CN109163621B - Can realize that EFP rotational stabilization flies gather can charge structure - Google Patents
Can realize that EFP rotational stabilization flies gather can charge structure Download PDFInfo
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- CN109163621B CN109163621B CN201811080891.0A CN201811080891A CN109163621B CN 109163621 B CN109163621 B CN 109163621B CN 201811080891 A CN201811080891 A CN 201811080891A CN 109163621 B CN109163621 B CN 109163621B
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- efp
- aluminum alloy
- cylindrical explosive
- spiral
- explosive charging
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
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Abstract
The invention discloses an energy-gathered charge structure capable of realizing EFP (extended face protection) rotating stable flight, which comprises a columnar charge shell for charging explosives, wherein a plurality of spiral grooves are axially formed in the outer surface of the columnar charge shell; the concave surface laminating of hemisphere type shaped as a Chinese character meaning pattern cover has a plurality of arc aluminum alloy paster that are the spiral and distribute, and the one end of arc aluminum alloy paster is located the outer edge of the concave surface of hemisphere type as a Chinese character meaning pattern cover, and the other end of arc aluminum alloy paster is located the concave surface front end of hemisphere type as a Chinese character meaning pattern cover and constitutes a circular port between the other end of a plurality of arc aluminum alloy paster. Compared with the prior art, the invention can realize the long-distance stable flight of EFP trajectory collimation and realize the accurate hit index of EFP to a remote target.
Description
Technical Field
The invention relates to the technical field of rotary EFP with tail wings, in particular to an energy-gathered charging structure capable of realizing rotary stable flight of EFP.
Background
Blast-formed projectiles (EFPs) play an important role in end-effector weapon systems, and future wars require EFP warhead systems to function further away, thus increasing the demand on EFP flight stability. There is a strong need for EFP technology that can achieve stable long-range (>100m) flight, trajectory alignment, but this is not the case in the presently disclosed tail rotating EFP technology.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, and provides an energy-gathering charge structure capable of realizing EFP rotation stable flight, which provides rotation stable torque for the EFP under the action of air resistance so as to realize flight stability.
In order to achieve the purpose, the invention is implemented according to the following technical scheme:
an energy-gathered charge structure capable of realizing EFP (extended face protection) rotating stable flight comprises a columnar charge shell for charging explosives, wherein a plurality of spiral grooves are axially formed in the outer surface of the columnar charge shell; the concave surface laminating of hemisphere type shaped as a Chinese character meaning pattern cover has a plurality of arc aluminum alloy paster that are the spiral and distribute, and the one end of arc aluminum alloy paster is located the outer edge of the concave surface of hemisphere type as a Chinese character meaning pattern cover, and the other end of arc aluminum alloy paster is located the concave surface front end of hemisphere type as a Chinese character meaning pattern cover and constitutes a circular port between the other end of a plurality of arc aluminum alloy paster.
Further, the cross section of the spiral groove is rectangular.
Further, the spiral direction of the spiral groove is left-handed or right-handed.
When the explosive explodes, the explosive cover and the gasket form a fold type spiral tail wing under the action of explosive detonation pressure; simultaneously, the distribution rule of detonation wave action on the liner is changed through the spiral grooves on the outer surface of the cylindrical explosive charging shell to adjust the axial initial rotating speed of the EFP, and the two actions are superposed to ensure that the explosive-formed projectile has the initial rotating speed and realizes the self-spinning stable flight under the action of air resistance.
Compared with the prior art, the invention can realize the long-distance stable flight of EFP trajectory collimation and realize the accurate hit index of EFP to a remote target.
Drawings
Fig. 1 is a cross-sectional view of the present invention.
Figure 2 is a front view of a shaped charge case of the present invention.
Figure 3 is a bottom view of the cylindrical charge case of the present invention.
Fig. 4 is a top view of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings and examples. The specific embodiments described herein are merely illustrative of the invention and do not limit the invention.
