CN111022216A - Inner hole combustion charge structure capable of realizing large combustion surface ratio climbing inner trajectory - Google Patents
Inner hole combustion charge structure capable of realizing large combustion surface ratio climbing inner trajectory Download PDFInfo
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- CN111022216A CN111022216A CN201911158715.9A CN201911158715A CN111022216A CN 111022216 A CN111022216 A CN 111022216A CN 201911158715 A CN201911158715 A CN 201911158715A CN 111022216 A CN111022216 A CN 111022216A
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- combustion
- hole
- grain
- lining layer
- trajectory
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/10—Shape or structure of solid propellant charges
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The invention discloses an inner hole combustion charge structure capable of realizing a climbing inner trajectory with a large combustion surface ratio, which belongs to the technical field of engines and comprises the following components: a grain, a lining layer and a coating layer; the powder column is a cylinder which is provided with an axial through hole, and two end surfaces of the powder column are respectively processed into convex arc surfaces, namely two axial end surfaces of the powder column are hemispherical surfaces with a central hole; the lining layer is coated on the outer surface of the grain, and the shape of the lining layer is consistent with that of the outer surface of the grain; two annular coating layers are respectively coated on the inner circumferential surfaces of two ends of the central axial through hole of the explosive column, and the outer ends of the two coating layers are respectively fixedly connected on the lining layers of the corresponding ends; the invention can reduce the outer diameter of the charging structure and further reduce the outer diameter of the engine while achieving the climbing inner trajectory target with large combustion surface ratio.
Description
Technical Field
The invention belongs to the technical field of engines, and particularly relates to an inner hole combustion charge structure capable of realizing a large combustion surface ratio climbing inner trajectory.
Background
The charge structure of traditional solid rocket engine for realizing climbing inner trajectory has many kinds, and the most widely used charge structure is inner hole combustion charge structure. In the hole burning charge structure combustion process, along with the increase of charge structure diameter, combustion area constantly increases to realize the continuous improvement of working pressure.
The inner hole combustion charging structure is usually large in initial combustion surface, the area ratio of the initial combustion surface to the combustion termination moment is in direct proportion to the square of the ratio of the inner hole radius to the outer radius of the charging structure, when the ratio of the combustion termination point working pressure to the initial working pressure is required to be large, namely the ratio of the combustion termination ignition surface to the initial combustion surface is required to be large, the outer diameter of the charging structure is large, the outer diameter of the whole engine is also large, and under the condition that the outer diameter of the engine is limited, the scheme cannot be realized.
Disclosure of Invention
In view of the above, the invention provides an inner hole combustion charge structure capable of realizing an inner climbing trajectory with a large combustion surface ratio, which is capable of reducing the outer diameter size of the charge structure and further reducing the outer diameter size of an engine while achieving the inner climbing trajectory target with the large combustion surface ratio.
The invention is realized by the following technical scheme:
an inner hole combustion charge structure capable of realizing an inner trajectory with a large combustion surface ratio climbing comprises: a grain, a lining layer and a coating layer;
the powder column is a cylinder which is provided with an axial through hole, and two end surfaces of the powder column are respectively processed into convex arc surfaces, namely two axial end surfaces of the powder column are hemispherical surfaces with a central hole; the lining layer is coated on the outer surface of the grain, and the shape of the lining layer is consistent with that of the outer surface of the grain; two annular coating layers are respectively coated on the inner circumferential surfaces of two ends of the central axial through hole of the explosive column, and the outer ends of the two coating layers are respectively fixedly connected on the lining layers of the corresponding ends;
the coating layer and the lining layer are both made of non-flammable materials.
Further, the length of the coating layer is the same as the radius of the hemispherical surface at the end part of the grain.
Has the advantages that: according to the invention, the coating layers are processed at the two ends of the central through hole of the explosive column for coating treatment, so that a smaller initial combustion area can be realized under the condition of a longer charging structure; and the arc surfaces arranged at the two ends of the explosive column are combined, and the radius of the arc is consistent with the length of the coating layer, so that the explosive charging structure burns under the parallel layer combustion rule, and when the combustion termination point is reached, the area of the combustion surface reaches the maximum. Therefore, the design of the inner trajectory of the solid rocket engine with large combustion surface ratio climbing is realized, and the outer diameter size of the charging structure is reduced compared with the traditional design mode of the inner hole combustion charging structure.
Drawings
FIG. 1 is a structural component diagram of the present invention;
FIG. 2 is a schematic view of the charge configuration of the present invention after combustion of one half;
wherein, 1-grain, 2-lining layer, 3-coating layer.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment provides a bore combustion charge structure capable of realizing a high combustion surface ratio climbing inner trajectory, referring to the attached figure 1, comprising: a grain 1, a lining layer 2 and a coating layer 3;
the powder column 1 is a cylinder provided with an axial through hole, and two end faces of the powder column are respectively provided with an outward convex arc surface, namely two axial end faces of the powder column are hemispherical surfaces provided with a central hole; the lining layer 2 is coated on the outer surface of the grain 1, and the shape of the lining layer 2 is consistent with that of the outer surface of the grain; two annular coating layers 3 are respectively coated on the inner circumferential surfaces of two ends of an axial through hole of the grain 1, and the outer ends of the two coating layers 3 are respectively fixedly connected on the lining layer 2 of the corresponding end;
wherein the length of the coating layer 3 is the same as the radius of the hemispherical surface at the end part of the grain 1;
the coating layer 3 and the lining layer 2 are both made of non-flammable materials.
