CN115784813A - Mixing method and mixing system of composite solid propellant - Google Patents
Mixing method and mixing system of composite solid propellant Download PDFInfo
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- CN115784813A CN115784813A CN202211493182.1A CN202211493182A CN115784813A CN 115784813 A CN115784813 A CN 115784813A CN 202211493182 A CN202211493182 A CN 202211493182A CN 115784813 A CN115784813 A CN 115784813A
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- 238000002156 mixing Methods 0.000 title claims abstract description 145
- 239000004449 solid propellant Substances 0.000 title claims abstract description 92
- 239000002131 composite material Substances 0.000 title claims abstract description 83
- 238000000034 method Methods 0.000 title claims abstract description 40
- 239000000843 powder Substances 0.000 claims abstract description 130
- 239000000853 adhesive Substances 0.000 claims abstract description 49
- 229910052751 metal Inorganic materials 0.000 claims abstract description 49
- 239000002184 metal Substances 0.000 claims abstract description 49
- 230000001070 adhesive effect Effects 0.000 claims abstract description 47
- 239000007787 solid Substances 0.000 claims abstract description 43
- 239000000945 filler Substances 0.000 claims abstract description 37
- 239000007800 oxidant agent Substances 0.000 claims abstract description 33
- 238000005507 spraying Methods 0.000 claims abstract description 33
- 239000000446 fuel Substances 0.000 claims abstract description 30
- 230000001590 oxidative effect Effects 0.000 claims abstract description 28
- 239000012752 auxiliary agent Substances 0.000 claims abstract description 8
- 150000001875 compounds Chemical class 0.000 claims abstract description 8
- 239000000203 mixture Substances 0.000 claims abstract description 7
- 238000003860 storage Methods 0.000 claims description 40
- 238000005266 casting Methods 0.000 claims description 23
- XTFIVUDBNACUBN-UHFFFAOYSA-N 1,3,5-trinitro-1,3,5-triazinane Chemical compound [O-][N+](=O)N1CN([N+]([O-])=O)CN([N+]([O-])=O)C1 XTFIVUDBNACUBN-UHFFFAOYSA-N 0.000 claims description 9
- 239000002245 particle Substances 0.000 claims description 9
- 239000000028 HMX Substances 0.000 claims description 7
- UZGLIIJVICEWHF-UHFFFAOYSA-N octogen Chemical compound [O-][N+](=O)N1CN([N+]([O-])=O)CN([N+]([O-])=O)CN([N+]([O-])=O)C1 UZGLIIJVICEWHF-UHFFFAOYSA-N 0.000 claims description 7
- 239000011230 binding agent Substances 0.000 claims description 6
- 238000002485 combustion reaction Methods 0.000 claims description 6
- 239000007921 spray Substances 0.000 claims description 5
- 239000002671 adjuvant Substances 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 claims description 3
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- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 239000002002 slurry Substances 0.000 description 17
- 238000011049 filling Methods 0.000 description 10
- 238000009826 distribution Methods 0.000 description 7
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 6
- 238000010586 diagram Methods 0.000 description 6
- 229920002121 Hydroxyl-terminated polybutadiene Polymers 0.000 description 4
- 238000001723 curing Methods 0.000 description 4
- 238000002360 preparation method Methods 0.000 description 4
- 239000000470 constituent Substances 0.000 description 2
- 239000006185 dispersion Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000227 grinding Methods 0.000 description 2
- 238000010907 mechanical stirring Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 239000005062 Polybutadiene Substances 0.000 description 1
- 238000005054 agglomeration Methods 0.000 description 1
- 230000002776 aggregation Effects 0.000 description 1
- SNAAJJQQZSMGQD-UHFFFAOYSA-N aluminum magnesium Chemical compound [Mg].[Al] SNAAJJQQZSMGQD-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 description 1
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- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- AXZAYXJCENRGIM-UHFFFAOYSA-J dipotassium;tetrabromoplatinum(2-) Chemical compound [K+].[K+].[Br-].[Br-].[Br-].[Br-].[Pt+2] AXZAYXJCENRGIM-UHFFFAOYSA-J 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
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- 238000005516 engineering process Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000013007 heat curing Methods 0.000 description 1
- 150000004678 hydrides Chemical class 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
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- 229920002857 polybutadiene Polymers 0.000 description 1
- 229920001021 polysulfide Polymers 0.000 description 1
- 239000005077 polysulfide Substances 0.000 description 1
- 150000008117 polysulfides Polymers 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 229910001487 potassium perchlorate Inorganic materials 0.000 description 1
