KR101405261B1 - Launching tube having function for preventing flame from flowing backward - Google Patents

Launching tube having function for preventing flame from flowing backward Download PDF

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Publication number
KR101405261B1
KR101405261B1 KR1020140021440A KR20140021440A KR101405261B1 KR 101405261 B1 KR101405261 B1 KR 101405261B1 KR 1020140021440 A KR1020140021440 A KR 1020140021440A KR 20140021440 A KR20140021440 A KR 20140021440A KR 101405261 B1 KR101405261 B1 KR 101405261B1
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KR
South Korea
Prior art keywords
projectile
flame
tube
sectional area
cross
Prior art date
Application number
KR1020140021440A
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Korean (ko)
Inventor
양영록
신재철
김경태
임범수
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국방과학연구소
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Priority to KR1020140021440A priority Critical patent/KR101405261B1/en
Application granted granted Critical
Publication of KR101405261B1 publication Critical patent/KR101405261B1/en

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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
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/0413—Means for exhaust gas disposal, e.g. exhaust deflectors, gas evacuation systems
    • 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
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/052—Means for securing the rocket in the launching apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Building Environments (AREA)

Abstract

The present invention relates to a flame backflow prevention tube for preventing a backflow of a flame injected from the projectile to a projectile at the moment the projectile is fired.
The flame counterflow prevention tube according to the present invention is formed in a cylindrical shape and is equipped with a projectile 1 therein and the flame discharged from the projectile 1 is discharged to the rear end The flame backflow reduction portion 30 is formed at a position where the rear end of the projectile 1 is located at a position larger than the other portion of the cross sectional area of the projectile, (10), an outer bulb (10), an inner bulb (10), and an inner bulb (11), which are disposed adjacent to the outer circumferential surface of the projectile (1) with a predetermined gap therebetween, (20).

Description

{LAUNCHING TUBE HAVING FUNCTION FOR PREVENTING FLAME FROM FLOWING BACKWARD}

BACKGROUND OF THE INVENTION 1. Field of the Invention [0002] The present invention relates to a launch tube for emitting a projectile, and more particularly, to a flame backflow prevention tube capable of preventing a flame injected from the projectile from flowing back to a projectile at the moment the projectile is fired.

A missile or a rocket is propelled by propelling force generated by the high pressure gas generated by burning the fuel in the propelling body of the projectile to the rear of the projectile.

On the other hand, the projectile is fired inside the tube when the projectile is loaded inside the tube.

A large amount of flame is discharged from the rear end of the projectile at the moment when the projectile is fired. The flame tube must smoothly discharge the flame to the outside.

However, as shown in FIG. 1, the conventional launching tube 100 fixes the projectile 1 with a weight, and the flame F discharged from the projectile 1 when the projectile 1 is abnormal is launched from the projectile 1 1), the area of the discharge port 101 of the launch tube 100 is narrowed.

However, since the cross-sectional area of the discharge port 101 of the launch pipe 100 is narrower than the cross-sectional area of the discharge pipe 100 as described above, the flame discharged from the projectile 1 is not discharged to the outside through the discharge port 101 1 and 2, there arises a case that the air flows back to the projectile 1 as shown in Fig.

When the flame flows back into the projectile 1 within the tube 100, the projectile 1 receives a thermal load. Therefore, a separate thermal protection design is required to prevent damage caused by the flame.

Therefore, the design of the projectile 1 is limited, and the cost required for the thermal protection design is added.

The following prior art documents relate to a missile launcher cell having an exhaust gas duct and an arrangement of the missile launcher cells. The missile launcher cell has a separate duct for discharging the exhaust gas emitted from the missile. Is disclosed.

KR 10-0925254 B1

SUMMARY OF THE INVENTION The present invention has been made in order to solve the above-mentioned problems, and it is an object of the present invention to provide a flame backflow prevention ventilation tube having a flame backflow reduction part for preventing backward flow of a flame sprayed from a projectile from a projectile, And the like.

According to an aspect of the present invention, there is provided a flame backflow prevention tube for a flame, the flame backflow prevention tube being formed in a cylindrical shape and having a projectile mounted therein, and a flame emitted from the projectile, And a flame backflow reduction portion formed in a portion of the tail pipe discharged through the formed discharge port at a position where the rear end of the projectile is located is formed to have a larger internal cross sectional area than the other portion.

