JP2012202597A - Deployed warhead - Google Patents
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- JP2012202597A JP2012202597A JP2011067056A JP2011067056A JP2012202597A JP 2012202597 A JP2012202597 A JP 2012202597A JP 2011067056 A JP2011067056 A JP 2011067056A JP 2011067056 A JP2011067056 A JP 2011067056A JP 2012202597 A JP2012202597 A JP 2012202597A
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Abstract
Description
本発明は、弾頭の側面が展開する展開弾頭に関する。 The present invention relates to a deployment warhead in which the side of the warhead is deployed.
壁等の攻撃対象物に対する破壊を目的とした弾頭について、例えば以下の非特許文献に記載の弾頭（図１）が知られている。 As a warhead for the purpose of destroying an attack target such as a wall, for example, a warhead described in the following non-patent document (FIG. 1) is known.
図１は、弾頭１の先端部２を拡大させ、爆風圧を拡大させることで攻撃対象物に対する破壊範囲の増大を狙ったものである。 FIG. 1 aims to increase the destruction range of an attack target by enlarging the tip 2 of the warhead 1 and increasing the blast pressure.
弾頭を用いて壁等の攻撃対象物に対して狙撃を行う場合、より破壊面積を大きくするために、先端部径を大きくすると、飛翔の安定性が欠如してしまうという問題点が生じることがある。
そのため、かかる場合には、照準点と着弾点にズレが生じてしまい、弾頭の機能を十分に発揮できないことがあった。
When aiming at an attack target such as a wall using a warhead, if the tip diameter is increased in order to increase the destruction area, there may be a problem that flight stability is lost. is there.
Therefore, in such a case, the aiming point and the landing point may be misaligned, and the warhead function may not be fully exhibited.
そこで、本発明の目的は、攻撃対象物に対して破壊面積を増大させ、かつ飛翔時の安定性も維持した先端部を有する弾頭を提供することにある。 Accordingly, an object of the present invention is to provide a warhead having a tip that increases the destruction area with respect to an attack target and maintains stability during flight.
前記目的を達成するため、本発明によると、攻撃対象物を破壊する展開弾頭であって、
先端部と、
該先端部の後端と一端が接続された軸と、
前記軸の一端と長手方向の一端が接続部において接続された１以上の炸薬部材と、
前記炸薬部材の長手方向について前記軸と平行になるように維持するロック装置を備え、
前記炸薬部材は、前記接続部を支点にして前記軸と垂直な方向に展開を行う付勢機構を有し、
前記ロック装置は、前記維持を解除させる解除機構を有する、ことを特徴とする展開弾頭が提供される。
In order to achieve the above object, according to the present invention, a deployment warhead for destroying an attack target,
The tip,
A shaft to which the rear end and one end of the tip are connected;
One or more glaze members in which one end of the shaft and one end in the longitudinal direction are connected at a connecting portion;
A locking device for maintaining the glaze member in parallel with the axis in the longitudinal direction;
The glaze member has a biasing mechanism that expands in a direction perpendicular to the axis with the connection portion as a fulcrum,
A deployment warhead is provided, wherein the lock device has a release mechanism for releasing the maintenance.
本発明によれば、前記先端部は、攻撃対象物までの距離を測定する攻撃対象物認識センサを有し、
前記ロック装置は、前記攻撃対象物認識センサからの前記展開を指示する展開信号を受信する展開信号受信部材を有し、
前記展開信号は、前記先端部が攻撃対象物までの距離が所定の値となった場合に、前記攻撃対象物認識センサから前記展開信号受信部材に送信される。
According to the present invention, the tip has an attack object recognition sensor for measuring a distance to the attack object,
The locking device includes a deployment signal receiving member that receives a deployment signal that instructs the deployment from the attack object recognition sensor,
The deployment signal is transmitted from the attack target recognition sensor to the deployment signal receiving member when the distance between the tip portion and the attack target becomes a predetermined value.
本発明の別の実施例によれば、前記軸は、タンデム子弾を発射するための発射機構を有する。 According to another embodiment of the invention, the shaft has a firing mechanism for firing a tandem shell.