- 239000005060 rubber Substances 0.000 description 1
- 238000006748 scratching Methods 0.000 description 1
- 230000002393 scratching effect Effects 0.000 description 1
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Abstract
The invention relates to the field of composite solid propellant manufacturing, and discloses a composite solid propellant mixing method and a composite solid propellant mixing system, wherein uniform mixing of solid filler powder in a micro-scale space is realized in a low-sensitivity and mechanical stirring-free mode by determining the layer thickness ratio of an oxidant and a metal fuel layer, accumulating primary powder, accumulating secondary powder on the first layer of powder, and mixing the primary powder and the second layer of powder at intervals; the small-component solid filler powder and the auxiliary agent are mixed and added into the adhesive for premixing according to the proportion, the small-component solid filler powder is high in mixing uniformity, and the small-component solid filler powder and the adhesive are mixed uniformly in a mode of firstly mixing and then spraying; through continuous mixing, realize continuous mixing through continuously providing solid filler powder, solve traditional compound solid propellant mixing process and mix the limited problem of capacity.
Description
Technical Field
The invention relates to the field of manufacturing of composite solid propellants, in particular to a mixing method and a mixing system of a composite solid propellant.
Background
The preparation method comprises the following steps of weighing, mixing, pouring, curing, demolding and shaping, and is a mainstream composite solid propellant grain preparation process. With the increasing performance requirements of solid rocket engines, the traditional hybrid process has the following limitations: (1) limited loading capacity of mixing equipment: the mass of slurry required by large-size composite solid propellant grains used by an ultra-long-range and high-performance solid rocket engine is far beyond the bearing capacity of the existing mixing equipment, and the traditional mixing equipment has great difficulty in manufacturing the large-size composite solid propellant grains; (2) the mixing process is more dangerous: the traditional mixing process realizes the uniform dispersion of solid filler powder with high solid content by external force action such as mechanical stirring and the like, and the solid filler powder can become a stimulus source for initiating the chemical reaction between an oxidant and a metal fuel, so that the hidden danger of combustion or explosion exists. (3) the mixing effect is difficult to guarantee: the traditional mixing equipment cannot directly observe, control and judge the powder distribution condition and state of each component of the solid filler during stirring. The solid filler contains multiple components, the powder content of each component is different, the content of the oxidant and the metal fuel powder is higher, and the content of the hexogen, the octogen and other components is lower, so that the uniform dispersion in the mixing process has quite high difficulty; the particle size distribution of the solid filler powder is wide, wherein powder clusters are generated by agglomeration of powder with small particle size, and uneven mixing is directly caused; the grains cast by the composite solid propellant slurry which is not uniformly mixed can reduce the energy management capability and the combustion performance stability of the propellant.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention aims to provide a mixing method and a mixing system of a composite solid propellant, so as to solve the technical problems of limited mixing capacity, unsafe mixing process and uneven mixing of small-component solid filler powder in the traditional mixing process of the composite solid propellant.
The invention is realized by the following technical scheme:
a method of continuously mixing a composite solid propellant, comprising the steps of:
step 3, spraying the premixed adhesive on the mixed micro-scale powder layer to bond the powder particles into a whole to obtain the composite solid propellant;
and 4, repeatedly executing the steps 1 to 3, and sequentially transporting the obtained composite solid propellant for casting to finish the continuous mixing work of the composite solid propellant.
Preferably, in step 1, the ratio of the stack thickness of each layer of the oxidizer powder to the metal fuel powder is determined according to the combustion speed and specific impulse required during the operation of the solid rocket engine.
Preferably, in step 1, the thickness of the first layer of powder and the second layer of powder is in the range of 50 μm to 1mm.
