CN112985174B - Cylindrical orthogonal type sealing rear end cover with rectification effect on shock wave reflection - Google Patents
Cylindrical orthogonal type sealing rear end cover with rectification effect on shock wave reflection Download PDFInfo
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- CN112985174B CN112985174B CN202110187113.7A CN202110187113A CN112985174B CN 112985174 B CN112985174 B CN 112985174B CN 202110187113 A CN202110187113 A CN 202110187113A CN 112985174 B CN112985174 B CN 112985174B
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- rear end
- end cover
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- cover body
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F7/00—Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, e.g. using spigots
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Abstract
The invention relates to a cylindrical surface orthogonal type sealing rear end cover with a rectification effect on shock wave reflection, which comprises a rear end cover body, a flange and a pressure ring, wherein the flange is used for being installed on the rear end face of an emission box, the pressure ring is connected with the flange, the skirt edge of the rear end cover body is placed in a flange sealing face, and the pressure ring is pressed on the skirt edge of the rear end cover body. Compared with the prior art, the cylindrical orthogonal type sealed rear end cover with the rectification effect on shock wave reflection is suitable for the rear end of a launching box, shock waves formed at a jet nozzle of a missile engine are reflected by the cylindrical surface on the inner surface of the rear end cover, formed longitudinal waves are arranged in the moving direction and then spread towards the front end of the launching box, the front end cover is opened by the shock waves, and the rear end cover is broken into a large block or a plurality of blocks along the weak area under the action of gas flow.
Description
Technical Field
The invention relates to a rear end cover, in particular to a cylindrical orthogonal type sealed rear end cover with a rectification effect on shock wave reflection.
Background
Along with the development of missile weapon systems, missile systems with higher movement speed, higher acceleration and stronger orbital transfer capacity are continuously developed, and in order to ensure that missiles can be quickly launched, the requirements on the response speed of a rear end cover of a launching box to shock waves generated when the missiles are launched and the capacity of smoothly opening a front end cover after the shock waves are rectified and reflected are higher; and because other technical properties of the missile system need to be ensured, the external pressure bearing capacity of the fragile cover needs to be ensured under the condition of ensuring the internal opening strength. At present, no research on a cylindrical orthogonal type sealing rear end cover with a rectifying effect on shock wave reflection exists.
Disclosure of Invention
The invention aims to provide a cylindrical orthogonal type sealing rear end cover with a rectification effect on shock wave reflection.
The cylindrical orthogonal type sealed rear end cover with the rectification effect on shock wave reflection is suitable for the rear end of a launching box, shock waves are formed at a jet nozzle of a missile engine, the motion direction of formed longitudinal waves is arranged after the shock waves are reflected by the cylindrical surface on the inner surface of the rear end cover, the longitudinal waves are spread towards the front end of the launching box, the front end cover is opened by the shock waves, and the rear end cover is broken into a large block or a plurality of blocks along the weak area under the action of gas flow.
The purpose of the invention can be realized by the following technical scheme:
the invention provides a cylindrical surface orthogonal type sealing rear end cover with a rectification effect on shock wave reflection, which comprises a rear end cover body, a flange and a pressure ring, wherein the flange is used for being installed on the rear end face of an emission box, the pressure ring is connected with the flange, the skirt edge of the rear end cover body is placed in a flange sealing face, and the pressure ring is pressed on the skirt edge of the rear end cover body.
In one embodiment of the invention, there are 1 flange,
in one embodiment of the present invention, the compression ring is provided in 1 number. Alternatively, the pressure ring may be assembled using multiple pieces.
In one embodiment of the present invention, the number of the rear end cover is 1.
In one embodiment of the present invention, the compression ring is connected to the flange by screws that fasten the rear end cover, the flange, and the compression ring.
In one embodiment of the invention, a sealing glue is coated on the sealing surface of the flange and the compression ring.
In one embodiment of the invention, after the flange is installed on the rear end face of the launch box, the sealing performance of the end face is ensured by using a sealing strip, a sealing ring or a sealing gasket.
In an embodiment of the invention, the rear cover skirt is sealed by the flange and the compression ring through a sealant.
In one embodiment of the present invention, the rear end cover skirt is fastened by the flange and the compression ring by screw fitting.
In an embodiment of the present invention, when the flange is used with a sealing strip or a sealing ring, the flange is provided with a groove for installing the sealing strip or the sealing ring, and when the flange is used with a sealing gasket, the flange is not provided with the groove.
In one embodiment of the invention, the rear end cover is provided with a weakened area along which the rear end cover fractures when the flow of missile engine fuel gas impinges on the rear end cover.
In one embodiment of the invention, the inner surface of the rear end cover body is designed into a cylindrical surface, and the cylindrical surface can arrange the motion direction of the shock wave formed from the engine nozzle, so that the reflected shock wave can be propagated towards the front end of the launching box, and the front end cover can be opened by the shock wave.
