JP4014033B2 - Rocket-mounted child bullet release device - Google Patents

Description

[0001]
[Technical field to which the invention belongs]
The present invention relates to a rocket-mounted bullet emission device used to spread a plurality of bullets mounted on a rocket to a destination.
[0002]
[Prior art]
In order to effectively spread multiple bullets to a destination in a rocket equipped with multiple bullets, it is effective to place the bullets on the rocket's circumference and release them in the centrifugal direction. It is even more effective to provide a speed difference or a time difference for the release.
[0003]
Conventionally, as the above-described rocket-mounted bullet discharge device, for example, as shown in FIG. 6, a combustion chamber 52 disposed on an axis La, a discharge explosive 53 disposed at an end of the combustion chamber 52, an ignition The combustion chamber 52 is provided with gas injection holes 55 that communicate with a plurality of the secondary bullet storage containers Co arranged around the axis La direction. The gas Ga generated by the combustion of the explosive 53 for discharge is ejected from the gas injection holes 55 to the respective bullet housing containers Co, whereby a plurality of the bullets Sb located on the circumference of the rocket are centrifuged. It discharges in the direction (the vertical direction in the figure).
[0004]
Further, as other rocket-mounted child bullet releasing devices, for example, as shown in FIG. 7, three-stage combustion chambers 62 arranged in series on the axis La, and arranged at each end of these combustion chambers 62, respectively. The discharge gunpowder 63 and the rocket-mounted child bullet discharge device 61 provided with each igniter 64 are provided. In the combustion chamber 62, the gas injection communicated with the plurality of bullet bullet storage containers Co arranged around each of them. Each hole 65 is provided.
[0005]
In this rocket-mounted child bullet discharge device 61, in each of the three-stage combustion chambers 62 located on the axis La, the discharge explosives 63 are sequentially burned with a time difference, and the gas Ga generated by the combustion of these discharge explosives 63. Are ejected from the gas injection holes 65 to the respective bullet housing containers Co in the illustrated example so that they are sequentially discharged in the centrifugal direction (vertical direction in the drawing) from the subsequent bullets Sb.
[0006]
[Problems to be solved by the invention]
However, in the above-described rocket-mounted reaming device 51, the gas Ga generated by the combustion of the explosive 53 for discharge in one combustion chamber 52 is distributed to each reaming container Co for convenience. As apparent from FIG. 6, there is a problem that it is not possible to set a time difference or a speed difference for the release of the plurality of bullets Sb.
[0007]
On the other hand, in the rocket-mounted child bullet discharge device 61, three stages of combustion chambers 62 are arranged in series on the axis La so that each discharge explosive 63 is sequentially burned. Although it is possible to release Sb, it is necessary to provide as many igniters 64 that require wiring as the number of combustion chambers 62. Therefore, it is not possible to say that the emission cost is increased and the reliability is high. There is a problem that the assembling workability is poor as much as the storage and wiring of the container 64 are required, and it has been a conventional problem to solve these problems.
[0008]
OBJECT OF THE INVENTION
The present invention has been made by paying attention to the above-described conventional problems. In addition to realizing reduction in discharge cost and improvement in assembly workability, it is possible to add a time difference and a speed difference while ensuring high reliability. An object of the present invention is to provide a rocket-mounted child bullet discharge device capable of discharging a bullet.
[0009]
[Means for Solving the Problems]
According to a first aspect of the present invention, there is provided a rocket-mounted bullet discharge device that is located on the circumference of a rocket and that is disposed in a gas container through a gas injection hole. together provided with a plurality of combustion chambers communicating with Te, provided with bomblets release explosives placed each of these combustion chamber end, the bomblets release explosives of the first-stage combustion chamber of the plurality of combustion chambers ignition A combustion chamber is connected to each of the second and subsequent combustion chambers following the first combustion chamber, and is sequentially operated in response to the pressure of the combustion gas generated by the combustion of the explosives for releasing the bullets in the previous combustion chamber. In this configuration, an ignition mechanism is provided for igniting the explosives for releasing the secondary bullets, and the configuration of the rocket-mounted secondary bullet releasing device is a means for solving the conventional problems.
[0010]
In the rocket-mounted shell discharge device according to claim 2 of the present invention, the ignition mechanism receives the combustion gas generated by the combustion of the bullet discharge explosive in the previous combustion chamber and moves to the gun discharge explosive side. And a restraining means for restricting the movement of the piston until the combustion pressure in the previous combustion chamber reaches a predetermined pressure, and a trigger that is located on the forward side of the piston and ignites the explosive for releasing the bullet. In the rocket-mounted shell discharge device according to claim 3 of the present invention, the plurality of combustion chambers are arranged in series on the rocket axis.
[0011]
[Effects of the Invention]