Preferably, in the step 2, the solid filler powder with small components and the auxiliary agent are mixed, wherein the mixing mass ratio is 5-20: 1.
preferably, in step 2, the minor component solid filler powders include, but are not limited to, hexogen RDX and octogen HMX; adjuvants include, but are not limited to, curing agents, plasticizers, and burn performance modifiers.
Preferably, in step 2, the spraying manner of the premixed binder to the mixed micro-scale powder layer comprises an overall reciprocating filling spraying or a block distribution filling spraying.
A continuous mixing system of composite solid propellant is used for realizing the continuous mixing method of the composite solid propellant, and comprises a plurality of compartments, a parallel conveying device, a casting chamber and a casting mold; the multiple compartments are connected through a parallel conveying device, wherein a continuous mixing device is arranged in each compartment, the output end of the continuous mixing device is connected with the input end of a vacuum conveying device, the output end of the vacuum conveying device is connected with the input end of the parallel conveying device, and the output end of the parallel conveying device is aligned to the casting mold through a casting chamber.
Preferably, the output end of the parallel conveying device is provided with a conveying pump.
Preferably, the continuous mixing device comprises an adhesive storage bin, a metal fuel storage bin, a composite solid propellant mixing bin, an oxidant storage bin, a metal powder feeding device, a small group component storage bin, an adhesive spraying device and a strickling device; the output end of the adhesive storage bin is connected with an adhesive spraying device, and the output end of the metal fuel storage bin is connected with a metal powder feeding device; the output ends of the adhesive spraying device, the metal powder feeding device and the oxidant storage bin are aligned to the composite solid propellant mixing bin, the vacuum conveying device is connected with the composite solid propellant mixing bin, the adhesive spraying device is provided with a group distribution storage bin, and the output end of the group distribution storage bin is provided with an ultrasonic vibration device.
Furthermore, the continuous mixing device also comprises a cross beam, the metal powder feeding device and the adhesive spraying device are assembled on the cross beam, the composite solid propellant mixing bin is arranged below the cross beam, and the output ends of the metal powder feeding device and the adhesive spraying device are aligned to the composite solid propellant mixing bin.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides a mixing method of a composite solid propellant, which comprises the steps of determining the layer thickness ratio of an oxidant and a metal fuel layer, accumulating first-time powder, accumulating second-time powder on the first-layer powder, and mixing the first-time powder and the second-layer powder in a clearance mode, so that the uniform mixing of solid filler powder in a micro-scale space is realized in a low-sensitivity and mechanical-stirring-free mode; the small-component solid filler powder and the auxiliary agent are mixed and added into the adhesive according to the proportion for premixing, the mixing uniformity of the small-component solid filler powder is high, and the small-component solid filler powder and the adhesive are mixed uniformly in a mode of firstly mixing and then spraying; through continuous mixing, realize continuous mixing through continuously providing solid filler powder, solve traditional compound solid propellant mixing process and mix the limited problem of capacity.
Furthermore, the spraying mode of the premixed adhesive to the mixed micro-scale powder layer comprises overall reciprocating filling spraying or block distribution filling spraying, and after small-component solid fillers and the adhesive are effectively premixed by adopting the block distribution filling spraying, the small-component solid fillers and the adhesive are separately sprayed in each block, so that the small-component solid fillers and the adhesive can be sprayed in each block.
The utility model provides a compound solid propellant's continuous mixing system, mix through the distributing type, set up a plurality of continuous mixing arrangement and distribute and carry out the mixing operation simultaneously in different compartments, and export them parallelly connected back together, it is big to solve the interior dose of single space of traditional compound solid propellant mixing process, the security is lower and the limited problem of mixing capacity, mutual noninterference when guaranteeing to break down or dangerous between the continuous mixing equipment simultaneously, promote mixed security, can pass through the parallelly connected mode of a plurality of equipment again, realize the preparation of large-traffic solid propellant medicine thick liquid.
