JP2879095B2 - Sublimation projectile loading mechanism - Google Patents

Description

Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a launching apparatus in which a sublimable object typified by dry ice is used as a flying object, and the flying object is caused to fly at high speed under the action of high-pressure gas injection. The present invention relates to a loading mechanism for a sublimable flying object that is suitably used for a sublimation flying object.

2. Description of the Related Art Objects that fly at high speed in space, such as bullets and shells fired from firearms, cannons, and rockets, can be generally referred to as "high-speed flying objects." These high-speed flying objects
Although the emphasis is mainly on the use mainly for military purposes, the large energy released when the projectile flies at high speed and collides with any object controls this appropriately. This allows for peaceful use. Therefore, the flying object is loaded into the launching device, and the flying object is driven at a high speed by the recoil due to the explosion of the explosive, the strong injection pressure of the high-pressure gas, and the other electric repulsive force to collide with the required object. Attempts to analyze the physical properties of objects have already been put to practical use at the experimental stage.

As a conventional mechanism for loading these projectiles into the launching device, since the projectiles are made of a metal material, the loading structure of general weapons such as firearms and artillery is diverted as it is. In most cases, the loading mechanism itself was not particularly new.

Problems to be Solved by the Invention As described above, the flying object is caused to fly at a high speed to collide with any object, and to achieve effective physical work by powerful energy released at that time. Each of the launching devices uses a metal material as a flying object. Therefore, the mechanism itself for loading the projectile into the launch device is:
The bullet loading mechanism developed for military use and already completed should have been diverted.

However, the present inventors have proposed a launch system according to a new idea that uses a sublimable object represented by dry ice in which carbon dioxide is solidified as a flying object instead of using the flying object made of the metal material. We developed and filed a patent application for the system on the same date as the present application. This launching system is to fly a flying object made of the sublimable object at a high speed under the action of jetting high-pressure gas, and to achieve the required physical work by projecting the flying object onto an object. In this case, since the projectile loaded into the launching system is sublimable as described above and at a very low temperature, the known mechanism used to load the conventional metal projectile is It cannot be put to practical use as it is.

That is, in the newly proposed launching system, since the projectile is a sublimable object, an operation of quickly and surely loading the projectile is required, and the projectile is driven at a high speed by a high-pressure gas injection action. For this reason, it is required to withstand high pressure and to have a high degree of hermeticity, but it is clear that a conventional bullet loading mechanism cannot be used for this purpose.

SUMMARY OF THE INVENTION The present invention provides a projectile loading mechanism used in the above-described sublimable projectile launching system, in which a sublimable projectile can be quickly and reliably loaded into a launching device, and has a high pressure resistance and It is an object of the present invention to provide a novel loading mechanism that achieves airtightness.

Means for Solving the Problems In order to overcome the above-mentioned problems and appropriately achieve the intended purpose, the present invention provides a projectile made of a sublimable object such as dry ice by applying the injection pressure of a high-pressure gas at once, A projectile loading mechanism for use in a launching device that launches the projectile from a launch tube at high speed, comprising a loading port that opens to the side of the mechanism body and communicates with a loading chamber formed in the middle of the mechanism. A lid capable of opening and closing the loading port, and a lid rotatably provided in the loading chamber, and a direction aligned with the loading port or a direction aligned with the launching cylinder can be selected according to a rotational position of the lid. And a posture conversion body having a spherical body and a flying object loading part therein.

Next, the loading mechanism of the sublimable flying object according to the present invention,
Preferred embodiments will be described below with reference to the accompanying drawings. In this embodiment, as the sublimable flying object, dry ice obtained by solidifying carbon dioxide gas into a cylindrical shape is used as a material, and an inert gas, particularly nitrogen gas is used as a driving source of the flying object. . This is liquefied natural gas (LN
G) A large amount of cold heat released when reducing to room temperature gas enables the production and production of low-cost, large-scale dry ice by liquefying by cooling and solidifying carbon dioxide gas produced by-product in the petrochemical and ammonia industries. This is because nitrogen gas, which is a by-product of the natural gas industry, can also be effectively used, and it is a matter of course that the use of dry ice and nitrogen gas is not limited.