In one embodiment of the invention, the overall structural design of the rear end cover body ensures certain strength, and the rear end cover body can not be damaged when certain pressure gas exists in the launching box and can also resist shock wave impact and/or gas flow scouring reflected when the missile engine in the adjacent launching box works.
In an embodiment of the present invention, the rear end cover body is formed by thermosetting resin through a mold, or is formed by machining thermosetting foam material, or is formed by sheet metal or machining non-ferrous metal plate, or is formed by compression molding high-strength fiber and thermosetting resin impregnant.
In one embodiment of the invention, the flange is formed by machining and molding metal, or the flange is formed by compression molding high-strength fiber and thermosetting resin impregnant.
In one embodiment of the invention, the press ring is formed by metal processing or compression molding by high-strength fiber and thermosetting resin impregnant.
In the invention, the structural size of the inner surface of the rear end cover is designed according to the size of the port of the launching box and the position of the nozzle of the missile engine, and the height of the rear end cover is designed according to the end surface of the launching box, the structure of the inner surface and the thickness of the cover body.
Compared with the prior art, the invention has the technical advantages and beneficial effects mainly embodied in the following aspects:
by adopting the cylindrical orthogonal type sealing rear end cover with the rectifying effect on the shock wave reflection, when a guided missile in the launching box is launched, the shock wave is formed and spread in a divergent shape when the nozzle blocking cover of the rocket engine is opened, and after the shock wave is reflected by the cylindrical surface on the inner surface of the rear end cover, the movement direction of the formed longitudinal wave is arranged and spread towards the front end of the launching box, so that the front end cover is favorably opened by the shock wave; the rear end cover is broken into a large block or a plurality of blocks to fall along the weak area under the action of the fuel gas flow, so that the channel of the launching box is completely opened, the strength of the pressure field in the launching box is quickly attenuated, the safety of the launching box is protected, and the reliability of the launching box in repeated use is improved. That is to say, this rear end housing can realize being opened by the gas flow of missile engine blowout, opens the front end housing after rectifying to the shock wave of reflection again, realizes opening the function of guided missile passageway and protection launching box.
Drawings
FIG. 1 is an assembled view of a rear end cap in example 1;
FIG. 2 is an isometric view of a flange according to example 1;
FIG. 3 is an isometric view of a compression ring according to example 1;
FIG. 4 is an isometric view of a back end cover according to example 1;
FIG. 5 is a schematic view of determining an arc surface of the inner surface of the rear cover in embodiment 1;
fig. 6 is a schematic diagram of the motion path of the shock longitudinal wave after being finished by the rear end cover in embodiment 1.
The reference numbers in the figures indicate: 1 rear end cover body, 2 flanges and 3 press rings.
Detailed Description
The invention provides a cylindrical surface orthogonal type sealing rear end cover with a rectification effect on shock wave reflection, which comprises a rear end cover body, a flange and a pressure ring, wherein the flange is used for being installed on the rear end face of an emission box, the pressure ring is connected with the flange, the skirt edge of the rear end cover body is placed in a flange sealing face, and the pressure ring is pressed on the skirt edge of the rear end cover body.
In one embodiment of the invention, the flange is provided with 1,
in one embodiment of the present invention, the compression ring is provided in 1 number. Alternatively, the pressure ring may be assembled using multiple pieces.
In one embodiment of the present invention, the number of the rear end cover is 1.
In one embodiment of the present invention, the compression ring is connected to the flange by screws that fasten the rear end cover, the flange, and the compression ring.
In one embodiment of the invention, the flange and the compression ring sealing surface are coated with a sealant.
In one embodiment of the invention, after the flange is installed on the rear end face of the launch box, the sealing performance of the end face is ensured by using a sealing strip, a sealing ring or a sealing gasket.
In an embodiment of the invention, the rear cover skirt is sealed by the flange and the compression ring through a sealant.
In one embodiment of the present invention, the rear end cover skirt is fastened by the flange and the compression ring by screw fitting.
In an embodiment of the present invention, when the flange is used with a sealing strip or a sealing ring, the flange is provided with a groove for installing the sealing strip or the sealing ring, and when the flange is used with a sealing gasket, the flange is not provided with the groove.
In one embodiment of the invention, the rear end cover is provided with a weakened area along which the rear end cover breaks when the missile engine gas stream impacts the rear end cover.
In one embodiment of the invention, the inner surface of the rear end cover body is designed into a cylindrical surface, and the cylindrical surface can arrange the motion direction of the shock wave formed from the engine nozzle and spread towards the front end of the launching box, so that the front end cover can be opened by the shock wave.