Drawings
FIG. 1 is a flow diagram of a continuous mixing process for a composite solid propellant in accordance with the present invention;
FIG. 2 is a block diagram of a continuous mixing system for the composite solid propellant of the present invention;
FIG. 3 is a schematic structural diagram of a powder feeding-powder laying type composite solid propellant continuous mixing device according to the present invention;
FIG. 4 is a schematic structural diagram of a continuous mixing device for upward powder feeding type composite solid propellant in the present invention;
FIG. 5 is a schematic structural diagram of a powder-laying type composite solid propellant continuous mixing device according to the present invention;
FIG. 6 is a top view of FIG. 5;
FIG. 7 is a block allocation filling diagram according to the present invention.
In the figure: 1-a compartment; 2-parallel conveying means; 3-a delivery pump; 4-a casting chamber; 5-casting the mould; 6-a continuous mixing device; 7-vacuum conveying device; 8-adhesive storage bin; 9-a metal fuel storage bin; 10-composite solid propellant mixing bin; 11-an oxidant storage bin; 12-a binder delivery tube; 13-a metal powder delivery tube; 14-a cross beam; 15-a metal powder feeding device; 16-small group storage bins; 17-ultrasonic vibration means; 18-a milling roller; 19-compacting rollers; 20-adhesive spraying means; 21-a screeding device; 22-push rod.
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. Moreover, 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:
the invention aims to provide a mixing method and a mixing system of a composite solid propellant, which aim to solve the technical problems of limited mixing capacity, unsafe mixing process and uneven mixing of small-component solid filler powder in the traditional mixing process of the composite solid propellant.
Specifically, as shown in fig. 1, the continuous mixing method of the composite solid propellant comprises the following steps:
specifically, the ratio of the stacking thickness of each layer of the oxidizer powder to the metal fuel powder is determined according to the combustion speed and specific impulse required in the working process of the solid rocket engine.
Specifically, the thickness of the first layer of powder and the second layer of powder ranges from 50 μm to 1mm.
Specifically, solid filler powder with small components and an auxiliary agent are mixed, wherein the mixing mass ratio is 5-20.
Specifically, the oxidant includes, but is not limited to, one or more of ammonium perchlorate, potassium perchlorate, and the like.
Specifically, the metal fuel includes, but is not limited to, one or more of aluminum powder, boron powder, magnesium powder, beryllium powder and their corresponding hydride and aluminum-magnesium powder.
specifically, minor component solid filler powders include, but are not limited to, hexogen RDX and octogen HMX; adjuvants include, but are not limited to, curing agents, plasticizers, and burn performance modifiers.
Specifically, the adhesive includes, but is not limited to, one or more of polysulfide rubber, polyurethane, hydroxyl-terminated polybutadiene, carboxyl-terminated polybutadiene and the like
Specifically, the spraying of the premixed binder onto the mixed micro-scale powder layer includes a whole reciprocating filling spray or a block dispensing filling spray, wherein the block dispensing filling spray is shown in fig. 7.
Step 3, spraying the premixed adhesive on the mixed micro-scale powder layer to bond the powder particles into a whole to obtain the composite solid propellant;
and 4, repeatedly executing the step 1 to the step 3, and sequentially transporting the obtained composite solid propellant for casting to finish the continuous mixing work of the composite solid propellant.
According to the figure 2, the invention also provides a continuous mixing system of the composite solid propellant, which is used for realizing the continuous mixing method of the composite solid propellant, and comprises a plurality of compartments 1, parallel conveying devices 2, a casting chamber 4 and a casting mould 5; the compartments 1 are connected by means of a parallel conveyor 2, wherein a continuous mixing device 6 is arranged in each compartment 1, the output of the continuous mixing device 6 is connected to the input of a vacuum conveyor 7, the output of the vacuum conveyor 7 is connected to the input of the parallel conveyor 2, and the output of the parallel conveyor 2 is directed onto a casting mould 5 via a casting chamber 4.
Specifically, the output end of the parallel conveying device 2 is provided with a conveying pump 3.
