CN109400424B - Method for coating tubular propellant grain by liquid medium - Google Patents
Method for coating tubular propellant grain by liquid medium Download PDFInfo
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- CN109400424B CN109400424B CN201811246171.7A CN201811246171A CN109400424B CN 109400424 B CN109400424 B CN 109400424B CN 201811246171 A CN201811246171 A CN 201811246171A CN 109400424 B CN109400424 B CN 109400424B
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- positioning piece
- coating
- propellant grain
- tubular propellant
- upper positioning
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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
- C06B21/0083—Treatment of solid structures, e.g. for coating or impregnating with a modifier
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- Chemical & Material Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Organic Chemistry (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
The invention relates to a method for coating tubular propellant grains by adopting a liquid medium, belonging to the field of propellant charge coating. The coating method is realized by adopting an upper positioning piece and a lower positioning piece; the lower positioning piece and the upper positioning piece are both of cylindrical structures, and cylindrical positioning columns extend from the inner side end faces of the two positioning pieces; wherein, the center and the excircle of the upper positioning piece are both axially provided with exhaust holes; the specific coating steps are as follows: the upper positioning piece and the lower positioning piece are inserted into inner holes at two ends of the tubular propellant grain, the sleeve-shaped thermal shrinkage type cladding flame-retardant material is sleeved outside the tubular propellant grain, and the opening parts at two ends are fixed through a clamp to form a cladding part; one end of the lower positioning piece of the cladding assembly is immersed into a high-temperature liquid medium downwards, and the immersion liquid level of the cladding assembly does not exceed the upper end face of the upper positioning piece; and after heating is finished, taking out the upper positioning piece and the lower positioning piece to finish coating. The coating method is suitable for coating the tubular propellant grain by the thermal shrinkage type coating flame-retardant material.
Description
Technical Field
The invention relates to a method for coating a tubular charge by adopting a liquid medium, belonging to the field of propellant charge coating.
Background
The coating serves as an important component of the propellant charge, the properties and the coating effect of which directly influence the reliability of the engine charge. In recent years, as the development of new coating materials increases, the coating methods matched with the new coating materials also need to be innovated continuously. When a certain heat-shrinkable coated flame-retardant material coats the tubular propellant, the processed sleeve-shaped coated material is sleeved outside the propellant grains, and the coated material is coated and bonded with the propellant grains after being shrunk in a hot air heating mode. And the mode of adopting hot-blast heating can not realize heating whole cladding simultaneously, and the degree of cladding material shrink is inconsistent, makes the cladding thickness of cladding inhomogeneous, influences the cladding effect.
Disclosure of Invention
The invention aims to solve the problem of uneven coating thickness when a hot air heating mode is adopted to coat a certain heat shrinkage type coating flame-retardant material in the traditional process, and provides a method for coating a tubular charge by adopting a liquid medium.
The purpose of the invention is realized by the following technical scheme:
the invention relates to a method for coating a tubular explosive column by adopting a liquid medium, which is realized by adopting an upper positioning piece and a lower positioning piece;
the lower positioning piece is of a cylindrical structure with the outer diameter larger than that of the tubular propellant grain, a cylindrical positioning column with the outer diameter matched with the inner diameter of the tubular propellant grain extends upwards from the center of the upper end face of the lower positioning piece, and a clamp installation groove is formed in the side wall of the lower positioning piece;
the upper positioning piece is of a cylindrical structure with the outer diameter larger than that of the tubular propellant grain, a cylindrical positioning column with the outer diameter matched with the inner diameter of the tubular propellant grain extends upwards from the center of the lower end face of the upper positioning piece, exhaust holes are axially formed in the center and the outer circle of the upper positioning piece, and a hoop mounting groove is formed in the side wall of the upper positioning piece;
the specific coating steps are as follows: the upper positioning piece and the lower positioning piece are respectively inserted into inner holes at two ends of the tubular propellant grain through respective cylindrical positioning columns, sealing gaskets are arranged at the butt joint positions of the upper positioning piece and the lower positioning piece and the inner holes at two ends of the tubular propellant grain, and the exhaust hole in the center of the upper positioning piece exhausts the pressurization of the inner hole of the tubular propellant grain when the upper positioning piece and the lower positioning piece are inserted; sleeving the sleeve-shaped thermal shrinkage type coated flame-retardant material outside the tubular propellant grain, and fixing the mouth parts at two ends of the sleeve-shaped thermal shrinkage type coated flame-retardant material on the side walls of the upper positioning piece and the lower positioning piece respectively through a clamp to form a coated assembly; one end of the lower positioning piece of the cladding assembly is immersed into a high-temperature liquid medium downwards, and the immersion liquid level of the cladding assembly does not exceed the upper end face of the upper positioning piece; the sleeve-shaped thermal shrinkage type coating flame-retardant material retracts under the heating of a high-temperature liquid medium, the coating is stuck to the outer side of the coating assembly, and air between the tubular propellant grain and the thermal shrinkage type coating flame-retardant material is exhausted from an exhaust hole on the excircle of the upper positioning piece; and after heating is finished, taking out the coating assembly, shearing off the bonding parts of the thermal shrinkage type coating flame-retardant material and the side walls of the upper positioning piece and the lower positioning piece, and finally taking out the upper positioning piece and the lower positioning piece from inner holes at two ends of the tubular propellant grain to finish coating.
