JP2004044884A - Rocket mounted sub warhead ejecting device - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To eject sub warheads with time difference and speed difference while reducing ejecting cost, improving assembly workability, and securing high reliability. <P>SOLUTION: The rocket mounted sub warhead ejecting device is provided with a plurality of combustion chambers 2 communicated with at least one sub warhead housing container C positioned on a circumference of a rocket R and housing sub warheads B so they can be released in centrifugal directions, and sub warhead ejecting explosives 3 respectively arranged in the combustion chambers 2. An igniter 4 is connected to the warhead ejecting explosive 3A for a first state combustion chamber 2A of the plurality of combustion chambers 2. Ignition mechanisms 10 receiving combustion gas G caused by combustion of the sub warhead ejecting explosives 3A and 3B in the combustion chambers 2A and 2B, sequentially operating, and igniting each sub warhead ejecting explosives 3B and 3C are respectively provided in the combustion chambers 2B and 2C of a second stage and onward subsequent to the first stage combustion chamber 2A. <P>COPYRIGHT: (C)2004,JPO

Description

[0001]
TECHNICAL FIELD OF THE INVENTION
TECHNICAL FIELD The present invention relates to a rocket-mounted submunition discharge device used to spray a plurality of submunitions mounted on a rocket to a destination.
[0002]
[Prior art]
In a rocket with multiple submunitions, in order to effectively distribute multiple submunitions to the destination, it is effective to arrange the submunitions on the circumference of the rocket and discharge them in the centrifugal direction. Yes, it is even more effective to provide a speed difference or time difference when releasing.
[0003]
Conventionally, as the above-described rocket-mounted submunition discharge device, for example, as shown in FIG. 6, a combustion chamber 52 disposed on an axis La, a discharge powder 53 disposed at an end of the combustion chamber 52, There is a rocket-mounted submunition discharge device 51 equipped with a rocket 54, and the combustion chamber 52 is provided with a gas injection hole 55 communicating with a plurality of submunition storage containers Co arranged around and along the machine axis La direction. A plurality of submunitions Sb located on the circumference of the rocket are centrifuged by ejecting the gas Ga generated by the burning of the explosive powder 53 from the gas injection holes 55 to the individual submunition storage containers Co. The light is emitted in the direction (vertical direction in the figure).
[0004]
As another rocket-mounted submunition release device, for example, as shown in FIG. 7, three stages of combustion chambers 62 arranged in series on the machine axis La, and at each end of these combustion chambers 62, respectively. And a rocket-mounted submunition discharge device 61 provided with each of the igniters 64. The combustion chamber 62 has a gas injection communicating with a plurality of submunition storage containers Co arranged around each other. Holes 65 are provided respectively.
[0005]
In the rocket-mounted submunition release device 61, each of the explosives 63 is sequentially burned with a time lag in a three-stage combustion chamber 62 located on the machine axis La, and the gas Ga generated by the combustion of these explosives 63 is discharged. Are ejected from the gas injection holes 65 to the respective submunition storage containers Co, so that the submunitions Sb in the illustrated example are sequentially discharged in the centrifugal direction (vertical direction in the figure) from the rear side.
[0006]
[Problems to be solved by the invention]
However, in the above-described rocket-mounted submunition discharge device 51, the gas Ga generated by the combustion of the explosive powder 53 inside one combustion chamber 52 is distributed to the submunition storage containers Co for convenience. As is clear from FIG. 6, there is a problem that a time difference and a speed difference cannot be set for the release of the plurality of submunitions Sb.
[0007]
On the other hand, in the rocket-mounted submunition discharge device 61, three stages of combustion chambers 62 are arranged in series on the machine axis La so as to sequentially burn each explosive powder 63, so that submunitions with a time difference are provided. Although Sb can be released, the number of igniters 64 requiring wiring must be provided by the number of the combustion chambers 62, so that the emission cost is increased and the reliability is not high. There is a problem that the workability of assembling is poor due to the necessity for devising the housing and wiring of the container 64, and it has been a conventional problem to solve these problems.
[0008]
[Object of the invention]
SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional problems, and has realized a reduction in time and speed while ensuring high reliability while realizing a reduction in emission cost and an improvement in assembly workability. It is an object of the present invention to provide a rocket-mounted submunition discharge device capable of discharging a bullet.
[0009]
[Means for Solving the Problems]
A rocket-mounted submunition discharge device according to claim 1 of the present invention includes a combustion chamber located on the circumference of the rocket and communicating with at least one submunition container that accommodates the submunition so as to be releasable in a centrifugal direction. A plurality of explosives are provided for each of the combustion chambers, and an explosive for explosives in the first-stage combustion chamber of the plurality of combustion chambers is connected to an igniter. In the combustion chambers of the second and subsequent stages following the first-stage combustion chamber, the combustion gases generated by the combustion of the explosive for discharging submunitions in the preceding combustion chamber are sequentially operated to ignite each of the explosives for discharging submunitions. The ignition mechanism is provided respectively, and the configuration of the rocket-mounted submunition release device is used as means for solving the conventional problems.