As shown in fig. 3, the continuous mixing device 6 includes an adhesive storage bin 8, a metal fuel storage bin 9, a composite solid propellant mixing bin 10, an oxidizer storage bin 11, a metal powder feeding device 15, a small component storage bin 16, an adhesive spraying device 20 and a strickling device 21; the output end of the adhesive storage bin 8 is connected with an adhesive spraying device 20, and the output end of the metal fuel storage bin 9 is connected with a metal powder feeding device 15; the output ends of the adhesive spraying device 20, the metal powder feeding device 15 and the oxidant storage bin 11 are aligned to the composite solid propellant mixing bin 10, the vacuum conveying device 7 is connected with the composite solid propellant mixing bin 10, the small component storage bin 16 is arranged on the adhesive spraying device 20, and the ultrasonic vibration device 17 is arranged at the output end of the small component storage bin 16.
Wherein, continuous mixing arrangement 6 still includes crossbeam 14, and metal powder send powder device 15 and adhesive sprinkler 20 to assemble on crossbeam 14, and compound solid propellant mixing bin 10 sets up in the below of crossbeam 14, and the output of metal powder send powder device 15 and adhesive sprinkler 20 aligns compound solid propellant mixing bin 10.
According to the illustration in fig. 3, the output end of the adhesive storage bin 8 is connected with the input end of the adhesive spraying device 20 through the adhesive conveying pipe 12, the output end of the minor constituent storage bin 16 is communicated with the input end of the adhesive spraying device 20, and the output end of the minor constituent storage bin 16 is provided with the ultrasonic vibration device 17;
the output end of the metal fuel storage bin 9 is connected with the input end of a metal powder feeding device 15 through a metal powder conveying pipe 13, and a powder grinding roller 18 and a compacting roller 19 are arranged at the output end of the metal powder feeding device 15; the grinding roller 18 and the compacting roller 19 are in contact with the composite solid propellant in the composite solid propellant mixing bin 10;
a push rod 22 is arranged in the oxidant storage bin 11, one end of the strickle device 21 is connected with the cross beam 14, and the other end of the strickle device is in contact with the oxidant powder in the oxidant storage bin 11 and is used for scratching the oxidant powder into the composite solid propellant mixing bin 10.
The continuous mixing device 6 can also adopt an upward powder feeding type composite solid propellant continuous mixing device, as shown in figure 4; a powder-laying type composite solid propellant continuous mixing device can also be adopted, as shown in fig. 5 and 6.
Examples
In this embodiment, each component of the composite solid propellant is mixed by a continuous mixing method of the composite solid propellant, and the specific flow is as follows:
(1) Adopting a powder-spreading type composite solid propellant slurry continuous mixing device, taking hydroxyl-terminated polybutadiene as an adhesive, taking ammonium perchlorate as an oxidant, taking aluminum powder as metal fuel, wherein the particle size of ammonium perchlorate powder is 75-150 mu m, and the particle size of aluminum powder is 30 mu m; 4 compartments were provided for continuous mixing at the same time.
(2) In this embodiment, the ratio of each component of the composite solid propellant is as follows: 10wt% of hydroxyl-terminated polybutadiene, 70wt% of ammonium perchlorate, 18wt% of aluminum powder and 2wt% of hexogen; firstly, premixing adhesive hydroxyl-terminated polybutadiene and small-component solid filler hexogen in a container for later use; and respectively filling the ammonium perchlorate powder, the aluminum powder and the premixed adhesive into corresponding storage bins to wait for feeding.
(3) The stacking thickness of the ammonium perchlorate powder is 500 mu m, the stacking thickness of the aluminum powder is 50 mu m, and after one layer of each is stacked, the adhesive is sprayed to bond the solid filler powder particles.
(4) The powder-spread type composite solid propellant slurry continuous mixing device in each compartment is stacked alternately through the steps to form 2 kilograms of composite solid propellant slurry.
(5) And (3) using a vacuum conveying device to connect the mixed composite solid propellant slurry in each compartment in parallel, conveying the slurry to a storage device of pouring equipment, and waiting for pouring.
(6) And casting the propellant slurry in the storage device into the engine shell casting mold under the environment of 0.02MPa of vacuum degree.
(7) During the casting process, the continuous mixing equipment in the four compartments is alternately matched to supply the casting equipment with the mixed composite solid propellant slurry.
(8) After the casting, the cast product is placed into an oven for heat curing, the oven is set at 60 ℃, and the curing time is 8 days.