FIG. 1 is a partially cutaway perspective view showing a loading mechanism for a sublimable flying object according to a preferred embodiment of the present invention. The firing cylinder 12 and the gas injection mechanism 60 in the firing system shown in FIG. 2 is an enlarged view of the mechanism main body 10 interposed between them. FIG. 7 shows a state in which the above-described sublimable projectile launching system is applied as a device for performing a destructive test of various samples. In order to absorb a strong impact when the projectile collides, FIG. , A shock absorbing chamber behind the sample storage chamber 78
80 are provided. And the launching system comprises a first
After the cylindrical dry ice projectile 32 shown in the figure is loaded into the mechanism body 10 described later, high-pressure gas injected at once from the gas injection mechanism 60 acts on the projectile 32, and the jet pressure Is made to fly from the launching cylinder 12 and collides with, for example, a sample (not shown) stored in the sample storage chamber 78 to perform required work.

Returning to FIG. 1, the high-pressure gas conduit 30 extending from the gas injection mechanism 60 (this mechanism also has a remarkable technical feature, and a patent application has been filed separately as of today), and the central axis is aligned therewith. The mechanism main body 10 according to the embodiment is interposed between the firing cylinder 12 and the firing cylinder 12 that extends straight (see FIG. 4). The mechanism body 10 includes a gas introduction path 20 connected to the high-pressure gas conduit 30, a firing path 22 communicating with the firing cylinder 12, and a projectile loading chamber 18 formed therebetween (see FIG. 3). The gas introduction path 20 and the firing path 22 are provided with corrosion resistance and
A cylindrical metal lining 56 having high pressure resistance is tightly fitted.

The firing path 22 is a sleeve separate from the mechanism body 10.
The sleeve 72 is inserted into the mechanism main body 10 with its axis lined up, and its flange 48 is attached to the main body 10.
The bolts 52 and the nuts 54 are tightened and fixed at necessary places by contacting the flange 50 on the side. Flying object 32
At the time of launching, a large gas pressure is applied to the flying object 32 loaded in the loading chamber 18, so that necessary sealing members 62, 62 are provided as shown in FIG. 3 to prevent the pressure from leaking to the outside. Have been.

The side of the mechanism body 10 has a loading chamber 18 formed therein.
A loading port 24 is opened that intersects with the
The cylindrical flying object 32 can be loaded into the loading chamber 18 from the side via the. As shown in FIG. 2, the loading port 24 is covered with a lid 26 provided with a packing 27 on the back side, and is pressed against the mechanism body 10 with bolts 28 to be removably sealed. The cover 26 is provided with a relief valve 29.
The relief valve 29 is used to easily remove the lid 26 when the lid 26 is removed from the main body 10 to be mounted on the flying object 32 described below, by setting the inside of the loading chamber 18 to atmospheric pressure. .

In the loading chamber 18, a spherical attitude converter 16 having a cylindrical loading portion 34 capable of completely storing the flying object 32 is stored. The attitude conversion body 16 is rotated by an external handle 40 to be described later to align the loading portion 34 with the loading port 24 shown in FIG. 5, and the firing path 22 and the gas introduction path shown in FIG. You can choose between the 20 alignment positions.

To describe the mounting state of the attitude converter 16 in more detail,
As shown in FIGS. 1 and 3, annular seals 46, 46, which are in close contact with the attitude converter 16, are provided at the upper and lower portions of a loading chamber 18 formed inside the main body 10, respectively. Therefore, the posture changing body 16 rotates while maintaining a high degree of airtight by rubbing closely with the annular seal bodies 46, 46. A rotating shaft 36 fixed to the top of the posture changing body 16 is rotatably supported by the mechanism main body 10 via a seal body 58 and a bearing 44, and a neck 38 formed integrally with the rotating shaft 36 is attached to the main body. It extends to the outside of 10.
A handle 40 having a shape shown in the figure is detachably attached to the neck portion 38. By operating the handle 40 in the direction of the arrow, the loading portion 34 of the posture changing body 16 is aligned with the loading port 24 as described above. Location or launch path 22 and gas introduction path
It is possible to select a position to align with 20. The rotation axis
36 is fixed to the mechanism body 10 by bolts 42 via a mounting plate 37.

