CN215952369U - Folding rudder wing dustproof device - Google Patents
Folding rudder wing dustproof device Download PDFInfo
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- CN215952369U CN215952369U CN202122347846.0U CN202122347846U CN215952369U CN 215952369 U CN215952369 U CN 215952369U CN 202122347846 U CN202122347846 U CN 202122347846U CN 215952369 U CN215952369 U CN 215952369U
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- rudder
- elastic clamping
- clamping strip
- piston
- dustproof
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Abstract
The utility model discloses a folding rudder wing dustproof device, wherein a conical rudder cabin is arranged at the head of a projectile body, two groups of rudder wings capable of being radially expanded are arranged in the rudder cabin, and two rudder wing grooves for the rudder wings to expand outwards from the inside are formed in the rudder cabin; the anti-dust plug is matched with the rudder wing groove; the outer surface of the rudder cabin is provided with a circumferential annular groove, an elastic clamping strip is arranged in the annular groove, connecting rings are arranged at two ends of the elastic clamping strip, through holes matched with the cross sections of the elastic clamping strip are formed in the dustproof plugs, the elastic clamping strip penetrates through the through holes of the two dustproof plugs, and the connecting rings at two ends of the elastic clamping strip are connected in series through connecting pins; the rudder engine room is provided with a pin puller. According to the technical scheme, the pin puller is started to release the elastic clamping strip and simultaneously drive the dustproof plug to be separated from the rudder cabin, so that the problem of influence of environmental factors in the stage from the projectile body entering the launcher to the rudder wing unfolding is effectively solved, and the device has the advantages of being simple in structure and high in reliability.
Description
Technical Field
The utility model relates to the field of projectile body protection devices, in particular to a folding rudder wing dustproof device.
Background
The rudder wing unfolding mechanism of the projectile body is developed under the requirement that the projectile body is sought to be miniaturized, and the rudder wing unfolding mechanism is simple in structure, small in occupied space, capable of saving storage space and convenient to store, transport and launch. During storage, transportation and launching, the rudder wing is folded inside the projectile body; when the projectile flies into the air, the rudder wings are unfolded to adjust the motion attitude of the projectile through the rotation of the rudder wings.
The rudder wing unfolding mechanism has the problems of dust, rain, snow or rocket residues launched by a plurality of bullets in the storage, transportation and launching processes, the problems can influence the unfolding reliability of the rudder wing, and in the protection aspect of the unfolding rudder wing unfolding mechanism, a plurality of modes such as oil seal paper wrapping, taking down before launching and the like are adopted, and the modes can not play a good protection role when a missile body enters a launching box.
Therefore, how to design a safe and reliable dustproof device for the folded rudder wing is a technical problem which needs to be solved by the technical personnel in the field at present.
Disclosure of Invention
In order to solve the technical problems, the utility model mainly aims to provide a folding rudder wing dustproof device to solve the problem that the rudder wing groove is blocked by dust, wind and sand and jet residues of a projectile body before the rudder wing is unfolded.
In order to achieve the above object, the present invention adopts the following technical solutions.
A folding rudder wing dustproof device is arranged on a conical rudder cabin, two groups of rudder wings capable of being radially unfolded are arranged in the rudder cabin, and two rudder wing grooves for the rudder wings to be unfolded from the inside to the outside are formed in the rudder cabin; the anti-dust plug is matched with the rudder wing groove; the outer surface of the rudder cabin is provided with a circumferential annular groove, an elastic clamping strip is arranged in the annular groove, connecting rings are arranged at two ends of the elastic clamping strip, through holes matched with the cross section of the elastic clamping strip are formed in the dustproof plugs, the elastic clamping strip penetrates through the through holes of the two dustproof plugs, and the connecting rings at two ends of the elastic clamping strip are connected in series through connecting pins; and a pin puller is arranged on the rudder cabin and used for pulling the connecting pin out of the two connecting rings.
Furthermore, the material of the dustproof plug is polytetrafluoroethylene.
Furthermore, the elastic clamping strip is made of spring steel.
Furthermore, the pin puller is an electromagnet, and the connecting pin is made of a ferromagnetic material.
Furthermore, the pin puller is a gunpowder pin puller, the gunpowder pin puller comprises a cylinder barrel, a piston is arranged in the cylinder barrel, a piston rear area is arranged between the piston and the bottom end of the cylinder barrel, a piston front area is arranged between the piston and the front end of the cylinder barrel, a piston rod extending out of the cylinder barrel is arranged on one side of the piston close to the piston front area, gunpowder is filled in the piston front area, and an igniter in contact with the gunpowder is arranged on the cylinder barrel; the piston rod is connected with the tail part of the connecting pin.