Furthermore, an annular retraction groove with the outer diameter smaller than the outer diameter of the tubular propellant grain is machined on the outer edge of the upper end of the lower positioning piece, an annular retraction groove with the outer diameter smaller than the outer diameter of the tubular propellant grain is machined on the outer edge of the lower end of the upper positioning piece, and when the sleeve-shaped thermal shrinkage type cladding flame retardant material retracts under the heating of a high-temperature liquid medium, the two ends of the tubular propellant grain are sunken inwards, and the cladding area is complete.
Advantageous effects
The coating method is suitable for coating the tubular propellant grain by the thermal shrinkage type coating flame-retardant material, and has simple coating operation and high coating efficiency; because of adopting the high-temperature liquid medium, the degree of shrinkage of the coating material is good in consistency, the coating thickness of the coating layer is uniform, and the coating effect is good.
Drawings
FIG. 1 is a schematic structural diagram of a clad member formed in the cladding method of the present invention;
FIG. 2 is a schematic structural view of a lower positioning member of the covering assembly of the present invention;
FIG. 3 is a schematic structural view of an upper positioning member of the covering member according to the present invention;
in the drawings, 1-lower positioning element; 2-a tubular propellant charge; 3-a sleeve-shaped thermal shrinkage type coating flame-retardant material; 4-upper positioning piece.
Detailed Description
The invention is further described with reference to the following figures and examples.
Examples
The method for coating the tubular propellant grain of a certain type by adopting the coating method is realized by adopting an upper positioning piece 4 and a lower positioning piece 1;
as shown in fig. 2, the lower positioning member 1 is a cylindrical structure with an outer diameter larger than the outer diameter of the tubular propellant grain 2, an annular retraction groove with an outer diameter smaller than the outer diameter of the tubular propellant grain 2 is processed at the outer edge of the upper end of the lower positioning member 1, a cylindrical positioning column with an outer diameter matched with the inner diameter of the tubular propellant grain 2 extends upwards from the center of the upper end surface of the lower positioning member 1, and a hoop installation groove is formed in the side wall of the lower positioning member 1;
as shown in fig. 3, the upper positioning member 4 is a cylindrical structure with an outer diameter larger than the outer diameter of the tubular propellant grain 2, an annular retraction groove with an outer diameter smaller than the outer diameter of the tubular propellant grain 2 is processed at the outer edge of the lower end of the upper positioning member 4, a cylindrical positioning column with an outer diameter matched with the inner diameter of the tubular propellant grain 2 extends upwards from the center of the lower end surface of the upper positioning member 4, exhaust holes are axially formed in the center and the outer circle of the upper positioning member 4, and a hoop mounting groove is formed in the side wall of the upper positioning member 4;
the specific coating steps are as follows: the upper positioning piece 4 and the lower positioning piece 1 are respectively inserted into inner holes at two ends of the tubular propellant grain 2 through respective cylindrical positioning columns, sealing gaskets are arranged at the butt joint positions of the upper positioning piece 4 and the lower positioning piece 1 and the inner holes at two ends of the tubular propellant grain 2, and the exhaust hole in the center of the upper positioning piece 4 exhausts the pressurization of the inner hole of the tubular propellant grain 2 when the upper positioning piece 4 and the lower positioning piece 1 are inserted; sleeving the sleeve-shaped thermal shrinkage type coated flame-retardant material 3 outside the tubular propellant grain 2, and fixing the mouth parts at two ends of the sleeve-shaped thermal shrinkage type coated flame-retardant material 3 on the side walls of the upper positioning piece 4 and the lower positioning piece 1 respectively through a hoop to form a coated piece, as shown in figure 1; one end of a lower positioning piece 1 of the coating and closing piece is immersed into a high-temperature liquid medium downwards, and the immersion liquid level of the coating and closing piece does not exceed the upper end face of an upper positioning piece 4; the sleeve-shaped thermal shrinkage type coating flame-retardant material 3 retracts under the heating of a high-temperature liquid medium, the coating is stuck on the outer side of the coating assembly, and air between the tubular propellant grain 2 and the thermal shrinkage type coating flame-retardant material is exhausted from an exhaust hole on the excircle of the upper positioning piece 4; and after heating is finished, taking out the coating assembly, cutting off the bonding parts of the thermal shrinkage type coating flame-retardant material and the side walls of the upper positioning piece 4 and the lower positioning piece 1, and finally taking out the upper positioning piece 4 and the lower positioning piece 1 from inner holes at two ends of the tubular propellant grain 2 to finish coating.
