is the area of the bonding surface, and the unit is cm 2 。
Optionally, the bonding surface is further processed in the following manner: grinding wheel grinding, turning annular grooves and grinding paper grinding.
Optionally, the combined charge comprises a low-combustion-rate propellant charge, a medium-combustion-rate propellant charge and a high-combustion propellant charge which are sequentially stacked along the axial direction, and the specific steps are as follows: (1) The low-combustion-rate propellant slurry is turned into a required drug form for standby after being cast and completely solidified; (2) The medium-combustion-rate propellant slurry is turned into a required drug form for standby after being cast and completely solidified; (3) The high-combustion-speed propellant slurry is turned into a required drug form for standby after being cast and completely solidified; (4) And uniformly coating the interface adhesive of the solid propellant combined charge between interfaces, and standing in vacuum to form the integrated solid propellant combined charge.
Optionally, the low-combustion-rate propellant charge is cured for 96 hours at a temperature of 50-70 ℃;
the medium-combustion-rate propellant charge is solidified for 96 hours at the temperature of 50-70 ℃;
uniformly coating the interface adhesive of the solid propellant combined charge between the charge interfaces of the low-combustion-rate propellant charge and the medium-combustion-rate propellant charge, and standing for 24 hours at 60 ℃ in vacuum to obtain a two-stage integrated solid propellant combined charge;
curing the high-combustion-speed propellant for 96 hours at the temperature of 50-70 ℃;
and uniformly coating the interface adhesive of the solid propellant combined charge on the interface between the two-stage integrated solid propellant combined charge and the grain of the high-combustion-speed propellant charge, and standing at 60 ℃ in vacuum for 24 hours to obtain the solid propellant combined charge.
Optionally, a low burn rate propellant charge, a medium burn rate propellant charge and a high burn propellant charge are provided in a bottom-to-top sequence.
Optionally, the method specifically comprises the following steps:
(1) Solidifying the low-combustion-rate propellant slurry after casting to obtain low-combustion-rate propellant powder;
(2) The low-combustion-rate propellant charge is fixed below the casting tool, the interface binder of the solid propellant combined charge is smeared on the top end surface of the low-combustion-rate propellant charge, and the medium-combustion-rate propellant slurry is cast on the low-combustion-rate propellant charge and solidified for 24 hours to obtain the medium-combustion-rate propellant charge;
(3) The interface binder of the solid propellant combined charge is smeared on the top end surface of the medium-combustion-speed propellant charge, and the high-combustion-speed propellant slurry is cast on the medium-combustion-speed propellant charge, and is solidified for 72 hours to obtain the integrated solid propellant combined charge.
The invention has the advantages that:
the invention solves the problems of weak mechanical property and the like of the interface of the solid propellant combined charge, provides the solid propellant combined charge interface adhesive which has simple process, stable structure and firm interface adhesion, and simultaneously provides a preparation process of the charge.
Drawings
FIG. 1 shows a failure adhesive obtained from an initial formulation;
FIG. 2 shows turning of an annular groove after curing of a propellant;
FIG. 3 illustrates coarse sandpaper sanding after curing of the propellant;
FIG. 4 illustrates grinding wheel dressing after curing of the propellant;
fig. 5 is a schematic diagram of the integrated solid propellant combination charge of the present invention.
Detailed Description
The present invention will be described in further detail with reference to specific examples.
The interface binder of the solid propellant combined charge comprises hydroxypropyl emulsion, aliphatic polyisocyanate, polyurethane water-removing agent and polyurethane defoamer; the weight percentage of the hydroxypropyl emulsion is 72.0 percent, the aliphatic polyisocyanate is 24.5 percent, the polyurethane water scavenger is 3.0 percent, and the polyurethane defoamer is 0.5 percent.
Optionally, the preparation steps are as follows:
(1) Uniformly mixing the hydroxypropyl emulsion and the polyurethane dehydrator according to the formula amount, and then carrying out vacuum standing at 60 ℃ to dehydrate the hydroxypropyl emulsion;
(2) Uniformly mixing the dehydrated hydroxypropyl emulsion, aliphatic polyisocyanate and polyurethane defoamer, and then standing in vacuum at 30 ℃ to obtain the polyurethane foam.