In one embodiment of the invention, the overall structural design of the rear end cover body ensures certain strength, and the rear end cover body can not be damaged when certain pressure gas exists in the launching box and can also resist shock wave impact or gas flow scouring reflected when the missile engine in the adjacent launching box works.
In an embodiment of the present invention, the rear end cover body is formed by thermosetting resin through a mold, or is formed by machining thermosetting foam material, or is formed by sheet metal or machining non-ferrous metal plate, or is formed by compression molding high-strength fiber and thermosetting resin impregnant.
In one embodiment of the invention, the flange is formed by processing and molding metal or formed by compression molding high-strength fiber and thermosetting resin impregnant.
In one embodiment of the invention, the pressing ring is formed by machining metal or compression molding by using high-strength fiber and thermosetting resin impregnant.
In the invention, the structural size of the inner surface of the rear end cover is designed according to the size of the port of the launching box and the position of the nozzle of the missile engine, and the height of the rear end cover is designed according to the end surface of the launching box, the structure of the inner surface and the thickness of the cover body.
The invention is described in detail below with reference to the figures and specific embodiments.
Example 1
Referring to fig. 1 to 4, a sealed rear end cap of a cylindrical orthogonal type having a rectifying effect on a shock wave reflection, the rear end cap comprising: rear end lid 1, flange 2 and clamping ring 3, wherein, rear end cap and the assembly of launching box rear end face.
Referring to fig. 5, a cylindrical orthogonal type hermetic rear end cap having a rectifying effect on shock wave reflection, the inner surface of the rear end cap body is designed as an arc surface limited by two parabolas:
parabola S 1 The equation: y is 1 ＝x 2 /[4×(b+c)]-h，x∈[-a,a](ii) a Focal coordinates (0, b + c-h);
parabola S 2 The equation: y is 2 ＝x 2 /[4×(b-c)]-h，x∈[-a,a](ii) a Focal coordinates (0, b-c-h);
arc C is located by 3 points, point a', and point B, wherein: point A and point A' are in parabola S 1 And S 2 And between the intersection points of the X axis and the X axis, the point B is the top point of the inner surface of the rear end cover.
Referring to fig. 6, a cylindrical orthogonal sealed rear end cap having a rectifying effect on shock wave reflection reflects shock wave longitudinal waves finished by the rear end cap toward the front end of the launch box.
In this embodiment, flange 2 is used for fixing on the emission case rear end face, and clamping ring 3 is connected with flange 2 through the screw, paints sealed glue with flange 2 and 3 sealed faces of clamping ring, and rear end lid 1 shirt rim is placed in flange 2 sealed face, and clamping ring 3 presses on rear end lid 1 shirt rim, fastens rear end lid 1, flange 2 and clamping ring 3 through the screw.
In this embodiment, after the flange 2 is installed on the rear end face of the launch box, the sealing property of the end face is ensured by the sealing strip.
In the embodiment, the sealing performance of the skirt edge is ensured by the flange 2 and the pressure ring 3 through the sealant on the skirt edge of the rear end cover body 1, and the skirt edge of the rear end cover body 1 is assembled and fastened by the flange 2 and the pressure ring 3 through the screws; the flange 2 is provided with a groove for mounting a sealing ring.
In this embodiment, the rear end cover 1 is provided with a weak area, and when the missile engine nozzle forms shock waves to impact the rear end cover, the rear end cover 1 is broken along the weak area.
In this embodiment, the internal surface of rear end lid 1 designs into the cambered surface, and this cambered surface can be arranged the shock wave that the engine spout formed in order, and towards the propagation of launching box front end, is favorable to the front end housing to be opened by the shock wave.
In the embodiment, the integral structural design of the rear end cover body 1 ensures certain strength, and the rear end cover body can not only be damaged when certain pressure gas exists in the launching boxes, but also resist shock waves reflected by missile engines in adjacent launching boxes during working.
In the embodiment, the rear end cover body 1 is made of epoxy foaming materials and is formed by hot curing through a mold, the flange 2 is made of metal and is formed by machining, and the pressing ring 3 is made of metal and is formed by machining;
the rear end cover shown in fig. 1 comprises 1 rear end cover body 1 made of epoxy resin foaming material; comprises 1 flange 2 made of aluminum alloy (brand: 5A 06); comprises 1 compression ring 3 made of aluminum alloy (brand: 5A 06). Sealing surfaces of the flange 2 and the pressure ring 3 are coated with sealing glue, the skirt edge of the rear end cover body 1 is placed in the sealing surface of the flange 2, the pressure ring 3 is pressed on the skirt edge of the rear end cover body 1, and the rear end cover body 1, the flange 2 and the pressure ring 3 are connected and fastened through screws.
Mounting the assembled 'rear end cover' shown in figure 1 on a pressure vessel, slowly inflating the pressure vessel to make the inner surface of the rear end cover body bear pressure, and reading the internal opening strength when the rear end cover body is broken; and slowly inflating the pressure container to enable the outer surface of the rear end cover body to bear pressure until the requirement of the external pressure-bearing capacity of the rear end cover is met.
