JPH09105597A - Shooter for projectile - Google Patents

Abstract

PROBLEM TO BE SOLVED: To obtain an effectively and safely functioning projectile and a shooting tube without requiring a special countermeasure for corrosion by supplying purge gas to the shooting tube through a nozzle from a purge gas supply system, during confined combustion of the projectile. SOLUTION: Air is compressed by a compressor 9 and stored in a purge gas storage tank 7. The air from the purge gas storage tank 7 selects a shooting tube 2 in which the confined combustion of a projectile 1 is generated among a plurality of shooting tubes 2, is branched by a purge gas distributor 5 and supplied to the selected shooting tube 2 through a purge gas supply tube 6. The purge gas is divided into two flows by a purge gas regulating valve 4 just before the shooting tube 2 and discharged into the shooting tube 2 from two counter nozzles 3. The purge gas discharged into the shooting tube 2 flows downward in the shooting tube 2 toward a shooter plenum 16. Thus, the entry of high temperature combustion gas burst from the projectile 1 to the shooting tube 2 is prevented and the equipments of the projectile 1 are protected from the high temperature combustion gas.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

TECHNICAL FIELD The present invention relates to a launching device for launching a projectile.

[0002]

2. Description of the Related Art A conventional projectile launching device will be described with reference to FIG.

The projectile 01 is housed in a launch tube 02 attached to a launcher plenum 016. The flying body 01 has a structure in which the flow rate of seawater sent from a seawater pump is adjusted by an adjusting valve 04, and the seawater is jetted from a spray nozzle 03 and cooled.

In such a structure, the propellant burns while propellant burns while the propellant 01 is restrained in the launch tube 02 for some reason, despite the fact that the propellant 01 is now fired. In this case, in order to protect the electronic control equipment, the crater product, the propellant, etc., which is the heart of the flying object 01, from the high temperature gas that enters the launch tube 02, seawater is pumped inside the launch tube 02 by the pump 09. To the surface of the flying object by the spray nozzle 03 to cool the flying object 01.

[0005]

SUMMARY OF THE INVENTION In the above-mentioned conventional apparatus, the seawater supply system and the flying body are provided by supplying seawater as cooling water into the flying body launching apparatus when an abnormality such as restraint combustion occurs. In 01, the launching cylinder 02, the drainage system of seawater, etc., the corrosion of the equipment occurs due to the salt content of seawater. For this reason, there is a problem that countermeasures against equipment corrosion are required.

An object of the present invention is to solve the above-mentioned problems in the prior art and to obtain a product that functions effectively and safely without the need for special measures against corrosion.

[0007]

The present invention has been made to solve the above problems, and a purge gas supply system is provided outside a launch tube of a projectile, and the purge gas supply system is provided at a side portion of the launch tube. Provided is a projectile launching device which is provided with a nozzle for receiving a purge gas from the jet nozzle and ejecting the jet gas into the launch barrel so as to supply the purge gas into the launch barrel when the projectile is restrained and burned. The purged gas prevents the high-temperature combustion gas generated by restraint combustion from entering the launch tube or is expelled from the launch tube, and the electronic control device for the projectile in the launch tube, the crater, and the propellant. And the like from high temperature combustion gas.

Further, according to the present invention, the purge gas supply system is constructed by providing an air compressor, a storage tank and a distributor, and the nozzle is provided with an adjusting valve so as to be mounted on the upper part of the launch cylinder for launching a projectile. By using compressed air as the purge gas, the purge gas is injected from the upper part of the firing cylinder into the firing cylinder to protect the inside of the firing cylinder from high temperature combustion gas.

Further, in the present invention, the purge gas supply system is constructed by providing an air compressor, a storage tank, a cooling device, and a distribution device, and the nozzle is provided with an adjusting valve in the vicinity of the combustion gas ejection portion of the projectile. Providing a projectile launcher attached to the lower part of the corresponding launch tube, using cooled compressed air as purge gas, the above-mentioned purge gas from the bottom of the launch tube corresponding to the vicinity of the combustion gas jet part of the projectile into the launch tube. Is injected to protect the interior of the launch tube from high-temperature combustion gas.