As shown in FIGS. 1 and 3, the mechanism main body 10 is provided with an exhaust hole 66 communicating with the internal firing path 22.
An exhaust valve 64 is provided at 66. This is because, when preparing to launch the flying object 32, a vacuum pump (not shown) is connected to the exhaust valve 64.
To deaerate the gas introduction path 20, the loading section 34 of the main body 10, and the firing path 22. Further, as shown in FIG. 3, a through hole 68 is formed in the firing path 22 close to the attitude converter 16.
The stopper pin 70 is screwed into this through hole 68 so that it can be freely inserted and removed, so that the tip of the pin can slightly face the firing path 22. This is because the flying object 32 loaded in the loading section 34 and aligned with the firing path 22
Moving forward on launch path 22 under the influence of degassing from 64,
This is because the stopper pin 70 slightly protrudes from the inner surface of the firing path to prevent it. Therefore, when the projectile 32 is launched,
The tip of the pin 70 is lowered from the inner surface of the launch path 22 and is operated so as not to interfere with the flying object 32.

Next, the operation of the sublimable flying object loading mechanism according to the present embodiment configured as described above will be described. In use, the lid 26 is removed from the side of the mechanism body 10 to open the loading port 24, and the handle 40 is rotated left or right to form the cylindrical shape of the posture changing body 16 as shown in FIG. Insert the loading section 34 into the loading port
Set the posture to align to 24. In this state,
As shown in FIG. 1, a cylindrical flying object 32 of dry ice is moved from the side intersecting the main body 10 through the loading port 24 to the attitude changing body.
It is inserted into the 16 loading sections 34. The external dimensions of the flying object 32 are
It is assumed that the mounting portion 34 of the attitude conversion body 16 is set in advance to a dimension that can be completely inserted with a slight annular gap left. Thereafter, the lid 26 is attached to the loading port 24 via the packing 27 and is pressed down by the bolt 28, whereby the inside of the mechanism body 10 is completely sealed from the outside.

Next, by turning the handle 40 approximately 90 ° in the direction of the arrow in FIG. 5, the attitude converter 16 also rotates 90 ° from the loading position, and the flying object 32 loaded in the loading portion 34 is As shown in the figure, the gas introduction path 20 and the emission path 22 are positioned with their central axes aligned. Note that the tip of the stopper pin 70 described with reference to FIG. 3 is slightly protruded into the firing path 22 so that degassing described later is performed, and the flying object 32 is drawn toward the firing path 22 side. However, since it immediately comes into contact with the pin 70, advancement to the firing path 22 side is prevented. In this state, a vacuum pump (not shown) connected to the exhaust valve 64 is driven to degas the gas introduction unit 20, the loading unit 34, and the firing path 22. Also, in the destructive test apparatus shown in FIGS. 7 and 8 using this loading mechanism, the sample storage chamber 78 and the shock absorbing chamber 80 are simultaneously degassed, and the inside of the entire system is maintained at a high vacuum. Is done.

When the loading of the flying object 32 is completed and the air is evacuated to a required degree of vacuum, the gas injection mechanism 60 is operated, and the flying object 32 is fired. Prior to firing, the stopper pin 70 descends through the through hole 68 while maintaining an airtight state, and moves the tip thereof inwardly from the firing path 22,
The movement inhibition for the flying object 32 is released. When the gas injection mechanism 60 is operated in this state, the nitrogen gas held at a high pressure enters the gas introduction path 20 at a stroke, acts on the projectile 32 loaded in the loading mechanism 10, and causes the projectile 32 to 22 and launcher
Fire at high speed through 12. In the example shown in FIG. 7, the flying object 32 collides with a large amount of energy with the sample stored in the sample storage chamber 78, and performs destruction and other physical work.

Effect of the Invention As described above, according to the sublimable flying object loading mechanism according to the present invention, a flying object composed of a sublimable object represented by dry ice can be quickly and reliably loaded into the launching device. At the same time, high pressure resistance and airtightness are realized. In addition, when the projectile is loaded, it is not necessary to match the axes of the projectile and the launch cylinder in advance, and after the projectile is loaded from the position where it is most easily loaded, the handle is turned to rotate the handle. Is converted, and finally both can be accurately aligned.

