JPH06288699A - Long bullet core - Google Patents

Abstract

PURPOSE:To provide a long bullet core which can stabilize a flying attitude without wing. CONSTITUTION:A long bullet core comprises an airframe body 1, and a spiral part 4 extended from a front end of the body 1 toward a rear end on a surface 1a of the body 1 to apply a spin to the body 1. Thus, a bullet core useful for an electrothermo-chemical gun can be obtained.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a long core and a novel improvement for stabilizing a flight attitude without a wing.

[0002]

2. Description of the Related Art The structure shown in FIG. 9 has been adopted as this type of long core which has been generally used. In FIG. 9, a symbol A indicates a long core,
The long core A has a columnar flying body 1 made of tungsten or depleted uranium. A surface 1a as an air resistance surface is formed on the flying body 1. A warhead 1b is formed at the tip of the flying body 1, and a sabot fixing groove 2 for fixing a sabot (not shown) is formed in the center of the flying body 1. Further, at the rear end of the flying body 1, a plurality of stabilizing wings 3 are erected from the surface 1a toward the outside. Therefore, the long core A, which is launched at high speed from a known launching device, can keep its attitude during flight by the stabilizing wings 3.

[0003]

Since the conventional long core has the above-mentioned structure, the following problems exist. That is, since the flying main body 1 is provided with a fairly large stabilizing wing 3 that contributes to stable flight, a launching device having a diameter smaller than the outer diameter of the stabilizing wing 3 cannot be used. There is a problem in that the launcher itself has to be made larger because it is used.

The present invention has been made to solve the above problems, and it is an object of the present invention, in particular, to provide a long core which is wingless and has a stable flight attitude.

[0005]

The elongated core according to the present invention has a flying body and a spiral portion formed on the surface of the flying body.

More specifically, the flying body is formed in a cylindrical shape.

More specifically, the flying body is formed in a conical shape.

More specifically, the flying body is a polyhedron.

The elongated core according to the present invention has a flight main body and an inner cavity formed in the flight main body, and has an overall cylindrical shape.

More specifically, a fin having a predetermined inclination angle with respect to the central axis of the flying body is projected at the rear end of the inner wall surface defining the inner cavity.

More specifically, an injection hole for communicating the inner wall surface defining the inner cavity with the surface of the flying body is formed at the rear end of the flying body, and the inner opening of the injection hole is located. The azimuth angle is different from the azimuth angle at which the outer opening of the injection hole is located.

[0012]

In the long core according to the present invention, when the long core is fired at a high speed by the firing device, the air current flows backward along the spiral portion formed on the surface, and the flying body is spun. As a result, the long core can continue stable flight while rotating spirally.

[0013]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A preferred embodiment of the long core according to the present invention will be described in detail below with reference to the drawings. In addition, the same or equivalent portions as those of the conventional example will be described using the same reference numerals.

In FIG. 1, reference numeral A1 indicates a long core which shows the first embodiment of the present invention.
1 is provided with a columnar flying body 1. This flight body 1
The flying body 1 has a surface 1a as an air resistance surface. The flying body 1 has a cylindrical warhead 1b integrally formed at the tip thereof, and the flying body 1 has a rear end integrally formed with a cylindrical bow 1c. Is formed in. Further, on the surface 1a, a spiral portion 4 extending from the front end to the rear end of the flying body 1 is formed. It is more preferable that the warhead 1b and the tail 1c have the same diameter. Further, the tip of the warhead 1b is streamlined to reduce air resistance.

In FIG. 2, reference numeral A2 indicates a long core which shows the second embodiment of the present invention.
2 is provided with a conical flying body 1. This flight body 1
Has a surface 1a as an air resistance surface, a conical warhead 1b is integrally formed at the tip of the flying body 1, and a cylindrical tail 1c is integrally formed at the rear end of the flying body 1. Is formed in. Further, on the surface 1a, a spiral portion 4 extending from the front end to the rear end of the flying body 1 is formed.

Next, the case of firing the long core A2 will be described. As shown in FIG. 3, the long core A2 is mounted in the cylindrical body 5a of the launching device 5, and the explosive 6 is mounted behind the long core A2. A relatively hard metal through plate 7 for penetrating the long core A2 is formed at the tip of the cylindrical body 5a. Therefore, by igniting the explosive powder 6, the long core A2 is propelled forward. Then, as shown in FIG. 4, the warhead 1b of the long core A2 advances while destroying the through plate 7, and the spiral part 4 of the flying body 1 and the through plate 7 cooperate with each other to make the long core A2.
2 can be given an initial rotation. And surface 1
Since the airflow flows backward along the spiral portion 4 formed in a and spins the flying body 1, the long core A2 flies in a stable posture while rotating.

In FIGS. 5 and 6, reference numeral A3 is a long bullet core showing a third embodiment of the present invention, and this long bullet core A3 is provided with a flying body 1 having a cylindrical shape. A uniform surface 1a as an air resistance surface is formed on the flying body 1, a tapered warhead 1b is integrally formed on the tip of the flying body 1, and an airflow introduction port 8 is formed on the warhead 1b. An airflow outlet 9 is formed at the rear end of the flying body 1. Therefore, in the center of the flying body 1, the airflow inlet 8
Lumen 1 extending in the longitudinal direction from the air flow outlet 9 to the air flow outlet 9
0 will be defined. At the rear end of the inner wall surface 11 that defines the inner cavity 10, a plurality of fins 1 (three in this case) having an inclination angle α with respect to the central axis 12 of the flying body 1.
3 is projected. These fins 13 are arranged at equal intervals as shown in FIG. The number and shape of the fins 13 and the tilt angle α can be appropriately changed according to the firing speed and the rotation speed of the flying body 1.