(1) The standing time is 4h; the standing time in (2) was 30 minutes.
The invention relates to a preparation process of a solid propellant combined charge, which is formed by stacking multiple stages of grains, wherein adjacent grains are bonded by adopting the interfacial adhesive of the solid propellant combined charge.
In embodiments of the present disclosure, the interfacial binder of the solid propellant composite charge is used in an amount of M (g) = (0.12-0.36) S, S being the area of the bonding face in cm, as measured by the application area between the interfaces 2 。
In an embodiment of the present disclosure, the bonding surface is further processed in a manner including: grinding wheel grinding, turning annular grooves and grinding paper grinding. In grinding the grinding wheel, grinding the bonding surface by adopting a brown alumina grinding wheel, firstly, carrying out preliminary grinding by adopting a 46# coarse grain grinding wheel, and then, carrying out further grinding by adopting a 100# fine grain grinding wheel. In turning the annular groove, a milling cutter is adopted to process the annular groove, the width of the annular groove is 10mm, and the depth of the annular groove is 5mm. In the sand paper polishing, 60-mesh sand paper is adopted for preliminary polishing, and then 100-mesh sand paper is adopted for further polishing.
In an embodiment of the present disclosure, the composite charge comprises a low burn rate propellant charge, a medium burn rate propellant charge and a high burn propellant charge stacked in sequence in an axial direction, the specific steps being as follows: (1) The low-combustion-rate propellant slurry is turned into a required drug form for standby after being cast and completely solidified; (2) The medium-combustion-rate propellant slurry is turned into a required drug form for standby after being cast and completely solidified; (3) The high-combustion-speed propellant slurry is turned into a required drug form for standby after being cast and completely solidified; (4) And uniformly coating the interface adhesive of the solid propellant combined charge between interfaces, and standing in vacuum to form the integrated solid propellant combined charge.
In embodiments of the present disclosure, the low burn rate propellant charge is cured for 96 hours at a temperature of 50-70 ℃; the medium-combustion-rate propellant charge is solidified for 96 hours at the temperature of 50-70 ℃; uniformly coating an interface binder of the solid propellant combined charge between a low-combustion-speed propellant charge and a medium-combustion-speed propellant charge interface, and standing for 24 hours at 60 ℃ in vacuum to obtain a two-stage integrated solid propellant combined charge;
curing the high-combustion-speed propellant for 96 hours at the temperature of 50-70 ℃; and uniformly smearing an interface adhesive of the solid propellant combined charge on an interface between the two-stage integrated solid propellant combined charge and a grain of the high-combustion-speed propellant charge, and standing at 60 ℃ in vacuum for 24 hours to obtain the solid propellant combined charge.
In an embodiment of the present disclosure, a low burn rate propellant charge, a medium burn rate propellant charge, and a high burn propellant charge are provided in a bottom-to-top order.
In an embodiment of the present disclosure, specifically including:
(1) Solidifying the low-combustion-rate propellant slurry after casting to obtain low-combustion-rate propellant powder; (2) The low-combustion-rate propellant charge is fixed below the casting tool, the interface binder of the solid propellant combined charge is smeared on the top end surface of the low-combustion-rate propellant charge, and the medium-combustion-rate propellant slurry is cast on the low-combustion-rate propellant charge and solidified for 24 hours to obtain the medium-combustion-rate propellant charge; (3) The interface binder of the solid propellant combined charge is smeared on the top end surface of the medium-combustion-speed propellant charge, and the high-combustion-speed propellant slurry is cast on the medium-combustion-speed propellant charge, and is solidified for 72 hours to obtain the integrated solid propellant combined charge. The low-combustion-rate propellant is not completely cured after 24 hours of curing, and the nitrocotton which is not completely cured in the propellant forms a swelling interpenetrating network with the nitrocotton of the medium-combustion-rate propellant, so that the two-stage integrated solid propellant combined charge is formed. The medium-combustion-rate propellant is not completely cured after 24 hours of curing, and the nitrocotton which is not completely cured in the propellant forms a swelling interpenetrating network with the nitrocotton of the high-combustion-rate propellant, so that the three-stage integrated solid propellant combined charge is formed. And then the bonding agent smeared on the interface is matched, a certain bonding fixation is realized between the butt joint interfaces under the action of gravity, and a swelling interpenetrating network is formed under the interpenetrating action of nitrocotton between the interfaces, so that the bonding effect is further improved, and the integration is stronger.