Compared with the prior art, the technical scheme of the utility model has the advantages that the elastic clamping strip is released and the dustproof plug is driven to be separated from the rudder cabin by starting the pin puller, so that the problem of influence of environmental factors in the stage from the projectile body entering the launching rack to the rudder wing unfolding is effectively solved, and the device has a simple structure and high reliability.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic perspective view of a folded rudder wing dust-proof device installed on a rudder cabin;
FIG. 2 is a perspective view of the rudder nacelle;
FIG. 3 is a perspective view of the dust plug;
FIG. 4 is an expanded view of the elastic clip strip;
FIG. 5 is a longitudinal section of the folded rudder wing dust keeper passing pin puller;
fig. 6 is a partially enlarged view of a portion a in fig. 5.
In the above figures:
1, a rudder engine room; 101 rudder wing groove; 102 an annular groove; 2, a dust plug; 3, elastic clamping strips; 301 connecting rings; 4 connecting pins; 5, a pin puller; 501 cylinder barrel; 502 a piston; 503 a piston rod; 504 gunpowder; 505 igniter.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
In the following description, specific details are set forth in order to provide a thorough understanding of the present invention. The utility model can be implemented in a number of ways different from those described herein and similar generalizations can be made by those skilled in the art without departing from the spirit of the utility model. Therefore, the present invention is not limited to the specific embodiments disclosed below.
The rudder wing unfolding mechanism is developed under the requirement that the projectile body is sought to be miniaturized, has a simple structure and small occupied space, can save storage space, and is convenient to store, transport and launch. During storage, transportation and launching, the rudder wing is folded inside the projectile body; when the projectile flies into the air, the rudder wings are unfolded to adjust the motion attitude of the projectile through the rotation of the rudder wings.
The rudder wing unfolding mechanism has the problems of dust, rain, snow or rocket residues launched by a plurality of bullets in the storage, transportation and launching processes, the problems can influence the unfolding reliability of the rudder wing, and in the protection aspect of the unfolding rudder wing unfolding mechanism, a plurality of modes such as oil seal paper wrapping, taking down before launching and the like are adopted, and the modes can not play a good protection role when a missile body enters a launching box.
The utility model provides a folding rudder wing dustproof device, which ensures that objects such as sand blown by wind, rain, snow, jet residues and the like do not influence the unfolding reliability of a rudder wing before the missile rudder wing is unfolded.
Referring to fig. 1 and 2, a folding rudder wing dustproof device is arranged on a conical rudder nacelle 1, two sets of rudder wings capable of being radially expanded are arranged in the rudder nacelle 1, and two rudder wing grooves 101 for the rudder wings to expand from the inside to the outside are arranged on the rudder nacelle 1;
please refer to fig. 3 and 4, further comprising a dust plug 2 matching with the rudder wing slot 101; the outer surface of the rudder cabin 1 is provided with a circumferential annular groove 102, an elastic clamping strip 3 is arranged in the annular groove 102, two ends of the elastic clamping strip 3 are provided with connecting rings 301, the dustproof plug 2 is provided with through holes 201 matched with the cross section of the elastic clamping strip 3, the elastic clamping strip 3 penetrates through the through holes 201 of the two dustproof plugs 2, and the connecting rings 301 at two ends of the elastic clamping strip 3 are connected in series through connecting pins 4; the rudder nacelle 1 is provided with a pin puller 5, and the pin puller 5 is used for pulling the connecting pin 4 out of the two connecting rings 301.
In the above embodiment, after the projectile is launched, the rudder wing does not immediately unfold but unfolds after a period of flight, referring to fig. 5 and 6, in this embodiment, the rudder wing slot 101 is plugged by the dust plug 2 in the strip-shaped groove, the dust plug 2 is in interference fit with the rudder wing slot 101, so as to prevent dust from entering, after the projectile receives a rudder wing unfolding command, the pin puller 5 is started to pull out the connecting pins 4 connected in series with the two ends of the elastic clamping strip 3, and the elastic clamping strip 3 unfolds under the self restoring force to pull out the dust plug 2 plugged in the rudder wing slot 101.
Furthermore, the material of the dust plug 2 is polytetrafluoroethylene.
Furthermore, the elastic clamping strip 3 is made of spring steel.
In the above embodiment, in order to prevent the dust plug 2 from melting during the heating process of the elastomer, the dust plug 2 is preferably made of high temperature resistant polytetrafluoroethylene; in order to ensure that the dust plug 2 can be pulled out after the projectile body receives the rudder wing unfolding instruction, the elastic clamping strip 3 is preferably made of spring steel with good elasticity.
Further, the pin puller 5 is an electromagnet, and the connecting pin 4 is made of a ferromagnetic material.
In the above embodiment, the pin remover 5 may be an electromagnet, and after receiving the rudder wing unfolding instruction, the projectile pulls out the connecting pin 4 made of ferromagnetic material through the action of the electromagnet.