本発明によれば、前記発射機構は、前記先端部から発射信号を受信する発射信号受信部材を有し、
前記発射信号は、前記先端部が攻撃対象物までの距離が所定の値となった場合に、該先端部に取り付けられた攻撃対象物認識センサから前記発射機構に送信される。
According to the present invention, the firing mechanism has a firing signal receiving member that receives a firing signal from the tip,
The firing signal is transmitted to the launching mechanism from an attack target recognition sensor attached to the tip when the distance between the tip and the attack target becomes a predetermined value.
本発明によると、飛翔中は炸薬部材が展開していない態勢を維持することで飛翔の安定性を維持し、着弾直前に炸薬部材を展開することで、破壊面積を増加させることを可能とする弾頭を提供することができる。 According to the present invention, the stability of the flight is maintained by maintaining a state where the glaze member is not deployed during the flight, and the fracture area can be increased by deploying the glaze member immediately before landing. A warhead can be provided.
本発明を実施するための実施形態を図面に基づいて説明する。なお、各図において共通する部分には同一の符号を付し、重複した説明を省略する。 An embodiment for carrying out the present invention will be described with reference to the drawings. In addition, the same code | symbol is attached | subjected to the common part in each figure, and the overlapping description is abbreviate | omitted.
図２は、本発明の第１実施例における展開前の弾頭の構成図である。
図２（Ａ）は展開前の弾頭の正面図、図２（Ｂ）は展開前の弾頭の側面についての断面図である。
また、図３は、本発明の第１実施例における展開後の弾頭の構成図である。
図３（Ａ）は展開後の弾頭の正面図、図３（Ｂ）は展開後の弾頭の側面についての断面図である。
この図において、１１は弾頭、１２は軸、１３は先端部、１４は炸薬部材、１４ａは付勢機構、１５はロケットモータ、１６はロック装置、１６ａは解除機構、１７は尾翼、１９は接続部である。
FIG. 2 is a configuration diagram of the warhead before deployment in the first embodiment of the present invention.
2A is a front view of the warhead before deployment, and FIG. 2B is a cross-sectional view of the side of the warhead before deployment.
FIG. 3 is a configuration diagram of the warhead after deployment in the first embodiment of the present invention.
3A is a front view of the warhead after deployment, and FIG. 3B is a cross-sectional view of the side surface of the warhead after deployment.
In this figure, 11 is a warhead, 12 is a shaft, 13 is a tip, 14 is a glaze member, 14a is a biasing mechanism, 15 is a rocket motor, 16 is a locking device, 16a is a release mechanism, 17 is a tail, 19 is a connection Part.
本発明の弾頭１１は、飛翔中に炸薬部材１４を軸１２と平行な状態に維持することで、安定的な飛翔を行うことが可能になっている。 The warhead 11 of the present invention can perform stable flight by maintaining the glaze member 14 in a state parallel to the shaft 12 during flight.
軸１２は、先端部１３とロケットモータ１５を接続しており、１以上の炸薬部材１４と接続部１９において接続している。 The shaft 12 connects the tip portion 13 and the rocket motor 15, and is connected to one or more glaze members 14 at the connection portion 19.
先端部１３は、半球形状又は円錐形状を有しており、空気抵抗が極力少なくなるような形状になっている。 The distal end portion 13 has a hemispherical shape or a conical shape, and has a shape that minimizes air resistance.
炸薬部材１４は、爆薬を有しており、攻撃対象物に接触した際に爆発を起こすようになっている。 The glaze member 14 has an explosive and causes an explosion when it comes into contact with an attack target.
炸薬部材１４は、接続点１９を支点に軸１２と垂直な方向に展開するための付勢機構１４ａを有している。
付勢機構１４ａは、例えば、バネ等の弾性力を利用したものや、磁石の反発力を利用したものである。
上記弾性力を利用した場合は、この弾性力が炸薬部材１４を展開させる方向に常に働いており、解除機構１６ａによってロックが解除されると同時に展開を行うようになっている。
The glaze member 14 has an urging mechanism 14a for deploying in a direction perpendicular to the shaft 12 with the connection point 19 as a fulcrum.