In the illustrated embodiment, the case where the present invention is applied to a test apparatus for analyzing a physical characteristic of an object by colliding a high-speed flying object with a sample has been described. However, the launching apparatus itself of the sublimable flying object is not limited to this. It is applied to various fields, not a thing. Therefore, in the example shown, a high degree of vacuum has to be achieved in the entire apparatus, in particular in order to be particularly adapted to the destructive test apparatus shown in FIG. 7, which requires a special arrangement which can maintain its airtightness. . However, the present invention itself is not necessarily required to maintain the airtightness. Depending on the application, the airtightness may be released to the atmosphere or the high vacuum may be maintained up to the tip of the launch cylinder. .

Further, as described above, the sublimable flying object is not limited to dry ice, and other than nitrogen, the high-pressure gas may be any inert gas such as helium as long as it does not affect the human body. Various kinds of hydrogen gas and the like can be selected and used depending on economic reasons and other factors.

[Brief description of the drawings]

FIG. 1 is a partially cutaway perspective view showing a preferred embodiment of a loading mechanism for a sublimable flying object according to the present invention, FIG. 2 is a cross-sectional view taken along the line II-II of the loading mechanism shown in FIG. FIG. 3 is a vertical sectional view taken along the line III-III of the loading mechanism shown in FIG. 1, FIG. 4 is a side view showing the loading mechanism according to the embodiment connected to a gas injection mechanism and a firing cylinder, and FIG. FIG. 6 is a partially cut-away plan view of the loading mechanism according to the embodiment from above, and shows a state immediately before loading a sublimable flying object. FIG. 6 is a plan view similar to FIG. After loading the sublimable flying object, the posture is changed by 90 °, aligned with the gas introduction path and the firing path, and a state where the lid is hermetically attached is shown. FIG.
FIG. 8 is an overall side view of a destructive test apparatus using the loading mechanism according to the present embodiment, and FIG. 8 is a plan view of the destructive test apparatus shown in FIG. 10… Flying object loading mechanism 12 …… Launching cylinder, 16 …… Attitude conversion body 18 …… Loading room, 24 …… Loading port 32 …… Sublimable flying object, 34 …… Loading section

Continued on the front page (72) Inventor Takao Kobayashi 95037 Morgan Hill Vista de Valle, California, USA 2865 (72) Inventor Morio Motoo 1-200 Shimokobari Nakajima, Komaki City, Aichi Prefecture Morita Iron Works Co., Ltd. (72) Invention Person Takashi Morita 1-200 Shimokohari Nakajima, Komaki City, Aichi Prefecture Inside Morita Iron Works Co., Ltd. (72) Inventor Hiroshi Takenaka 19-18 Sakuradacho, Atsuta-ku, Nagoya City, Aichi Prefecture Toho Gas Co., Ltd. (72) Inventor Sawai Hideaki 19-18, Sakurada-cho, Atsuta-ku, Nagoya-shi, Aichi Prefecture Toho Gas Co., Ltd. Ogisho-cho, Showa-ku, Nagoya-shi, Nagoya (in the address) Nagoya Institute of Technology (72) Inventor Kouji Fukatsu Oki-sho-cho, Showa-ku, Nagoya-shi, Aichi (in the address) Nagoya Institute of Technology (72) Nagoya City Showa Gokisho-cho (address a tooth) in the Nagoya Institute of Technology (56) Reference Patent Sho 62-213886 (JP, A) (58 ) investigated the field (Int.Cl. ^6, DB name) F41A 9/38 F41B 11 / 26

Claims (1)

(57) [Claims] 1. A launching device that applies a high-pressure gas injection pressure to a projectile (32) made of a sublimable object such as dry ice at a stroke, and launches the projectile (32) from a launch tube (12) at a high speed. A loading port (24) that opens to the side of the mechanism body (10) and communicates with a loading chamber (18) formed in the middle of the mechanism (10). )
And a lid (26) that can open and close the loading port (24)
And a spherical interior provided rotatably provided in the loading chamber (18) and capable of selecting a direction to align with the loading port (24) or a direction to align with the launching cylinder (12) depending on the rotation position. And a posture converter (16) having a flying object loading section (34).