In the rocket-mounted shell bullet releasing device according to claim 1 of the present invention, the first-stage combustion chamber is configured when ignition is performed on the bullet-release explosive in the first-stage combustion chamber by the igniter. Following the combustion of the explosives for the release of secondary bullets, the explosives for the release of secondary bullets in the combustion chambers in the second and subsequent stages are sequentially burned by an ignition mechanism that operates in response to the pressure of the combustion gas. by the pressure of the respective combustion gas ejected to the bomblets accommodating container from the chamber of the gas injection holes, each child bullet accommodating container child bullet is to be released with a time difference. At this time, by changing the amount of each explosive explosive in a plurality of combustion chambers, it is possible to release the explosive with a speed difference.
[0012]
Further, since the igniter is used only for ignition of the explosive for releasing the bullets in the first stage combustion chamber among the plurality of combustion chambers, that is, it is sufficient to provide one igniter, so that the cost is low and the reliability is high. As a result, only one igniter that needs to be devised for storage and wiring is used, so that the assembly workability is improved accordingly.
[0013]
In the rocket-mounted child bullet discharge device according to claim 2 of the present invention, since it has the above-described configuration, it is possible to perform ignition of each bullet discharge explosive in the second and subsequent combustion chambers with a simple structure, The emission cost can be further reduced, and the rocket-mounted shell release device according to claim 3 of the present invention has the above-described configuration. There is less chance that the slaves will interfere with each other.
[0014]
【The invention's effect】
According to the rocket-mounted bullet discharge device according to claim 1 of the present invention, the above-described configuration is adopted, so that the bullet can be discharged with a time difference and a speed difference while ensuring high reliability at a low cost. As a result, it is possible to achieve a very excellent effect that it is possible to achieve a significant improvement in the assembly workability.
[0015]
Since the rocket-mounted child bullet releasing device according to claim 2 of the present invention has the above-described configuration, the emission cost can be further reduced. In the rocket-mounted child bullet discharging device according to claim 3 of the present invention, With the above-described configuration, efficient storage in the rocket is possible, and in addition, a very excellent effect is achieved in that it is possible to suppress the interference of the bullets released with a time difference from each other. .
[0016]
【Example】
Hereinafter, the present invention will be described with reference to the drawings.
[0017]
FIG. 1 shows an embodiment of a rocket-mounted bullet discharge device according to the present invention.
[0018]
As shown in FIG. 1, this rocket-mounted bullet release device 1 is located on the circumference of the rocket R and accommodates two bullets releasably in a centrifugal direction (vertical direction in the figure). The container C is provided with a plurality of combustion chambers 2 communicating with each other through the gas injection holes 2a, and is equipped with explosives 3 for releasing the bullets arranged at the front ends ( one end which is the left end in the drawing) of the combustion chambers 2, respectively. The plurality of combustion chambers 2 are arranged in series on the axis L of the rocket R.
[0019]
In this case, as shown also in FIG. 2, an igniter 4 is connected to the explosive 3A for expelling bullets of the first stage combustion chamber 2A among the plurality of combustion chambers 2, and the first stage combustion chamber 2A In the second and subsequent combustion chambers 2B, 2C,..., As shown in FIG. 3, the combustion of the explosive 3A (3B, 3C) for releasing the bullets in the previous combustion chamber 2A (2B, 2C) is performed. An ignition mechanism 10 is provided for igniting each of the explosives 3B and 3C for releasing the bullets in response to the combustion gas generated by the above.
[0020]
As shown in FIGS. 4 and 5, this ignition mechanism 10 is housed in a cylindrical cartridge 11 filled with explosives 3B (3C) for ejecting bullets and releases the bullets in the previous combustion chamber 2A (2B). Receiving the combustion gas generated by the combustion of the explosive 3A (3B), the piston 12 that moves to the explosive 3B (3C) side, and the previous combustion that is embedded between the cylindrical cartridge 11 and the piston 12 The shell pin 13 as a restraining means for restricting the movement of the piston 12 until the combustion pressure in the chamber 2A (2B) reaches a predetermined pressure, and the discharge of the bullet through the explosive 5 for ignition located on the forward side of the piston 12 A trigger 14 for igniting the explosive 3B (3C) is provided.
[0021]
In addition, the code | symbol 6 in FIGS. 2-5 is a seal ring.
[0022]
As shown in FIG. 2, in the rocket-mounted submunition release device 1, first, when the igniter 4 ignites the subunit explosive 3A in the first-stage combustion chamber 2A, the first-stage combustion chamber 2A The combustion gas G generated by the combustion of the explosive 3A for expelling the secondary bullets is ejected into the secondary bullet storage containers C and C through the gas injection holes 2a, so that the secondary bullet on the head side of the rocket R (left side in FIG. 1) B and B are released.
[0023]