The low-combustion-rate propellant slurry is prepared by fully mixing a liquid propellant component (mainly comprising nitroglycerin) and a solid propellant component (mainly comprising nitrocotton and black cable gold) through a kneader to obtain the required low-combustion-rate propellant slurry, then injecting the low-combustion-rate propellant slurry into a cylindrical mold in a vacuum casting mode, casting the low-combustion-rate propellant slurry into a required shape, solidifying for 24 hours, and turning into a required medicament form for later use.
The medium-combustion-rate propellant slurry is prepared by fully mixing a liquid propellant component (mainly comprising nitroglycerin) and a solid propellant component (mainly comprising nitrocotton and black cable gold) through a kneader to obtain the required medium-combustion-rate propellant slurry, placing the turned low-combustion-rate propellant slurry under a casting tool for fixing, casting the medium-combustion-rate propellant slurry at the upper end of the low-combustion-rate propellant, and turning the medium-combustion-rate propellant slurry into the required medicament type after 24h of solidification.
The high-combustion-rate propellant slurry is prepared by fully mixing a liquid propellant component (mainly comprising nitroglycerin) and a solid propellant component (mainly comprising nitrocotton and black-wire gold) through a kneader to obtain the required high-combustion-rate propellant slurry, placing a cast low-combustion-rate propellant and a cast medium-combustion-rate propellant under a casting tool, casting the high-combustion-rate propellant slurry into a cylindrical mold at the upper end of the medium-combustion-rate propellant by adopting a vacuum casting method, placing the turned medium-combustion-rate propellant under the casting tool for fixing, casting the high-combustion-rate propellant slurry at the upper end of the medium-combustion-rate propellant, and curing for 72 hours to prepare the integrated solid propellant combined charge (figure 5).
Example 1
The following description of the initial embodiments of the present invention will be provided in order to more readily understand the advantages and features of the present invention and to more clearly and clearly define the scope of the present invention.
The formula of the initial adhesive is as follows (mass percent): 75.0% of a hydroxypropyl emulsion of type HPA-1004 and 25.0% of an aliphatic polyisocyanate of type N3390. The preparation steps of the initial adhesive are as follows: (1) Taking out 72.0% of hydroxypropyl emulsion with the model HPA-1004 and aliphatic polyisocyanate with the model N3390, pouring the hydroxypropyl emulsion and the aliphatic polyisocyanate into the same container, uniformly mixing the hydroxypropyl emulsion and the aliphatic polyisocyanate under the stirring of a 1000r/min stirring paddle, placing the mixture in a vacuum oven at 30 ℃ for 30min, and finally obtaining the adhesive, wherein the adhesive prepared by the formula has agglomeration and bubbles (shown in figure 1) and loses the bonding effect.
Example 2
The following detailed description of the modified embodiments of the present invention will provide those skilled in the art with a better understanding of the advantages and features of the present invention, so as to make the scope of the present invention more clearly and clearly defined.
The formula and the preparation steps of the solid propellant combined charge interface adhesive are as follows: the adhesive comprises the following components in percentage by mass: 52.0% of a hydroxypropyl emulsion of type HPA-1004, 44.5% of an aliphatic polyisocyanate of type N3390, 3.0% of a polyurethane water scavenger of type PG-101, 0.5% of a polyurethane defoamer of type DT-69. The preparation steps of the adhesive are as follows: (1) pretreatment of raw materials. Taking out the hydroxypropyl emulsion with the model HPA-1004 of which the formula mass fraction is 52.0%, adding the polyurethane water scavenger with the model PG-101 of which the formula mass fraction is 3.0%, uniformly mixing the components under the stirring of a stirring paddle of 800r/min, and placing the components in a vacuum oven at 60 ℃ for 4 hours to realize the dehydration of the hydroxypropyl emulsion; (2) obtaining an adhesive. Pouring the dehydrated hydroxypropyl emulsion with the model of HPA-1004 and the aliphatic polyisocyanate with the model of N3390 into the same container, adding 0.5% of polyurethane defoamer with the model of DT-69, uniformly mixing under the stirring of a stirring paddle with the speed of 1000r/min, and then placing in a vacuum oven with the temperature of 30 ℃ for 30min to finally obtain the interface adhesive for combined charging of the solid propellant.