The bullet tube is connected to an outside bullet tube and an internal bullet tube disposed inside the outside bullet tube and adjacent to the outer circumferential surface of the projectile with a predetermined gap and the lower end thereof connected to the flame backflow reduction unit .

Sectional area of the flame backflow reduction portion is formed to be larger than a cross-sectional area of the internal heat pipe.

And the cross-sectional area of the flame backflow reduction portion is formed to be equal to the cross-sectional area of the external launch tube.

Wherein the cross-sectional area of the discharge port is formed to be the same as the cross-sectional area of the projectile or the cross-sectional area of the internal blower tube.

The shape and height of the flame backflow reduction portion are determined according to the intensity of the flame emitted from the projectile.

According to the flame counterflow prevention tube of the present invention having the above-described structure, it is possible to prevent flame sprayed from the projectile from flowing backward, thereby preventing additional heat from being added to the projectile to avoid heat load due to the flame Thermal protection design becomes unnecessary.

As described above, since additional thermal protection design for the projectile is not required, the degree of freedom in designing the projectile is improved, and the cost for manufacturing the projectile and the launch tube is reduced.

1 is a cross-sectional view showing a state in which a flame backflow occurs at the moment when a projectile is fired from a launching tube according to a related art.
FIG. 2 is a schematic view showing flame backflow at the rear of the projectile at the moment when the projectile is launched from the launch pipe according to the prior art; FIG.
3 is a sectional view showing a flame backflow prevention tube according to the present invention;
4 is a cross-sectional view showing a state in which flame is reduced at the moment when a projectile is fired in a flame backflow prevention tube according to the present invention.
FIG. 5 is a graph showing a speed distribution at the tail end of a projectile at the moment when a projectile is fired in a flame backflow prevention tube according to the present invention. FIG.
6 is a graph showing the velocity distribution when the projectile is adjacent to the outlet of the launch tube in the flame backflow prevention tube according to the present invention.
7 is a graph showing the flame backflow amount in the launch tube of the present invention and the prior art.
8 is a cross-sectional view showing an example of an internal heat pipe in a flame backflow preventing duct according to the present invention.

Hereinafter, a flame backflow prevention tube according to the present invention will be described in detail with reference to the accompanying drawings.

The flame counterflow prevention tube according to the present invention includes an outer tube 10, an inner tube 20 installed inside the outer tube 10, and a cross-sectional area of the inner tube 20 below the inner tube 20, A flame backflow reduction portion 30 having a larger cross sectional area is formed.

The outer bullet tube 10 forms the outer shape of the flame backflow prevention bulb according to the present invention.

The inner bullet tube 20 is positioned inside the outer bullet tube 10 and the inner side surface of the inner bullet tube 20 is formed adjacent to the outer circumferential surface of the projectile 1 with a predetermined gap. A space between the inner bullet tube 20 and the projectile 1 is substantially not present so that the flame injected from the rear end of the projectile 1 is separated from the space between the inner bullet tube 20 and the projectile 1 To prevent backflow.

The cross-sectional shape of the inner bullet tube 20 may be formed corresponding to the shape of the projectile 1, as shown in FIG.

The flame backflow reduction section (30) is formed such that the inner cross sectional area of the inside of the flame backflow prevention duct is larger than the other part adjacent to the outside of the projectile (1).

The flame backflow reduction portion 30 is formed to be connected to a lower portion of the internal bulb tube 20 and has a cross sectional area larger than that of the internal bulb tube 20. The cross-sectional area of the flame backflow reduction portion 30 is preferably the same as the cross-sectional area of the outer bulb 10.

The flame backflow reduction part 30 forms a portion having a large cross-sectional area temporarily in the inside of the flame backflow prevention flue pipe so that the flame injected from the projectile 1 flows into the flame backflow reduction part 30 , The flame backflow reduction portion 30 is formed as a space in which the flame F can temporarily stay.

The flame backflow reduction portion 30 is formed to have the flame backflow reduction portion 30 so as to have the same cross sectional area as that of the external flame tube 10 so that the flame backflow prevention flame tube appears to be formed into a single cylindrical structure.

The shape and height of the flame backflow reduction portion 30 can be determined according to the intensity of the flame emitted from the projectile 1. [ That is, the shape of the flame backflow reduction portion 30 is determined according to the strength type of the flame emitted from the projectile 1.