[0010]
In the rocket mounted submunition discharge device according to claim 2 of the present invention, the ignition mechanism receives the combustion gas generated by the combustion of the submunition discharge explosive in the combustion chamber and moves to the submunition discharge explosive side. And a restraining means for restricting the movement of the piston until the combustion pressure in the combustion chamber reaches a predetermined pressure, and a trigger positioned on the forward side of the piston to ignite the explosive for discharging ammunition. In the rocket-mounted submunition discharge device according to claim 3 of the present invention, the plurality of combustion chambers are arranged in series on the axis of the rocket.
[0011]
Effect of the Invention
The rocket-mounted submunition discharge device according to claim 1 of the present invention has the above-described configuration. Therefore, when ignition of the submunition discharge explosive of the first-stage combustion chamber by the igniter is performed, this first-stage combustion chamber is used. Following the burning of the submunition discharge explosive, each submunition discharge explosive in the second and subsequent combustion chambers is sequentially burned by the ignition mechanism, and is ejected to the submunition container connected to each combustion chamber. Due to the respective combustion gas, the submunition is released from each submunition storage container with a time difference. At this time, by changing the amount of each explosive for discharging submunitions in a plurality of combustion chambers, submunitions having different speeds can be discharged.
[0012]
Further, since the igniter is used only for igniting the explosive for discharging submunitions in the first-stage combustion chamber of 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. With this arrangement, the submunition can be discharged at a time difference, and in addition, since only one system of igniters requiring storage and wiring is used, the assembling workability is improved accordingly.
[0013]
In the rocket-mounted submunition discharge device according to claim 2 of the present invention, since the above configuration is adopted, ignition of each submunition discharge explosive in the combustion chambers of the second and subsequent stages can be performed with a simple structure. This further reduces the release cost, and the rocket-mounted submunition discharge device according to the third aspect of the present invention has the above-described configuration, so that the rocket can be easily settled in the rocket and can be released with a time difference. It is less likely that the bombs will interfere with each other.
[0014]
【The invention's effect】
According to the rocket-mounted submunition release device according to the first aspect of the present invention, the above configuration enables the submunition to be released with a time difference and a speed difference while ensuring low cost and high reliability. Thus, a very excellent effect that it is possible to greatly improve the assembling workability is provided.
[0015]
The rocket-mounted submunition release device according to claim 2 of the present invention has the above-described configuration, so that it is possible to further reduce the release cost, and the rocket-mounted submunition discharge device according to claim 3 of the present invention has With the above-described configuration, it is possible to efficiently store the rockets in the rocket, and in addition, it is possible to obtain a very excellent effect that it is possible to reduce the possibility that the submunitions emitted with a time difference interfere with 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 submunition discharge device according to the present invention.
[0018]
As shown in FIG. 1, this rocket-mounted submunition release device 1 includes two submunitions which are positioned on the circumference of a rocket R and accommodate a submunition B in a releasable manner in a centrifugal direction (vertical direction in the drawing). A plurality of combustion chambers 2 are provided in communication with the container C via the gas injection holes 2a, and a plurality of explosives 3 for discharging submunitions arranged at the front ends (left ends in the drawing) of these combustion chambers 2 are provided. The combustion chambers 2 are arranged in series on the axis L of the rocket R.
[0019]
In this case, as shown in FIG. 2, an igniter 4 is connected to the explosive 3A of the first stage combustion chamber 2A of the plurality of combustion chambers 2, and the first stage combustion chamber 2A As shown in FIG. 3, the combustion chambers 2B, 2C,... Of the second stage and subsequent stages burn the explosive 3A (3B, 3C) in the previous combustion chamber 2A (2B, 2C). There is provided an ignition mechanism 10 for receiving the combustion gas generated by the above and sequentially operating to ignite each of the submunition discharge explosives 3B and 3C.
[0020]
As shown in FIGS. 4 and 5, this ignition mechanism 10 is housed in a cylindrical cartridge 11 filled with a submunition discharge explosive 3B (3C) and is used to discharge submunition in the combustion chamber 2A (2B). The piston 12 which receives the combustion gas generated by the combustion of the explosive 3A (3B) and moves to the submunition discharge explosive 3B (3C) side, and is buried between the cylindrical cartridge 11 and the piston 12 to be burned. A shear 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 a submunition is discharged via the ignition powder 5 located on the forward side of the piston 12 A trigger 14 for firing the explosive 3B (3C) is provided.