(9) And taking out the prepared composite solid propellant, arranging equipment, closing each valve and cutting off the power.
The composite solid propellant prepared in the example was measured to obtain the relevant performance parameters of quality, mechanical properties, combustion performance, etc. as shown in table 1.
TABLE 1 quality and Properties of the composite solid propellant formation
The continuous mixing technology of the invention is that a plurality of composite solid propellant continuous mixing devices are utilized to uniformly mix the composite solid propellant slurry and then the composite solid propellant slurry is conveyed to a casting device after being connected in parallel by a material conveying device. The solid filler powder particles are uniformly distributed in a high-safety mode through a low-sensitivity powder mixing mode without mechanical stirring, then the solid filler powder is bonded through spraying an adhesive, and the uniformly mixed oxidant and metal fuel powder are bonded layer by layer for multiple times to obtain composite solid propellant slurry so as to realize the continuous mixing of the composite solid propellant. Then, a plurality of same continuous mixing devices are distributed in different compartments according to requirements to mix the slurry, and the outputs of the continuous mixing devices in different physical spaces which are mutually isolated are connected in parallel and then output together, so that the amount of the slurry mixed in each compartment is minimum, the requirement of large-flow continuous mixing can be met, and the high-safety continuous mixing preparation of the composite solid propellant slurry is realized
In summary, the present invention provides a mixing method and a mixing system for a composite solid propellant, which continuously provide solid filler powder to achieve continuous mixing; the uniform mixing of the solid filler powder in the micro-scale space is realized in a low-sensitivity and mechanical-stirring-free mode; uniformly mixing the small-component solid filler powder and the adhesive in a mode of mixing and spraying; the continuous mixing devices are distributed in different compartments to perform distributed mixing, so that the problems of low safety and limited mixing capacity in the mixing process are solved, and high-safety continuous mixing of the composite solid propellant slurry is realized at the feeding end. The method can realize continuous mixing of large-batch composite solid propellant slurry and can also ensure the safety of the mixing process and the mixing uniformity of the solid filler powder.
Finally, it should be noted that: although the present invention has been described in detail with reference to the above embodiments, it should be understood by those skilled in the art that: modifications and equivalents may be made to the embodiments of the invention without departing from the spirit and scope of the invention, which is to be covered by the claims.
Claims (10)
1. A method for continuously mixing a composite solid propellant, comprising the steps of:
step 1, determining the layer thickness ratio of an oxidant and a metal fuel layer, stacking a first layer of oxidant powder or metal fuel powder, stacking a second layer of metal fuel powder or oxidant powder on the stacked layer of oxidant powder or metal fuel powder, and mixing the first powder and the second powder in a gap to form a mixed micro-scale powder layer;
step 2, mixing the solid filler powder of the minor components and the auxiliary agent, and adding the mixture into the adhesive according to the proportion for premixing;
step 3, spraying the premixed adhesive on the mixed micro-scale powder layer to bond the powder particles into a whole to obtain the composite solid propellant;
and 4, repeatedly executing the step 1 to the step 3, and sequentially transporting the obtained composite solid propellant for casting to finish the continuous mixing work of the composite solid propellant.
2. The method for continuously mixing a composite solid propellant according to claim 1, wherein in step 1, the ratio of the stacking thickness of each layer of the oxidizer powder to the metallic fuel powder is determined according to the combustion speed and specific impulse required during the operation of the solid rocket engine.
3. The continuous mixing process for a composite solid propellant according to claim 1, wherein the thickness of the first and second layers of powder in step 1 is in the range of 50 μm to 1mm.
4. The continuous mixing method of the composite solid propellant as claimed in claim 1, wherein in the step 2, the solid filler powder with small components and the auxiliary agent are mixed, wherein the mixing mass ratio is 5-20: 1.
5. the method for continuously mixing a composite solid propellant as claimed in claim 1, wherein in step 2, the minor component solid filler powder includes but is not limited to hexogen RDX and octogen HMX; adjuvants include, but are not limited to, curing agents, plasticizers, and burn performance modifiers.