Claims (4)
1. The method for coating the tubular propellant grain by adopting the liquid medium is characterized by comprising the following steps: the method is realized by adopting an upper positioning piece and a lower positioning piece;
the lower positioning piece is of a cylindrical structure with the outer diameter larger than that of the tubular propellant grain, a cylindrical positioning column with the outer diameter matched with the inner diameter of the tubular propellant grain extends upwards from the center of the upper end face of the lower positioning piece, and a clamp installation groove is formed in the side wall of the lower positioning piece;
the upper positioning piece is of a cylindrical structure with the outer diameter larger than that of the tubular propellant grain, a cylindrical positioning column with the outer diameter matched with the inner diameter of the tubular propellant grain extends upwards from the center of the lower end face of the upper positioning piece, exhaust holes are axially formed in the center and the outer circle of the upper positioning piece, and a hoop mounting groove is formed in the side wall of the upper positioning piece;
the specific coating steps are as follows: the upper positioning piece and the lower positioning piece are respectively inserted into inner holes at two ends of the tubular propellant grain through respective cylindrical positioning columns, and the exhaust hole in the center of the upper positioning piece exhausts the pressurization of the inner hole of the tubular propellant grain when the upper positioning piece and the lower positioning piece are inserted; sleeving the sleeve-shaped thermal shrinkage type coated flame-retardant material outside the tubular propellant grain, and fixing the mouth parts at two ends of the sleeve-shaped thermal shrinkage type coated flame-retardant material on the side walls of the upper positioning piece and the lower positioning piece respectively through a clamp to form a coated assembly; one end of the lower positioning piece of the cladding assembly is immersed into a high-temperature liquid medium downwards, and the immersion liquid level of the cladding assembly does not exceed the upper end face of the upper positioning piece; the sleeve-shaped thermal shrinkage type coating flame-retardant material retracts under the heating of a high-temperature liquid medium, the coating is stuck to the outer side of the coating assembly, and air between the tubular propellant grain and the thermal shrinkage type coating flame-retardant material is exhausted from an exhaust hole on the excircle of the upper positioning piece; and after heating is finished, taking out the coating assembly, shearing off the bonding parts of the thermal shrinkage type coating flame-retardant material and the side walls of the upper positioning piece and the lower positioning piece, and finally taking out the upper positioning piece and the lower positioning piece from inner holes at two ends of the tubular propellant grain to finish coating.
2. A method of coating a tubular propellant charge with a liquid medium as claimed in claim 1, wherein: the outer edge of the upper end of the lower positioning piece is provided with an annular retraction groove with the outer diameter smaller than that of the tubular propellant grain.
3. A method of coating a tubular propellant charge with a liquid medium as claimed in claim 1, wherein: an annular retraction groove with the outer diameter smaller than that of the tubular propellant grain is processed on the outer edge of the lower end of the upper positioning piece.
4. A method of coating a tubular propellant charge with a liquid medium as claimed in claim 1, wherein: and sealing gaskets are arranged at the butt joint parts of the upper positioning piece and the lower positioning piece and the inner holes at the two ends of the tubular propellant grain.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811246171.7A CN109400424B (en) | 2018-10-25 | 2018-10-25 | Method for coating tubular propellant grain by liquid medium |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811246171.7A CN109400424B (en) | 2018-10-25 | 2018-10-25 | Method for coating tubular propellant grain by liquid medium |
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| Publication Number | Publication Date |
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| CN109400424A CN109400424A (en) | 2019-03-01 |
| CN109400424B true CN109400424B (en) | 2020-10-09 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3954526A (en) * | 1971-02-22 | 1976-05-04 | Thiokol Corporation | Method for making coated ultra-fine ammonium perchlorate particles and product produced thereby |
| CN101982721A (en) * | 2010-10-13 | 2011-03-02 | 宜宾北方川安化工有限公司 | Method for coating grains |
| CN104276910A (en) * | 2013-07-22 | 2015-01-14 | 湖北航天化学技术研究所 | Process for forming burning restriction layer of explosive column of gas generating agent |
| CN106589650A (en) * | 2016-12-27 | 2017-04-26 | 郑州源冉生物技术有限公司 | Fine-performance plastic material and preparation method thereof |
| CN207746043U (en) * | 2017-09-29 | 2018-08-21 | 中国航天科技集团公司川南机械厂 | One kind automatic coating unit of powder column containing energy |
-
2018
- 2018-10-25 CN CN201811246171.7A patent/CN109400424B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3954526A (en) * | 1971-02-22 | 1976-05-04 | Thiokol Corporation | Method for making coated ultra-fine ammonium perchlorate particles and product produced thereby |
| CN101982721A (en) * | 2010-10-13 | 2011-03-02 | 宜宾北方川安化工有限公司 | Method for coating grains |
| CN104276910A (en) * | 2013-07-22 | 2015-01-14 | 湖北航天化学技术研究所 | Process for forming burning restriction layer of explosive column of gas generating agent |
| CN106589650A (en) * | 2016-12-27 | 2017-04-26 | 郑州源冉生物技术有限公司 | Fine-performance plastic material and preparation method thereof |
| CN207746043U (en) * | 2017-09-29 | 2018-08-21 | 中国航天科技集团公司川南机械厂 | One kind automatic coating unit of powder column containing energy |
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| Publication number | Publication date |
|---|---|
| CN109400424A (en) | 2019-03-01 |
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