Further, in the present invention, the purge gas supply system comprises a liquid nitrogen tank, a flow rate controller, a carburetor, a temperature controller and a distributor, and the nozzle is provided with a regulator valve to burn a flying object. Provide a projectile launching device attached to the lower part of the launch tube corresponding to the vicinity of the gas jetting part, adopt low-temperature nitrogen gas as purge gas, and launch this at a position corresponding to the vicinity of the combustion gas jetting part of the projectile It is designed to be injected from the lower part into the launch tube to protect the launch tube from high temperature combustion gas.

[0011]

BEST MODE FOR CARRYING OUT THE INVENTION A first embodiment of the present invention will be described with reference to FIG.

The projectile 1 is housed in each of a plurality of launch barrels 2 attached to a launcher plenum 16. A nozzle 3 for blowing air into the launch tube 2 is provided on the top of the launch tube 2.
Is attached.

A purge gas supply system 10 including a compressor 9, a purge gas storage tank 7 and a purge gas distribution device 5 for supplying air to the nozzle 3 and a purge gas adjusting valve 4 immediately downstream of the nozzle 3 in the subsequent flow are installed. Has been done.

With such a structure, when the projectile 1 is restrained and burned, the nozzle 3 provided on the upper portion of the launch tube 2 is now in operation.
To send air into the firing tube 2 so that the high-temperature combustion gas that tries to enter the firing tube 2 is pushed into the plenum 16 of the firing apparatus.

That is, the atmosphere is compressed by the compressor 9 and stored in the purge gas storage tank 7, and the flying body 1
At the time of the restricted combustion, the air is sent from the purge gas storage tank 7 into the firing cylinder 2. However, the air from the purge gas storage tank 7 is subjected to the restricted combustion from the plurality of firing cylinders 2 by the purge gas distribution device 5. The selected firing cylinder 2 is selected and branched, and goes to the selected firing cylinder 2 through the purge gas supply pipe 6.

Immediately before the firing cylinder 2, the purge gas regulating valve 4 divides the flow into two flows, and the two flows are discharged from the opposing left and right nozzles 3 into the firing cylinder 2. Although two nozzles 3 are provided so as to be opposed to each other on the left and right sides here, it goes without saying that three or more nozzles 3 may be provided.

The purge gas thus discharged into the launch tube 2 flows downward in the launch tube 2 toward the launcher plenum 16 and the high temperature combustion gas ejected from the projectile 1 enters the launch tube 2. It prevents entry and safely protects electronic control devices (not shown), craters, propellants, etc., installed on the flying vehicle 1 from high-temperature combustion gas. The purge gas is discharged from the launcher plenum 16 through the flue 17 to the atmosphere together with the high temperature combustion gas.

Next, a second embodiment of the present invention will be described with reference to FIG. In the present embodiment, at the time of restraint combustion of the projectile 1, low-temperature air is sent to the vicinity of the high-temperature combustion gas jet portion of the projectile 1 in the launch tube 2, and the high-temperature combustion gas entering the launch tube is mixed. It is designed to be cooled.

The structural difference from the above-described first embodiment is that in this embodiment, the purge gas cooling device 8 is installed between the purge gas storage tank 7 and the purge gas distribution device 5, and the firing is performed. That is, the mounting portion of the nozzle 3 that discharges the purge gas to the cylinder 2 is in the vicinity of the high temperature combustion gas ejection portion of the projectile 1.

Therefore, in this embodiment, the atmosphere is compressed by the compressor 9
Is compressed and stored in the purge gas storage tank 7, and when the air is sent from the purge gas storage tank 7 into the firing cylinder 2 during the restrained combustion of the projectile 1, between the purge gas storage tank 7 and the purge gas distributor 5. Air is cooled by the provided purge gas cooling device 8 and is supplied into the firing cylinder 2. Other configurations and effects are similar to those of the above-described first embodiment, and therefore common parts are not included. Common reference numerals are given in the drawings, and redundant description will be omitted.

Furthermore, regarding the third embodiment of the present invention,
This will be described with reference to FIG. In the present embodiment, the low temperature air is supplied as the purge gas in the above-described second embodiment, whereas the low temperature air is supplied instead of the low temperature air to the firing cylinder 2 during the restrained combustion. The purge gas supply system 10 includes a liquid nitrogen tank 11, a flow rate controller 12, a purge gas temperature controller 14, a vaporizer 13, and a purge gas distributor 5.