The main steps of the interface bonding of the solid propellant combined charge are as follows: (1) Casting the low-combustion-rate propellant slurry into a required shape, curing at 50-70 ℃ for 96 hours, and turning into a required shape for later use; (2) Casting the medium-combustion-rate propellant slurry into a required shape, curing at 50-70 ℃ for 96 hours, and turning into a required shape for later use; (3) Casting the high-combustion-speed propellant slurry into a required shape, curing at 50-70 ℃ for 96 hours, and turning into a required shape for later use; (4) Uniformly smearing a certain amount of interface adhesive for the combined solid propellant charge between interfaces of the low-combustion-rate propellant and the combined medium-combustion-rate propellant charge, and standing for 24 hours in a vacuum oven at 60 ℃ to prepare a two-stage integrated combined solid propellant charge consisting of the low-combustion-rate propellant and the medium-combustion-rate propellant; (5) The two-stage integrated solid propellant composite charge has formed a firm bond. And uniformly smearing a certain amount of interface adhesive for the solid propellant combined charge between interfaces of the medium-combustion-rate propellant and the high-combustion-rate propellant combined charge, and standing for 24 hours in a vacuum oven at 60 ℃ to prepare the three-stage integrated solid propellant combined charge consisting of the low-combustion-rate propellant, the medium-combustion-rate propellant and the high-combustion-rate propellant.
The mass of the interfacial adhesive is M (g) =0.24×s, s is the area of the bonding surface, and the unit is cm 2 ；
The required shape is cut into the required shape by grinding the propellant after solidification (figure 4).
Example 3.1:
the following detailed description of the preferred embodiments of the invention is provided to enable those skilled in the art to more readily understand the advantages and features of the invention and to make a clear and concise definition of the scope of the invention.
The formula and the preparation steps of the solid propellant combined charge interface adhesive are as follows: the adhesive comprises the following components in percentage by mass: 72.0% of a hydroxypropyl emulsion of type HPA-1004, 24.5% of an aliphatic polyisocyanate of type N3390, 3.0% of a polyurethane water scavenger of type PG-101, 0.5% of a polyurethane defoamer of type DT-69. The preparation steps of the adhesive are as follows: (1) pretreatment of raw materials. Taking out the hydroxypropyl emulsion with the model HPA-1004 and the formula mass fraction of 72.0%, adding the polyurethane water scavenger with the model PG-101 and the formula mass fraction of 3.0%, uniformly mixing under the stirring of a stirring paddle of 800r/min, and placing in a vacuum oven at 60 ℃ for 4 hours to realize the dehydration of the hydroxypropyl emulsion; (2) obtaining an adhesive. Pouring the dehydrated hydroxypropyl emulsion with the model of HPA-1004 and the aliphatic polyisocyanate with the model of N3390 into the same container, adding 0.5% of polyurethane defoamer with the model of DT-69, uniformly mixing under the stirring of a stirring paddle with the speed of 1000r/min, and then placing in a vacuum oven with the temperature of 30 ℃ for 30min to finally obtain the interface adhesive for combined charging of the solid propellant.