The discharge port 11 is formed next to the flame backflow reduction section 30 to form the rear end in the entire discharge pipe. The discharge port 11 may preferably be formed to have the same cross-sectional area as that of the inner bullet tube 20 or the projectile 1. The flame F injected from the projectile 1 through the discharge port 11 is finally discharged to the outside. The cross-sectional area of the discharge port 11 may be the same as the cross-sectional area of the inner bullet tube 20 or the cross-sectional area of the projectile 1.

Hereinafter, the operation of the flame backflow prevention tube according to the present invention will be described.

The flame F is injected from the rear end of the projectile 1 when fuel starts to be burned from the projectile 1 so that the projectile 1 is fired inside the tube.

The flame F is ejected from the projectile 1 and then discharged to the outside through the discharge port 11 so that the projectile 1 obtains a propulsion force.

At this time, since the gap between the projectile 1 and the inner bullet tube 20 is not substantially present, the flame F can not flow backward between the outer circumferential surface of the projectile 1 and the inner surface of the bullet tube.

The flame F injected from the projectile 1 flows into the flame backflow reduction section 30 and then flows into the flame backflow reduction section 30 so that the flame F does not flow back toward the projectile 1. 3 to 5, the flame backflow reduction unit 30 is formed to have a diameter larger than that of the portion where the projectile 1 is located, and the flame F flowing into the flame backflow reduction unit 30, And does not flow back toward the projectile 1 while it is revolving inside.

Therefore, the flame F injected from the projectile 1 is discharged back to the discharge port 11 through the flame backflow reduction portion 30 without flowing backward.

FIG. 7 is a graph illustrating a comparison of the flame backflow amount according to the present invention and the related art. However,

The flame backflow prevention tube according to the present invention has almost no flame backflow after the launch of the projectile 1 in the conventional launch tube 100, Able to know.

Therefore, according to the conventional anti-wadding flushing tube of the present invention, since there is substantially no back fl ow flame, the tropical fl ow of the back fl ow is not necessary .

1: Projectile 10: Outside Launcher
11: discharge port 20: internal bulb
30: Flame backflow reduction part 100:
101: Outlet F: Flame

Claims (6)

1. A tubular tube which is formed in a cylindrical shape and into which a projectile is loaded and in which a flame discharged from the projectile is discharged through a discharge port formed at a rear end of the projectile,
A flame backflow reduction portion is formed at a position where the rear end of the projectile is located,
The launch tube may include:
An external launcher,
Wherein the flame backflow prevention tube is disposed inside the outer flue tube and adjacent to the outer circumferential surface of the projectile at a predetermined interval and the lower end thereof is connected to the flame backflow reduction section.
delete The method according to claim 1,
Wherein the cross-sectional area of the flame backflow reduction portion is larger than the cross-sectional area of the internal blower.
The method according to claim 1,
Wherein the cross-sectional area of the flame backflow reduction portion is formed to be equal to the cross-sectional area of the outer flame tube.
The method according to claim 1,
Wherein the cross-sectional area of the discharge port is formed to be the same as the cross-sectional area of the projectile or the cross-sectional area of the inner tube.
The method according to claim 1,
Wherein the shape and height of the flame backflow reduction portion are determined according to the intensity of the flame emitted from the projectile.
KR1020140021440A 2014-02-24 2014-02-24 Launching tube having function for preventing flame from flowing backward KR101405261B1 (en)

Priority Applications (1)

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KR1020140021440A KR101405261B1 (en) 2014-02-24 2014-02-24 Launching tube having function for preventing flame from flowing backward

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KR1020140021440A KR101405261B1 (en) 2014-02-24 2014-02-24 Launching tube having function for preventing flame from flowing backward

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20160020306A (en) 2014-08-13 2016-02-23 국방과학연구소 Apparatus for preventing back flow of flame of the hot-launch missile

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4324167A (en) * 1980-04-14 1982-04-13 General Dynamics, Pomona Division Flexible area launch tube rear cover
US5012718A (en) * 1988-10-27 1991-05-07 British Aerospace Public Limited Company Impingement pressure regulator

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4324167A (en) * 1980-04-14 1982-04-13 General Dynamics, Pomona Division Flexible area launch tube rear cover
US5012718A (en) * 1988-10-27 1991-05-07 British Aerospace Public Limited Company Impingement pressure regulator

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20160020306A (en) 2014-08-13 2016-02-23 국방과학연구소 Apparatus for preventing back flow of flame of the hot-launch missile

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