The working principle is as follows: because the charge structure follows the parallel layer combustion law, in the whole combustion process of the charge structure, the combustion area is continuously increased, namely the initial combustion surface is the combustion surface in the middle of the two coating layers 3, the combustion surface area is continuously increased along with the inward movement of the combustion surface, when the combustion is half, the charge structure is shaped as shown in figure 2, and when the combustion end point is reached, the combustion surface area is maximum.
Thus, the charge outer diameter dimension of the present embodiment is smaller than the outer diameter of a conventional bore combustion charge, while achieving the same combustion face ratio.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. An inner hole combustion charge structure capable of realizing a high combustion surface ratio climbing inner trajectory, which is characterized by comprising: a grain (1), a lining layer (2) and a coating layer (3);
the powder column (1) is a cylinder which is provided with an axial through hole, and two end surfaces of the powder column are respectively provided with an outward convex arc surface, namely two axial end surfaces of the powder column are hemispherical surfaces with a central hole; the lining layer (2) is coated on the outer surface of the grain (1), and the shape of the lining layer (2) is consistent with that of the outer surface of the grain; the two annular coating layers (3) are respectively coated on the inner circumferential surfaces of two ends of a central axial through hole of the explosive column (1), and the outer ends of the two coating layers (3) are respectively fixedly connected on the lining layers (2) of the corresponding ends;
the coating layer (3) and the lining layer (2) are both made of non-flammable materials.
2. The structure of the inner hole combustion charge capable of realizing the inner trajectory with large combustion surface ratio climbing as claimed in claim 1, wherein the length of the coating layer (3) is the same as the radius of the hemispherical surface at the end of the charge column (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911158715.9A CN111022216A (en) | 2019-11-22 | 2019-11-22 | Inner hole combustion charge structure capable of realizing large combustion surface ratio climbing inner trajectory |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911158715.9A CN111022216A (en) | 2019-11-22 | 2019-11-22 | Inner hole combustion charge structure capable of realizing large combustion surface ratio climbing inner trajectory |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111022216A true CN111022216A (en) | 2020-04-17 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911158715.9A Pending CN111022216A (en) | 2019-11-22 | 2019-11-22 | Inner hole combustion charge structure capable of realizing large combustion surface ratio climbing inner trajectory |
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| Country | Link |
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| CN (1) | CN111022216A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114233517A (en) * | 2021-12-21 | 2022-03-25 | 西安零壹空间科技有限公司 | High-overload solid rocket engine and design method of explosive type thereof |
| CN114856858A (en) * | 2022-03-02 | 2022-08-05 | 武汉高德红外股份有限公司 | Solid rocket engine powder charge grain structure and solid rocket engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103267453A (en) * | 2013-05-27 | 2013-08-28 | 湖北航天化学技术研究所 | Gas generator propellant grain |
| CN109578148A (en) * | 2018-11-07 | 2019-04-05 | 北方特种能源集团有限公司西安庆华公司 | A kind of fanjet pyrotechnic initiator abnormity powder charge |
| CN110145411A (en) * | 2019-05-27 | 2019-08-20 | 上海新力动力设备研究所 | A kind of solid propellant rocket inner hole cast charge constitution and method with inner cavity partition |
| CN110439708A (en) * | 2019-08-30 | 2019-11-12 | 南京理工大学 | A kind of part cladding without jet pipe propeller powder column |
-
2019
- 2019-11-22 CN CN201911158715.9A patent/CN111022216A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103267453A (en) * | 2013-05-27 | 2013-08-28 | 湖北航天化学技术研究所 | Gas generator propellant grain |
| CN109578148A (en) * | 2018-11-07 | 2019-04-05 | 北方特种能源集团有限公司西安庆华公司 | A kind of fanjet pyrotechnic initiator abnormity powder charge |
| CN110145411A (en) * | 2019-05-27 | 2019-08-20 | 上海新力动力设备研究所 | A kind of solid propellant rocket inner hole cast charge constitution and method with inner cavity partition |
| CN110439708A (en) * | 2019-08-30 | 2019-11-12 | 南京理工大学 | A kind of part cladding without jet pipe propeller powder column |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114233517A (en) * | 2021-12-21 | 2022-03-25 | 西安零壹空间科技有限公司 | High-overload solid rocket engine and design method of explosive type thereof |
| CN114233517B (en) * | 2021-12-21 | 2024-03-29 | 西安零壹空间科技有限公司 | Solid rocket engine for high overload and drug pattern design method thereof |
| CN114856858A (en) * | 2022-03-02 | 2022-08-05 | 武汉高德红外股份有限公司 | Solid rocket engine powder charge grain structure and solid rocket engine |
| CN114856858B (en) * | 2022-03-02 | 2024-02-06 | 武汉高德红外股份有限公司 | Solid rocket engine powder charge grain structure and solid rocket engine |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20200417 |
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