As shown in fig. 1 to 4, the energy-gathered charge structure capable of realizing EFP rotation stable flight in this embodiment includes a cylindrical charge casing 3 for charging explosive, a plurality of spiral grooves 31 are axially formed in the outer surface of the cylindrical charge casing 3, in this embodiment, the cross sections of the spiral grooves 31 are rectangular, as shown in fig. 1, the spiral direction of the spiral grooves 31 is right-handed, the rear end of the cylindrical charge casing 3 is open, and the rear end of the cylindrical explosive 1 is completely attached to the spherical surface of the hemispherical charge cover 2; a plurality of arc-shaped aluminum alloy patches 4 which are spirally distributed are attached to the concave surface of the hemispherical liner 2, one ends of the arc-shaped aluminum alloy patches 4 are positioned on the outer edge of the concave surface of the hemispherical liner 2, the other ends of the arc-shaped aluminum alloy patches 4 are positioned at the front end of the concave surface of the hemispherical liner 2, and a circular hole 41 is formed between the other ends of the arc-shaped aluminum alloy patches 4; as shown in fig. 4, the arc-shaped aluminum alloy patch 4 is provided with a first arc 401, a second arc 402, a third arc 403 and a fourth arc 404, the first arc 401 coincides with the outer edge circle of the hemispherical shaped charge liner 2, i.e. the radius of the first arc 401 is the same as the radius of the hemispherical shaped charge liner 2, and the third arc 403 coincides with the circular hole 41, i.e. the radius of the third arc 403 is the same as the radius of the circular hole 41.
As shown in fig. 1, the columnar explosive 1 is initiated by using a central point and propagates with the spherical detonation wave of the hemispherical explosive cover 2, the detonation wave at the inner wall surface of the columnar explosive charging shell 3 propagates along the spiral direction of the spiral groove 31, and the spherical detonation wave of the hemispherical explosive cover 2 generates circumferential components at the edge of the inner wall of the columnar explosive charging shell 3 to form circumferential rotation impulse; when the decomposed detonation waves act on the inner surface (spherical surface) of the hemispherical liner 2 in the form of axial and circumferential components, the EFP obtains axial movement impulse and circumferential rotation impulse, and the hemispherical liner 2 performs circumferential accelerated rotation; when the detonation wave acts on the hemispherical shaped charge liner 2, a stress wave (compression wave) is generated and is transmitted from the inner surface to the outer surface of the hemispherical shaped charge liner 2, the outer surface (concave surface) of the hemispherical shaped charge liner 2 is tightly attached to the arc-shaped aluminum alloy patch 4, the stress wave is reflected on the surface of the arc-shaped aluminum alloy patch 4, and the reflected pressure is the compression wave due to the fact that rho copper c copper is greater than rho aluminum c aluminum, and the compression wave interacts with the compression wave which is subsequently followed in the hemispherical shaped charge liner 2, so that the retarded hemispherical shaped charge liner 2 is crushed at the speed. At the position where the inner surface of the hemispherical liner 2 is not in contact with the arc-shaped aluminum alloy patch 4, the stress wave is reflected and transmitted on the inner surface (free surface) of the hemispherical liner 2, and the interference effect of the reflected wave on the compression wave in the hemispherical liner 2 is small, so that the crushing speed of the hemispherical liner 2 is not influenced; because the arc-shaped aluminum alloy patches 4 are spirally arranged in a strip shape, in the EFP forming process, the axial collapse speed of the mass of the hemispherical shaped charge liner 2 at the contact position of the arc-shaped aluminum alloy patches 4 and the inner surface of the hemispherical shaped charge liner 2 is lower than the collapse speed of the mass of the hemispherical shaped charge liner 2 at the free surface, and a spiral fold-type empennage is formed at the cover opening of the hemispherical shaped charge liner 2; when explosive explodes, the semispherical shaped charge shell 2 forms an EFP with a spiral tail wing and an initial rotating speed under the two actions of the columnar shaped charge shell 3 and the arc-shaped aluminum alloy patch 4.
Under the action of air resistance, the spiral type empennage generates a rotation stabilizing moment, EFP spin acceleration is facilitated, trajectory collimation stability flight is guaranteed, and therefore long-distance accurate combat tactical indexes are achieved.
The technical solution of the present invention is not limited to the limitations of the above specific embodiments, and all technical modifications made according to the technical solution of the present invention fall within the protection scope of the present invention.