Further, the pin puller 5 is a gunpowder pin puller 5, the gunpowder pin puller 5 comprises a cylinder 501, a piston 502 is arranged in the cylinder 501, a piston rear area is arranged between the piston 502 and the bottom end of the cylinder 501, a piston front area is arranged between the piston 502 and the front end of the cylinder 501, a piston rod 503 extending out of the cylinder 501 is arranged on one side of the piston 502 close to the piston front area, the piston front area is filled with gunpowder 504, and an igniter 505 contacting with the gunpowder 504 is arranged on the cylinder 501; the piston rod 503 is connected to the tail of the connecting pin 4.
In the above embodiment, the pin remover 5 is another embodiment, and the powder pin remover 5 is selected in consideration of the higher temperature of the projectile body during the shooting process. The igniter can be an electronic igniter, when the projectile body receives a rudder wing unfolding instruction, the igniter 505 is ignited, gunpowder 504 in the front area of the piston is ignited, the gunpowder 504 is rapidly combusted in a closed space to generate a large amount of gas, the piston 502 is pushed to the rear area of the piston, the piston 502 moves to drive the piston rod 503 to retract, the piston rod 503 drives the connecting pin 4 connected with the piston rod to be pulled out from the connecting ring 301 of the elastic clamping strip 3, and the two dustproof plugs 2 are pulled out from the rudder wing groove 101 by the elastic clamping strip 3 in the unfolding process. The igniter can also be other types of igniters as long as the igniter can receive instructions to detonate the gunpowder.
According to the technical scheme, the pin puller is started to release the elastic clamping strip and simultaneously drive the dustproof plug to be separated from the rudder cabin, so that the problem of influence of environmental factors in the stage from the projectile body entering the launcher to the rudder wing unfolding is effectively solved, and the device has the advantages of being simple in structure and high in reliability.
Although the present invention has been described in detail in this specification with reference to specific embodiments and illustrative embodiments, it will be apparent to those skilled in the art that modifications and improvements can be made thereto based on the present invention. Accordingly, such modifications and improvements are intended to be within the scope of this invention as claimed.
Claims (5)
1. A folding rudder wing dustproof device is arranged on a conical rudder cabin (1), and is characterized in that two groups of rudder wings capable of being radially unfolded are arranged in the rudder cabin (1), and two rudder wing grooves (101) for the rudder wings to be unfolded from the inside to the outside are formed in the rudder cabin (1); the rudder wing groove (101) is matched with the dustproof plug (2); the outer surface of the rudder cabin (1) is provided with a circumferential annular groove (102), an elastic clamping strip (3) is arranged in the annular groove (102), connecting rings (301) are arranged at two ends of the elastic clamping strip (3), a through hole (201) matched with the cross section of the elastic clamping strip (3) is formed in the dustproof plug (2), the elastic clamping strip (3) penetrates through the through holes (201) of the two dustproof plugs (2), and the connecting rings (301) at two ends of the elastic clamping strip (3) are connected in series through connecting pins (4); the rudder engine room (1) is provided with a pin puller (5), and the pin puller (5) is used for pulling the connecting pin (4) out of the two connecting rings (301).
2. The folded rudder wing dustproof device according to claim 1, wherein the dustproof plug (2) is made of polytetrafluoroethylene.
3. The folded rudder wing dustproof device according to claim 1, wherein the elastic clamping strip (3) is made of spring steel.
4. The folded rudder wing dustproof device according to claim 1, wherein the pin puller (5) is an electromagnet, the connecting pin (4) is made of ferromagnetic material, and the electromagnet is located right above the connecting pin (4).
5. The folding rudder wing dustproof device according to claim 1, wherein the pin remover (5) is a gunpowder pin remover (5), the gunpowder pin remover (5) comprises a cylinder (501), a piston (502) is arranged in the cylinder (501), a piston rear area is arranged between the piston (502) and the bottom end of the cylinder (501), a piston front area is arranged between the piston (502) and the front end of the cylinder (501), a piston rod (503) extending out of the cylinder (501) is arranged on one side of the piston (502) close to the piston front area, gunpowder (504) is filled in the piston front area, and an igniter (505) in contact with the gunpowder (504) is arranged on the cylinder (501); the piston rod (503) is connected with the tail part of the connecting pin (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122347846.0U CN215952369U (en) | 2021-09-27 | 2021-09-27 | Folding rudder wing dustproof device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122347846.0U CN215952369U (en) | 2021-09-27 | 2021-09-27 | Folding rudder wing dustproof device |
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| CN215952369U true CN215952369U (en) | 2022-03-04 |
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| CN202122347846.0U Active CN215952369U (en) | 2021-09-27 | 2021-09-27 | Folding rudder wing dustproof device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115183634A (en) * | 2022-08-01 | 2022-10-14 | 湖北航天飞行器研究所 | Folding wing guided missile projectile body dimension shape device and guided missile projectile body |
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2021
- 2021-09-27 CN CN202122347846.0U patent/CN215952369U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115183634A (en) * | 2022-08-01 | 2022-10-14 | 湖北航天飞行器研究所 | Folding wing guided missile projectile body dimension shape device and guided missile projectile body |
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