6. The method of claim 1, wherein the step 2 of spraying the premixed binder onto the mixed micro-scale powder layer comprises a bulk reciprocating fill spray or a block dispense fill spray.
7. Continuous mixing system of composite solid propellant for carrying out the continuous mixing method of composite solid propellant according to any one of claims 1 to 6, characterized by comprising several compartments (1), parallel delivery means (2), a casting chamber (4) and a casting mould (5); the plurality of compartments (1) are connected through the parallel conveying device (2), wherein a continuous mixing device (6) is arranged in each compartment (1), the output end of the continuous mixing device (6) is connected with the input end of the vacuum conveying device (7), the output end of the vacuum conveying device (7) is connected with the input end of the parallel conveying device (2), and the output end of the parallel conveying device (2) is aligned to the casting mold (5) through the casting chamber (4).
8. Continuous mixing system for composite solid propellants according to claim 7, characterized in that the output end of the parallel conveying device (2) is provided with a conveying pump (3).
9. The continuous mixing system of composite solid propellant according to claim 7, characterized in that the continuous mixing device (6) comprises a binder storage bin (8), a metal fuel storage bin (9), a composite solid propellant mixing bin (10), an oxidizer storage bin (11), a metal powder feeding device (15), a small group component storage bin (16), a binder spraying device (20) and a strickling device (21); the output end of the adhesive storage bin (8) is connected with an adhesive spraying device (20), and the output end of the metal fuel storage bin (9) is connected with a metal powder feeding device (15); the output of adhesive sprinkler (20), metal powder send powder device (15) and oxidant storage silo (11) to aim at compound solid propellant mixing bin (10), vacuum conveyor (7) are connected with compound solid propellant mixing bin (10), be equipped with subgroup storage silo (16) on adhesive sprinkler (20), be equipped with ultrasonic vibration device (17) on the output of subgroup storage silo (16).
10. Continuous mixing system for composite solid propellants according to claim 9, characterized in that the continuous mixing device (6) further comprises a cross beam (14), the metal powder feeding device (15) and the adhesive spraying device (20) are assembled on the cross beam (14), the composite solid propellant mixing bin (10) is arranged below the cross beam (14), and the output ends of the metal powder feeding device (15) and the adhesive spraying device (20) are aligned with the composite solid propellant mixing bin (10).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211493182.1A CN115784813B (en) | 2022-11-25 | 2022-11-25 | Mixing method and mixing system for composite solid propellant |
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| CN202211493182.1A CN115784813B (en) | 2022-11-25 | 2022-11-25 | Mixing method and mixing system for composite solid propellant |
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| CN115784813A true CN115784813A (en) | 2023-03-14 |
| CN115784813B CN115784813B (en) | 2024-04-16 |
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| CN202211493182.1A Active CN115784813B (en) | 2022-11-25 | 2022-11-25 | Mixing method and mixing system for composite solid propellant |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108000870A (en) * | 2017-12-01 | 2018-05-08 | 西安交通大学 | A kind of 3DP technological formings system and its operating method |
| CN109438149A (en) * | 2018-12-05 | 2019-03-08 | 湖北航天化学技术研究所 | A kind of thermosetting property composite solidpropellant and preparation method thereof |
| CN109759579A (en) * | 2019-02-19 | 2019-05-17 | 南通理工学院 | Three-dimensional printing rapid forming method of metal matrix composite powder |
| JP7026281B1 (en) * | 2021-06-10 | 2022-02-25 | 湖北航天化学技術研究所 | High-density specific impulse propellant and its preparation method |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108000870A (en) * | 2017-12-01 | 2018-05-08 | 西安交通大学 | A kind of 3DP technological formings system and its operating method |
| CN109438149A (en) * | 2018-12-05 | 2019-03-08 | 湖北航天化学技术研究所 | A kind of thermosetting property composite solidpropellant and preparation method thereof |
| CN109759579A (en) * | 2019-02-19 | 2019-05-17 | 南通理工学院 | Three-dimensional printing rapid forming method of metal matrix composite powder |
| JP7026281B1 (en) * | 2021-06-10 | 2022-02-25 | 湖北航天化学技術研究所 | High-density specific impulse propellant and its preparation method |
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