The main steps of the interface bonding of the solid propellant combined charge are as follows: (1) Casting the low-combustion-rate propellant slurry into a required shape, curing at 50-70 ℃ for 96 hours, and turning into a required shape for later use; (2) Casting the medium-combustion-rate propellant slurry into a required shape, curing at 50-70 ℃ for 96 hours, and turning into a required shape for later use; (3) Casting the high-combustion-speed propellant slurry into a required shape, curing at 50-70 ℃ for 96 hours, and turning into a required shape for later use; (4) Uniformly smearing a certain amount of interface adhesive for the combined solid propellant charge between interfaces of the low-combustion-rate propellant and the combined medium-combustion-rate propellant charge, and standing for 24 hours in a vacuum oven at 60 ℃ to prepare a two-stage integrated combined solid propellant charge consisting of the low-combustion-rate propellant and the medium-combustion-rate propellant; (5) The two-stage integrated solid propellant composite charge has formed a firm bond. And uniformly smearing a certain amount of interface adhesive for the solid propellant combined charge between interfaces of the medium-combustion-rate propellant and the high-combustion-rate propellant combined charge, and standing for 24 hours in a vacuum oven at 60 ℃ to prepare the three-stage integrated solid propellant combined charge consisting of the low-combustion-rate propellant, the medium-combustion-rate propellant and the high-combustion-rate propellant.
The mass of the interfacial adhesive is M (g) =0.12×s, s is the area of the bonding surface, and the unit is cm 2 ；
The required shape is cut into the required shape by grinding the propellant after solidification (figure 4).
Example 3.2:
the following detailed description of the preferred embodiments of the invention is provided to enable those skilled in the art to more readily understand the advantages and features of the invention and to make a clear and concise definition of the scope of the invention.
Unlike example 3.1, the following is: the mass of the interfacial adhesive is M (g) =0.36×s, s is the area of the bonding surface, and the unit is cm 2 ；
Turning into required drug forms, and grinding by a grinding wheel after the propellant is solidified (figure 4);
the amount of binder used in example 3.2 was large and could affect subsequent combustion of the propellant at the adhesive junction after ignition, and the second stage propellant did not burn after combustion of the first stage propellant was completed.
Example 3.3:
the following detailed description of the preferred embodiments of the invention is provided to enable those skilled in the art to more readily understand the advantages and features of the invention and to make a clear and concise definition of the scope of the invention.
Unlike example 3.1, the following is: the mass of the interfacial adhesive is M (g) =0.24×s, s is the area of the bonding surface, and the unit is cm 2 ；
The required shape is turned into the annular groove after the propellant is solidified (figure 2).
Example 3.4:
the following detailed description of the preferred embodiments of the invention is provided to enable those skilled in the art to more readily understand the advantages and features of the invention and to make a clear and concise definition of the scope of the invention.
Unlike example 3.1, the following is: the mass of the interfacial adhesive is M (g) =0.24×s, s is the area of the bonding surface, and the unit is cm 2 ；
The required shape is cut into the required shape by coarse sand paper grinding after the propellant is solidified (figure 3).
Example 3.5:
the following detailed description of the preferred embodiments of the invention is provided to enable those skilled in the art to more readily understand the advantages and features of the invention and to make a clear and concise definition of the scope of the invention.
Unlike example 3.1, the following is: the mass of the interfacial adhesive is M (g) =0.24×s, s is the area of the bonding surface, and the unit is cm 2 ；
The required shape is cut into the required shape by grinding the propellant after solidification (figure 4).
The advantage of example 3.5 is that the three-stage propellant obtained has a clean interface, a strong bond, a high interface strength, and no effect on the subsequent combustion of the bonded interface (table 1).
Example 4:
casting the low-combustion-rate propellant slurry into a required shape, solidifying for 24 hours, and turning a pseudo-bonding interface of the low-combustion-rate propellant into a required shape for later use; (2) Placing the turned low-combustion-rate propellant under a casting tool for fixing, smearing a binder between the to-be-bonded interfaces, casting the medium-combustion-rate propellant slurry at the upper end of the low-combustion-rate propellant, solidifying for 24 hours, and turning the to-be-bonded interfaces of the medium-combustion-rate propellant into required drug forms for later use; (3) And placing the turned medium-speed propellant under a casting tool for fixing, smearing a binder between the to-be-bonded interfaces, casting high-speed propellant slurry at the upper end of the medium-speed propellant, and curing for 72 hours to prepare the integrated solid propellant combined charge.