[0021]
Reference numeral 6 in FIGS. 2 to 5 denotes a seal ring.
[0022]
In the rocket-mounted submunition discharge device 1, first, as shown in FIG. 2, when the igniter 4 ignites the first stage combustion chamber 2A with respect to the submunition discharge explosive 3A, the first stage combustion chamber 2A The combustion gas G generated by the burning of the submunition discharging explosive 3A is ejected to the submunition storage containers C, C through the gas injection holes 2a, so that the submunition 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 restraint by the shear pin 13 is released. The piston 12 receives the combustion gas G in the first-stage combustion chamber 2A and moves toward the submunition discharge explosive 3B.
[0024]
Then, as shown in FIG. 5, when the trigger 14 located on the forward side of the piston 12 ignites the submunition discharge gunpowder 3B via the ignition gunpowder 5, the submunition discharge gunpowder in the second stage combustion chamber 2B is discharged. Since the combustion gas G generated by burning 3B is ejected to the submunition storage containers C, C through the gas injection holes 2a in the same manner as above, the submunitions B, B in the center of FIG. 1 are released. Then, the submunitions B in the third and subsequent combustion chambers 2 are sequentially burned, so that the submunitions B are discharged from the submunition storage containers C with a time difference.
[0025]
At this time, by changing the amount of each explosive 3 for discharging submunitions in the plurality of combustion chambers 2, it is possible to discharge submunitions B having different speeds.
[0026]
In the above-described rocket-mounted submunition discharge device 1, since only one system of igniter 4 is required for igniting the submunition discharge explosive 3A in the first-stage combustion chamber 2A of the plurality of combustion chambers 2, The time delay discharge of the submunitions B can be performed at low cost and with high reliability, and in addition, the workability of assembling is good because only one system of the igniter 4 is used for storage and wiring. Become.
[0027]
Further, in the above-described rocket-mounted submunition discharge device 1, the ignition mechanism 10 is constituted by the piston 12, the shear pin 13 for controlling the movement of the piston 12, and the trigger 14 for igniting the submunition discharge explosive 3. In addition, the ignition of each submunition discharge explosive 3 in the second and subsequent combustion chambers 2 is performed with a simple structure, and as a result, the discharge cost can be further reduced. In the mounted submunition discharge device 1, the plurality of combustion chambers 2 are arranged in series on the axis L of the rocket R, so that the submunitions B released within the rocket R are good and interfere with each other. Such things are almost gone.
[0028]
The detailed configuration of the rocket-mounted submunition release 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 submunition discharge device according to the present invention.
FIG. 2 is an enlarged cross-sectional explanatory view showing a situation in which a submunition discharge explosive in a first stage combustion chamber of the rocket mounted submunition discharge device in FIG. 1 is ignited.
3 is an enlarged sectional explanatory view showing a state before an ignition mechanism for igniting a submunition discharge explosive in a second-stage combustion chamber of the rocket-mounted submunition discharge device in FIG. 1 before operation;
FIG. 4 is an enlarged 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 the ignition mechanism in FIG. 3 operates to generate combustion gas.
FIG. 6 is an operation explanatory view showing a conventional rocket-mounted submunition discharge device.
FIG. 7 is an operation explanatory view showing another conventional rocket-mounted submunition discharge device.
[Explanation of symbols]
DESCRIPTION OF REFERENCE NUMERALS 1 Rocket mounted submunition discharge device 2 Combustion chamber 3 Gunpowder traction rocket for discharging submunitions 4 Igniter 10 Ignition mechanism 12 Piston 13 Sharpin (restraint means)
14 Trigger B Submunition C Submunition container G Combustion gas L Axis R Rocket

Claims (3)

A plurality of combustion chambers are provided on the circumference of the rocket and communicate with at least one submunition container that accommodates the submunitions in a releasable manner in the centrifugal direction, and the submunitions respectively arranged in these combustion chambers An explosive is provided, an igniter is connected to the submunition discharge explosive of the first stage combustion chamber of the plurality of combustion chambers, and the second and subsequent combustion chambers following the first stage combustion chamber are provided with: A rocket-mounted submunition discharge characterized in that an ignition mechanism is provided for sequentially receiving the combustion gas generated by the combustion of the submunition release explosive in the combustion chamber and igniting each submunition discharge explosive. apparatus. The ignition mechanism receives a combustion gas generated by the combustion of the explosive explosive in the previous combustion chamber and moves to the explosive explosive side after receiving the combustion gas, and until the combustion pressure in the previous combustion chamber reaches a predetermined pressure. 2. The rocket-mounted submunition release device according to claim 1, further comprising a restraining means for restricting the movement of the piston, and a trigger positioned on the forward side of the piston to ignite the submunition discharge explosive. The rocket-mounted submunition release device according to claim 1 or 2, wherein the plurality of combustion chambers are arranged in series on the axis of the rocket.

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