Here, the case of firing the long core A3 will be described. The long core A3 is propelled forward by a launching device (not shown) to fire the long core A3 at high speed. At this time, the airflow is introduced from the airflow introducing port 8 and discharged to the airflow discharging port 9, but the airflow flowing in the direction of the arrow B in the inner cavity 10 collides with the fin 13 to change its direction. Then, the reaction force caused by the collision force spins the long core A3, so that the long core A3 flies in a stable posture while rotating.

In FIGS. 7 and 8, reference numeral A4 is a long bullet core showing a fourth embodiment of the present invention, and this long bullet core A4 is provided with a cylindrical flying body 1. A uniform surface 1a as an air resistance surface is formed on the flying body 1, a tapered warhead 1b is integrally formed on the tip of the flying body 1, and an airflow introduction port 8 is formed on the warhead 1b. The lid 1e is integrally formed at the rear end of the flying body 1. Therefore, the flying body 1 has a longitudinal direction defined by a lumen 10 whose one side is sealed by the lid 1e and whose other side is opened by the airflow inlet 8.

An injection hole 14 is formed at the rear end of the flying body 1 to connect the inner wall surface 11 defining the inner cavity 10 and the surface 1a. As shown in FIG. 8, the injection hole 14 is provided with an inner opening 14a and an outer opening 14b. The azimuth angle β at which the inner opening 14a is located is the azimuth angle γ at which the outer opening 14b is located. Is different from.
Therefore, the jet flow discharged from the jet hole 14 can be made closer to the tangential direction of the flying body 1. The injection hole 1
It is preferable to arrange the nozzles 4 at equal intervals, and the number and shape of the injection holes 14 and the direction angles β and γ can be appropriately changed according to the firing speed and the rotation speed of the flying body 1.

Here, the case of firing the long core A4 will be described. The long core A4 is propelled forward by a launching device (not shown) to fire the long core A4 at high speed. At this time, the airflow introduced from the airflow introduction port 8 flows in the direction of arrow C along the inner cavity 10 and escapes outward through the injection hole 14, but the injection flow discharged from the injection hole 14 is tangential. Since the jet flow causes the flying main body 1 to spin, the long core A3 flies in a stable posture while rotating.

The present invention is not limited to the above-described embodiment, and for example, the surface 1a may be formed in a polyhedron, and the direction of the fins 13 and the injection holes 14 and the thread cutting direction of the spiral portion 4 may be changed. It goes without saying that the rotation direction of the flying body 1 can be appropriately selected by changing it.

Further, the launching device 5 is not limited to the one described above, and for example, the long cores A1, A2, A3, A4 are used.
Can also be applied to an electrothermal chemical cannon configured to fire a long core with high-temperature generated gas generated by the electrothermal chemical reaction of the electrothermal chemical section. In addition, since the electrothermal chemical gun must take into consideration extinction and mass separation, it is difficult to use the conventional fixed stabilizing blade extending outward from the surface 1a. Therefore, the long cores A1, A2, A3 and A4 described above are particularly useful in the electrothermal chemical gun.

[0024]

Since the long core according to the present invention is constructed as described above, the following effects can be obtained. That is, by forming a spiral portion extending from the front end to the rear end of the flight main body on the surface of the flight main body and giving the spin to the flight main body, it is possible to match the outer diameter of the long core. Since the diameter of the launcher can be selected,
A small-diameter launcher can be used, and the launcher itself can be miniaturized. Further, it is possible to achieve a wingless long core having a stable flight attitude with a simple configuration. Further, by forming the flying main body in a cylindrical shape, there is an excellent effect that a light long elongated core can be configured for its length.

[Brief description of drawings]

FIG. 1 is a side view showing a first embodiment of a long core of the present invention.

FIG. 2 is a side view showing a second embodiment of the long core of the present invention.

FIG. 3 is a cross-sectional view showing a state in which a long core of the present invention is attached to a launching device.

FIG. 4 is a cross-sectional view showing a state in which a long core of the present invention is fired.

FIG. 5 is a vertical sectional view showing a third embodiment of the long core of the present invention.

6 is a transverse sectional view of the elongated core shown in FIG.

FIG. 7 is a vertical cross-sectional view showing a fourth embodiment of the long core of the present invention.

8 is a cross-sectional view of the long core shown in FIG.

FIG. 9 is a plan view showing a conventional long core.

[Explanation of symbols]

 A1, A2, A3, A4 Long core α Inclination angle β, γ Azimuth 1 Flight body 1a Surface 4 Spiral part 10 Inner cavity 11 Inner wall surface 12 Center axis 13 Fin 14 Injection hole 14a Inner opening 14b Outer opening

Claims (7)

[Claims] 1. A flying body (1) and this flying body (1)
And a helical portion (4) formed on the surface (1a) of the long core. 2. The long bullet core according to claim 1, wherein the flying body (1) is formed in a cylindrical shape. 3. The long core according to claim 1, wherein the flying body (1) is formed in a conical shape. 4. The long core according to claim 1, wherein the flying body (1) is a polyhedron. 5. A flying body (1) and this flying body (1)
An elongated core having an inner cavity (10) formed in and a tubular shape as a whole. 6. An inner wall surface (1) defining the lumen (10).
1) At the rear end, the central axis (12) of the flying body (1)
Fins (13) having a predetermined tilt angle (α) with respect to
6. The long core according to claim 5, wherein the long core is provided so as to project. 7. An inner wall surface (1) defining the lumen (10).
1) and the surface (1a) of the flying body (1) are communicated with each other by forming an injection hole (14) at the rear end of the flying body (1), and an inner opening (14a) of the injection hole (14). The azimuth (β) in which the) is located is different from the azimuth (γ) in which the outer opening (14b) of the injection hole (14) is located. Shaku bullet core.