The mass of the interfacial adhesive used was M (g) =0.24×s, s being the area of the bonding surface in cm 2 。
Performance test: referring to GJB770B-2005 method 413.1, the mechanical properties of the propellant combination grain interface were tested with an INSTRON 4505 materials tester (USA) with a sample size of 10mm 120mm, and the combination grain sample was prepared with the two-stage grain interface in the middle of the tensile sheet (FIG. 5), at a tensile rate of 100mm/min, and at a temperature of 20 ℃.
TABLE 1 interfacial mechanical Properties of samples (20 ℃ C.)
| Sample of | The tensile strength of the steel sheet is higher than the tensile strength of the steel sheet,MPa |
| Prior Art | 3.68 |
| Example 2 | 3.81 |
| Example 3.1 | 4.13 |
| Example 3.2 | 7.30 |
| Example 3.3 | 4.09 |
| Example 3.4 | 6.17 |
| Example 3.5 | 7.27 |
| Example 4 | 6.57 |
In table 1, the higher the tensile strength, the stronger the adhesive bond. In connection with examples 2 and 3.5, it is illustrated that the adhesive formulation is intended to be the formulation described in the specification of the present invention; in combination with examples 3.3, 3.4 and 3.5, it is illustrated that the bonding surface needs to be polished by a grinding wheel; in examples 3.1, 3.2 and 3.5, the tensile strength of example 3.2 was the greatest, but the increase in tensile strength was not significant compared to example 3.5, and excessive binder could adversely affect the subsequent combustion of the bonding interface. Thus, the amount of adhesive used is M (g) =0.24* S, S is the area of the bonding surface, in cm 2 。
The preferred embodiments have been discussed in detail above in connection with the drawings and are not intended to limit the invention. The above-described specific technical features may be combined in any suitable form without contradiction, and the present invention is not described in detail. Any person skilled in the art adopts simple modification or amendment means such as arbitrary combination or equivalent replacement of technical schemes without departing from the scope of the technical schemes, and does not affect the essence of the technical schemes, and the technical schemes still belong to the protection scope of the technical schemes represented by the embodiments of the invention.
Claims (9)
1. An interface binder for a solid propellant combined charge is characterized by comprising hydroxypropyl emulsion, aliphatic polyisocyanate, polyurethane water-removing agent and polyurethane defoamer;
the weight percentage of the hydroxypropyl emulsion is 72.0 percent, the aliphatic polyisocyanate is 24.5 percent, the polyurethane water scavenger is 3.0 percent, and the polyurethane defoamer is 0.5 percent.
2. The interface binder for a solid propellant composite charge of claim 1, wherein the steps of preparing are as follows:
(1) Uniformly mixing the hydroxypropyl emulsion and the polyurethane dehydrator according to the formula amount, and then carrying out vacuum standing at 60 ℃ to dehydrate the hydroxypropyl emulsion;
(2) Uniformly mixing the dehydrated hydroxypropyl emulsion, aliphatic polyisocyanate and polyurethane defoamer, and then standing in vacuum at 30 ℃ to obtain the polyurethane foam.
3. The interface binder for a solid propellant composite charge of claim 2 wherein the rest time of (1) is 4 hours;
the standing time in the step (2) is 30min.
4. A process for preparing a solid propellant composite charge, wherein the solid propellant composite charge is formed by stacking a plurality of stages of grains, and adjacent grains are bonded by the interfacial adhesive of the solid propellant composite charge according to any one of claims 1 to 3;
the amount of the interfacial adhesive for the solid propellant combined charge is calculated by the application area, the mass of the adhesive is M (g) = (0.12-0.24) S, S is the area of the bonding surface, and the unit is cm 2 。
5. The process for preparing a solid propellant composite charge of claim 4 wherein said bonding surfaces are further treated by a method comprising:
grinding wheel grinding, turning annular grooves and grinding paper grinding.