Next, as shown in FIG. 3, when the combustion pressure in the first stage combustion chamber 2A reaches a predetermined pressure, as shown in FIG. 4, the shear pin 13 is cut by the pressure, and the restriction by the shear pin 13 is released. The piston 12 receives the combustion gas G in the first-stage combustion chamber 2A and moves to the explosive 3B side for expelling explosives.
[0024]
Then, as shown in FIG. 5, when the trigger 14 located on the forward side of the piston 12 ignites the explosive 3B for expelling the bullet through the explosive 5 for ignition, the explosive for expelling the bullet in the second stage combustion chamber 2B. Since the combustion gas G generated by the combustion of 3B is ejected to the secondary bullet storage containers C, C through the gas injection holes 2a in the same manner as described above, the secondary bullets B, B in the center of FIG. 1 are released. Subsequently, the explosives 3 for releasing the bullets in the combustion chambers 2 in the third and subsequent stages are sequentially burned, so that the bullets B are released from the respective bullet housing containers C with a time difference.
[0025]
At this time, if the amount of each explosive explosive 3 in the plurality of combustion chambers 2 is changed, the explosive B having a speed difference can be released.
[0026]
In the above-described rocket-mounted reaming device 1, it is only necessary to provide a single igniter 4 for igniting the explosive 3 </ b> A for ejecting the remuneration in the first stage combustion chamber 2 </ b> A among the plurality of combustion chambers 2. It is possible to release the time difference of the bullet B at low cost and with high reliability, and in addition, the assembly workability is good because only one system of the igniter 4 that is devised for storage and wiring is used. Become.
[0027]
Further, in the above-described rocket-mounted child bullet releasing device 1, the ignition mechanism 10 is composed of the piston 12, the shear pin 13 that restricts the movement of the piston 12, and the trigger 14 that ignites the explosive 3 for releasing the bullet. Thus, the ignition of each of the explosives 3 for releasing the bullets in the second and subsequent combustion chambers 2 is performed with a simple structure. As a result, the emission cost can be further reduced. In the on-board bullet releasing device 1, since the plurality of combustion chambers 2 are arranged in series on the axis L of the rocket R, the inside of the rocket R has a good fit, and the bullets B released with a time difference interfere with each other. Such a thing almost disappears.
[0028]
The detailed configuration of the rocket-mounted child bullet releasing device according to the present invention is not limited to the above-described embodiment.
[Brief description of the drawings]
FIG. 1 is an operation explanatory view showing an embodiment of a rocket-mounted shell bullet releasing device according to the present invention.
FIG. 2 is an enlarged cross-sectional explanatory view showing a state in which a bullet discharge explosive in a first stage combustion chamber of the rocket-mounted bullet discharge device in FIG. 1 is ignited.
3 is an enlarged cross-sectional explanatory view showing a state before the operation of an ignition mechanism for igniting explosives for releasing bullets in a second stage combustion chamber of the rocket-mounted bullet discharge device in FIG. 1; FIG.
4 is an enlarged cross-sectional explanatory view showing a state immediately after the operation of the ignition mechanism in FIG. 3; FIG.
5 is an enlarged cross-sectional explanatory view showing a state in which combustion gas is generated by the operation of the ignition mechanism in FIG. 3. FIG.
FIG. 6 is an operation explanatory view showing a conventional rocket-mounted bullet discharge device.
FIG. 7 is an operation explanatory view showing another conventional rocket-mounted child bullet releasing device.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Rocket-mounted child bullet discharge device 2 Combustion chamber 3 Gunpowder tow rocket 4 for releasing bullets Ignition device 10 Ignition mechanism 12 Piston 13 Shear pin (restraint means)
14 Trigger B Ream C C Ream containment container G Combustion gas L Axle R Rocket

Claims (3)

A plurality of combustion chambers that are located on the circumference of the rocket and that communicate with the at least one secondary bullet storage container that releasably stores the secondary bullets in the centrifugal direction via the gas injection holes are provided. comprising a bomblets release explosives disposed to one end of the bomblets release explosives of the first-stage combustion chamber of the plurality of combustion chambers to connect the igniters, second following the first stage combustion chamber Each of the combustion chambers after the stage is provided with an ignition mechanism that sequentially operates in response to the pressure of the combustion gas generated by the combustion of the explosives for releasing the bullets in the previous combustion chamber and ignites each explosive for expelling the bullets. A rocket-mounted child bullet discharge device characterized by that.   The ignition mechanism receives the combustion gas generated by the combustion of the explosive for expelling bullets in the previous combustion chamber and moves to the explosive for expelling explosives until the combustion pressure in the previous combustion chamber reaches a predetermined pressure. The rocket-mounted reaming device according to claim 1, further comprising: a restraining means for restricting movement of the piston; and a trigger that is located on the forward side of the piston and ignites the explosive for ejecting the remnant.   The rocket-mounted bullet discharge device according to claim 1 or 2, wherein the plurality of combustion chambers are arranged in series on a rocket axis.

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