Claims (3)
1. An ability charge structure that can realize EFP rotational stabilization flight, includes the columnar shape powder charge casing that is used for filling the explosive, its characterized in that: the cylindrical explosive charging device comprises a cylindrical explosive charging shell, a cylindrical explosive charging sleeve and a cylindrical explosive charging sleeve, wherein a plurality of spiral grooves are axially formed in the outer surface of the cylindrical explosive charging shell, the rear end of the cylindrical explosive charging shell is open, cylindrical explosive is filled in the cylindrical explosive charging shell, a hemispherical shaped charge cover is arranged in the open end of the cylindrical explosive charging shell, the spherical surface of the hemispherical shaped charge cover faces the inside of the cylindrical explosive charging shell, and the rear end of the cylindrical explosive is completely attached to the spherical surface of the hemispherical shaped charge cover; the concave surface laminating of hemisphere type shaped as a Chinese character meaning pattern cover has a plurality of arc aluminum alloy paster that are the spiral and distribute, and the one end of arc aluminum alloy paster is located the outer edge of the concave surface of hemisphere type as a Chinese character meaning pattern cover, and the other end of arc aluminum alloy paster is located the concave surface front end of hemisphere type as a Chinese character meaning pattern cover and constitutes a circular port between the other end of a plurality of arc aluminum alloy paster.
2. A shaped charge configuration to enable rotationally stable flight of an EFP as claimed in claim 1 wherein: the cross section of the spiral groove is rectangular.
3. A shaped charge configuration to enable rotationally stable flight of an EFP as claimed in claim 1 wherein: the spiral direction of the spiral groove is left-handed or right-handed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811080891.0A CN109163621B (en) | 2018-09-17 | 2018-09-17 | Can realize that EFP rotational stabilization flies gather can charge structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811080891.0A CN109163621B (en) | 2018-09-17 | 2018-09-17 | Can realize that EFP rotational stabilization flies gather can charge structure |
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| CN109163621A CN109163621A (en) | 2019-01-08 |
| CN109163621B true CN109163621B (en) | 2022-04-01 |
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| CN201811080891.0A Active CN109163621B (en) | 2018-09-17 | 2018-09-17 | Can realize that EFP rotational stabilization flies gather can charge structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110375595A (en) * | 2019-05-15 | 2019-10-25 | 中国人民解放军陆军工程大学 | A kind of jetting gun type explosively formed projectile ammunition |
| CN113607005B (en) * | 2021-07-22 | 2022-04-15 | 北京理工大学 | Can form gradient activation activity and invade shaped charge structure of exploding body of rod |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5925845A (en) * | 1997-08-01 | 1999-07-20 | Alliant Techsystems Inc. | Shoot-through cover for an explosively formed penetrator warhead |
| DE10221759A1 (en) * | 2002-05-16 | 2003-12-04 | Diehl Munitionssysteme Gmbh | warhead |
| JP2005090782A (en) * | 2003-09-12 | 2005-04-07 | Daikin Ind Ltd | Efp warhead |
| CN101427097A (en) * | 2006-03-04 | 2009-05-06 | 奥尔福德研究有限公司 | An explosive charge |
| CN205175257U (en) * | 2015-11-17 | 2016-04-20 | 山西江阳工程爆破有限公司 | Blasting loaded constitution in water hole |
-
2018
- 2018-09-17 CN CN201811080891.0A patent/CN109163621B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5925845A (en) * | 1997-08-01 | 1999-07-20 | Alliant Techsystems Inc. | Shoot-through cover for an explosively formed penetrator warhead |
| DE10221759A1 (en) * | 2002-05-16 | 2003-12-04 | Diehl Munitionssysteme Gmbh | warhead |
| JP2005090782A (en) * | 2003-09-12 | 2005-04-07 | Daikin Ind Ltd | Efp warhead |
| CN101427097A (en) * | 2006-03-04 | 2009-05-06 | 奥尔福德研究有限公司 | An explosive charge |
| CN205175257U (en) * | 2015-11-17 | 2016-04-20 | 山西江阳工程爆破有限公司 | Blasting loaded constitution in water hole |
Non-Patent Citations (1)
| Title |
|---|
| 贴片球缺药型罩成型斜置尾翼EFP;左振英等;《弹道学报》;20101231;第22卷(第3期);全文 * |
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| CN109163621A (en) | 2019-01-08 |
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