The verification test confirms that the product of the rear end cover shown in figure 1 meets the indexes of internal opening strength and external bearing capacity. When the rear cover body is opened under the internal pressure, the rear cover body is broken into large pieces and flies out; the rear end cover body is not damaged when bearing external pressure.
The embodiments described above are described to facilitate an understanding and use of the invention by those skilled in the art. It will be readily apparent to those skilled in the art that various modifications to these embodiments may be made, and the generic principles described herein may be applied to other embodiments without the use of the inventive faculty. Therefore, the present invention is not limited to the above embodiments, and those skilled in the art should make modifications and alterations without departing from the scope of the present invention.
Claims (6)
1. The cylindrical orthogonal type sealing rear end cover with the rectification effect on shock wave reflection is characterized by comprising a rear end cover body (1), a flange (2) and a pressing ring (3), wherein the flange (2) is used for being installed on the rear end face of a launching box, the pressing ring (3) is connected with the flange (2), the skirt edge of the rear end cover body (1) is placed in the sealing face of the flange (2), and the pressing ring (3) presses the skirt edge of the rear end cover body (1);
the compression ring (3) is connected with the flange (2) through a screw, and the screw fastens the rear end cover body (1), the flange (2) and the compression ring (3);
the rear end cover body (1) is provided with a weak area, and when the missile engine gas flow impacts the rear end cover body (1), the rear end cover body (1) is broken along the weak area;
the inner surface of the rear end cover body (1) is designed into a cylindrical surface, and the inner surface of the rear end cover body is designed into an arc surface limited by two parabolas;
the strength of the whole structure design of the rear end cover body (1) meets the following requirements: the gas-fired missile launcher can not be damaged when certain pressure gas exists in the launching boxes, and can resist shock wave impact and/or gas flow scouring reflected when the missile engines in the adjacent launching boxes work.
2. The cylindrical orthogonal type sealed rear end cap with the rectifying effect on the shock wave reflection according to claim 1 is characterized in that a sealing glue is coated on the sealing surface of the flange (2) and the pressure ring (3).
3. The cylindrical orthogonal type sealing rear end cover with the rectifying effect on the shock wave reflection of claim 1 is characterized in that after the flange (2) is installed on the rear end face of the launch box, the sealing performance of the end face is guaranteed by a sealing strip, a sealing ring or a sealing gasket.
4. The cylindrical orthogonal type sealed rear end cover with the rectifying effect on the shock wave reflection as claimed in claim 1, wherein the sealing performance of the skirt edge is guaranteed by the flange (2) and the compression ring (3) through a sealant on the skirt edge of the rear end cover body (1);
the skirt edge of the rear end cover body (1) is assembled and fastened by the flange (2) and the pressing ring (3) through screws.
5. The cylindrical orthogonal type rear end cover with the rectifying effect on the shock wave reflection of claim 1 is characterized in that when the flange (2) is matched with a sealing strip or a sealing ring for use, a groove for installing the sealing strip or the sealing ring is formed in the flange (2), and when the flange (2) is matched with a sealing gasket for use, the groove is not formed in the flange (2).
6. The cylindrical orthogonal type sealed rear end cover with the rectification effect on the shock wave reflection of claim 1 is characterized in that the rear end cover body (1) is formed by thermosetting resin through a mold in a thermosetting mode, or the rear end cover body (1) is formed by machining thermosetting foam materials, or the rear end cover body (1) is formed by metal plates or machining nonferrous metal plates in a metal plate mode, or the rear end cover body (1) is formed by compression molding high-strength fibers and thermosetting resin impregnant in a compression molding mode; and/or the presence of a gas in the gas,
the flange (2) is formed by processing metal, or the flange (2) is formed by compression molding high-strength fiber and thermosetting resin impregnating compound; and/or the presence of a gas in the gas,
the compression ring (3) is formed by processing metal, or the compression ring (3) is formed by compression molding high-strength fiber and thermosetting resin impregnating material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110187113.7A CN112985174B (en) | 2021-02-10 | 2021-02-10 | Cylindrical orthogonal type sealing rear end cover with rectification effect on shock wave reflection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110187113.7A CN112985174B (en) | 2021-02-10 | 2021-02-10 | Cylindrical orthogonal type sealing rear end cover with rectification effect on shock wave reflection |
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| CN112985174A CN112985174A (en) | 2021-06-18 |
| CN112985174B true CN112985174B (en) | 2023-01-10 |
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| CN202110187113.7A Active CN112985174B (en) | 2021-02-10 | 2021-02-10 | Cylindrical orthogonal type sealing rear end cover with rectification effect on shock wave reflection |
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