The equipment is more complicated and more expensive than those of the first and second embodiments described above, but since the equipment related to liquid nitrogen has a wide range of applications, it is installed for other purposes. In such a case, it is possible to obtain the entire equipment at low cost by using the same function or diverting it.

The other constructions of this embodiment, the means for supplying low-temperature nitrogen gas to the firing cylinder 2 for the occurrence of restrained combustion, and the function and effect thereof are substantially the same as those of the second embodiment. Therefore, common parts are denoted by common reference numerals, and redundant description will be omitted.

The low temperature nitrogen gas used in the present embodiment and the low temperature air used in the second embodiment are well known, and these media are used in the first embodiment. Replacing with compressed air can be easily performed.

Although the present invention has been described above with reference to the illustrated embodiments, the present invention is not limited to such embodiments.
It goes without saying that various modifications may be made to the specific structure within the scope of the present invention.

[0026]

As described above, according to the inventions of claims 1 and 2 of the present application, in the flying object and its launching device,
Since seawater is not injected at the time of restrained combustion, there are no problems such as corrosion and rust caused by the seawater injection, and there is no need to use an expensive corrosion resistant material.

In the case of restrained combustion, the heart of the flying object can be completely protected from the hot combustion gas, and the protective equipment therefor can be simplified.

According to the invention of claim 3, in addition to the above matters, at the time of restrained combustion, the cooling air is injected from a place near the high temperature combustion gas injection part, so that the high temperature part is cooled. The effect is great, and the cooling effect of the whole is also great.

Further, according to the invention of claim 4, in addition to the above matters, by using liquid nitrogen as the purge gas used at the time of restrained combustion, the diffusion preventing effect of the high temperature combustion gas is further enhanced, and particularly for other applications. In the case where liquid nitrogen is used, the facility cost of the entire cooling system can be greatly reduced by diverting or diverting it.

[Brief description of the drawings]

FIG. 1 is an explanatory view related to a first embodiment of the present invention, in which (a) is a plane thereof and (b) is a side view thereof.

FIG. 2 is an explanatory view related to a second embodiment of the present invention, in which (a) is its plane and (b) is a side view.

FIG. 3 is an explanatory diagram related to a third embodiment of the present invention, in which (a) is a plan view thereof and (b) is a side view thereof.

FIG. 4 is an explanatory view showing a conventional one, in which (a) is its plane and (b) is a side view.

[Explanation of symbols]

 1 Flying Body 2 Firing Cylinder 3 Nozzle 4 Adjusting Valve 5 Distributor 7 Storage Tank 8 Cooling Device 9 Air Compressor 11 Liquid Nitrogen Tank 12 Flow Regulator 13 Vaporizer

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Hidenobu Kasuya 1-1 No. 1 Atsunouramachi, Nagasaki City Mitsubishi Heavy Industries Ltd. Nagasaki Shipyard Co., Ltd.

Claims (4)

[Claims] 1. A purge gas supply system is provided outside a projectile barrel of a projectile, and a nozzle for receiving a purge gas from the purge gas supply system and ejecting the jet gas into the launch barrel is provided on a side portion of the projectile barrel. A projectile launching device, characterized in that a purge gas is supplied into the launching cylinder at the time of combustion or the like. 2. The purge gas supply system comprises an air compressor, a storage tank, and a distributor, and the nozzle is attached to the upper part of the firing cylinder with a regulating valve provided side by side. The device for launching the described flying object. 3. The purge gas supply system comprises an air compressor, a storage tank, a cooling device, and a distribution device, and the nozzle is provided with an adjusting valve so as to correspond to the vicinity of the combustion gas ejection portion of the projectile. The launcher for a flying object according to claim 1, wherein the launcher is attached to a lower part of the. 4. The purge gas supply system is configured by providing a liquid nitrogen tank, a flow rate controller, a carburetor, a temperature controller, and a distributor, and the nozzle is provided with a regulator valve in the vicinity of a combustion gas ejection portion of a projectile. The launching device for a flying object according to claim 1, wherein the launching device is attached to a lower portion of a launching barrel corresponding to.