6. The process for preparing a solid propellant composite charge according to claim 4, wherein the composite charge comprises a low-combustion-rate propellant charge, a medium-combustion-rate propellant charge and a high-combustion propellant charge which are stacked in sequence along the axial direction, and comprises the following specific steps: (1) The low-combustion-rate propellant slurry is turned into a required drug form for standby after being cast and completely solidified; (2) The medium-combustion-rate propellant slurry is turned into a required drug form for standby after being cast and completely solidified; (3) The high-combustion-speed propellant slurry is turned into a required drug form for standby after being cast and completely solidified; (4) And uniformly coating the interface adhesive of the solid propellant combined charge between interfaces, and standing in vacuum to form the integrated solid propellant combined charge.
7. The process for preparing a solid propellant composite charge according to claim 6, wherein the low burn rate propellant charge is cured at a temperature of 50 to 70 ℃ for 96 hours;
the medium-combustion-rate propellant charge is solidified for 96 hours at the temperature of 50-70 ℃;
uniformly coating the interface adhesive of the solid propellant combined charge between the charge interfaces of the low-combustion-rate propellant charge and the medium-combustion-rate propellant charge, and standing for 24 hours at 60 ℃ in vacuum to obtain a two-stage integrated solid propellant combined charge;
curing the high-combustion-speed propellant for 96 hours at the temperature of 50-70 ℃;
and uniformly coating the interface adhesive of the solid propellant combined charge on the interface between the two-stage integrated solid propellant combined charge and the grain of the high-combustion-speed propellant charge, and standing at 60 ℃ in vacuum for 24 hours to obtain the solid propellant combined charge.
8. The process for preparing a solid propellant combination charge of claim 6 wherein the low, medium and high burn propellant charges are provided in a bottom-to-top sequence.
9. The charge preparation process of a solid propellant combined charge according to claim 6, characterized in that it comprises in particular:
(1) Solidifying the low-combustion-rate propellant slurry after casting to obtain low-combustion-rate propellant powder;
(2) The low-combustion-rate propellant charge is fixed below the casting tool, the interface binder of the solid propellant combined charge is smeared on the top end surface of the low-combustion-rate propellant charge, and the medium-combustion-rate propellant slurry is cast on the low-combustion-rate propellant charge and solidified for 24 hours to obtain the medium-combustion-rate propellant charge;
(3) The interface binder of the solid propellant combined charge is smeared on the top end surface of the medium-combustion-speed propellant charge, and the high-combustion-speed propellant slurry is cast on the medium-combustion-speed propellant charge, and is solidified for 72 hours to obtain the integrated solid propellant combined charge.
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| DE102008001384A1 (en) * | 2008-04-25 | 2009-10-29 | Wacker Chemie Ag | Silicone-containing polyisocyanurate foam |
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| US4165247A (en) * | 1966-02-09 | 1979-08-21 | The United States Of America As Represented By The Secretary Of The Navy | Polyurethane solid propellant binder |
| US9181140B1 (en) * | 1992-09-16 | 2015-11-10 | Orbital Atk, Inc. | Solid propellant bonding agents and methods for their use |
| CN106366630A (en) * | 2016-08-31 | 2017-02-01 | 上海新力动力设备研究所 | Liner material for improving interfacial bonding of HTPB propellant and preparation method thereof |
| CN109233485A (en) * | 2017-04-27 | 2019-01-18 | 宁夏和而不同创意有限公司 | A kind of water-soluble colorful coating and preparation method thereof |
| CN107311826B (en) * | 2017-07-24 | 2019-04-30 | 湖北航天化学技术研究所 | Improve the combination function auxiliary agent of solid propellant mechanical property and the solid propellant comprising the combination function auxiliary agent |
| CN109232848B (en) * | 2018-03-22 | 2021-04-13 | 湖北航天化学技术研究所 | DDI lining layer for solid rocket engine medicine loading and application method thereof |
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| DE3641788A1 (en) * | 1986-12-06 | 1988-06-09 | Fraunhofer Ges Forschung | Process for improving the burning behaviour of solid propellants, and solid propellant |
| DE102008001384A1 (en) * | 2008-04-25 | 2009-10-29 | Wacker Chemie Ag | Silicone-containing polyisocyanurate foam |
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