The urging mechanism 14a uses, for example, an elastic force such as a spring or a repulsive force of a magnet.
When the elastic force is used, the elastic force always works in the direction in which the glaze member 14 is expanded, and the expansion is performed at the same time as the lock is released by the release mechanism 16a.
ロケットモータ１５は、内部に搭載した推進薬を用いて、攻撃対象物に向けた推進力を発生させている。
また、ロケットモータ１５の周辺に１つ以上の尾翼１７が設置されており、かかる構成によって飛翔を安定させることができる。
The rocket motor 15 generates a propulsive force toward the attack target using a propellant mounted inside.
In addition, one or more tail blades 17 are installed around the rocket motor 15, and the flight can be stabilized by such a configuration.
軸１２は、ロック装置１６を有している。
ロック装置１６は、展開信号受信部材（図示しない）を有しており、攻撃対象物認識センサ１８から展開を指示する展開信号を展開信号受信部材（図示しない）において受け取ると、解除機構１６ａによって解除を行う。
これによって、炸薬部材１４は付勢機構１４ａによって展開される。
また、ロック装置１６は、飛翔中に炸薬部材１４の一部にロック装置１６が重なるように配置されることで、炸薬部材１４の状態が軸１２と平行になるように維持している。
また、炸薬部材１４と軸１２の間に接続フックを設けておき、ロック装置１６が展開信号を受信することで上記フックを取り外す構成でもよい。
The shaft 12 has a locking device 16.
The locking device 16 has a deployment signal receiving member (not shown). When a deployment signal instructing deployment is received from the attack object recognition sensor 18 at the deployment signal receiving member (not shown), it is released by the release mechanism 16a. I do.
Thereby, the glaze member 14 is developed by the biasing mechanism 14a.
Further, the locking device 16 is arranged so that the locking device 16 overlaps a part of the glaze member 14 during the flight, so that the state of the glaze member 14 is maintained parallel to the shaft 12.
Further, a connection hook may be provided between the glaze member 14 and the shaft 12, and the hook may be removed when the lock device 16 receives a deployment signal.
攻撃対象物認識センサ１８は、先端部１３と攻撃対象物の距離が所定の値（事前に設定した値等）になった時に、展開信号受信部材（図示しない）等の各部位に信号を送る。
これによって、例えば、先端部１３が攻撃対象物に接触した瞬間に炸薬部材１４を展開させる等の調整を行うことが可能となる。
この例において、攻撃対象物認識センサ１８は、認識センサによって先端部１３と攻撃対象物の距離を認識しているが、先端部１３に攻撃対象物が接触した際の衝撃を契機に各部位に信号を送る構造でもよい。
The attack target recognition sensor 18 sends a signal to each part such as a deployment signal receiving member (not shown) when the distance between the tip 13 and the attack target reaches a predetermined value (a preset value or the like). .
Thereby, for example, it is possible to perform adjustment such as deploying the glaze member 14 at the moment when the distal end portion 13 contacts the attack target.
In this example, the attack object recognition sensor 18 recognizes the distance between the tip portion 13 and the attack target object by the recognition sensor. A structure for sending a signal may be used.
図４は、本発明の第２実施例における弾頭の側面についての断面図である。
この図は、炸薬部材を弾頭の後方に展開した場合の断面図である。
FIG. 4 is a cross-sectional view of the side of the warhead in the second embodiment of the present invention.
This figure is a cross-sectional view when the glaze member is deployed behind the warhead.
第１実施例において、展開時には先端部１３と炸薬部材１４は接触する形になるが、先端部１３が攻撃対象物と接触する際の衝撃によって炸薬部材１４の展開を妨げることが想定される場合等には、図４のように炸薬部材１４の展開位置を先端部１３から離す形に設定してもよい。 In the first embodiment, the tip 13 and the glaze member 14 come into contact with each other at the time of deployment, but it is assumed that the glaze member 14 is prevented from being deployed due to an impact when the tip 13 comes into contact with the attack target. For example, the development position of the glaze member 14 may be set away from the distal end portion 13 as shown in FIG.
図５は、本発明の第３実施例における弾頭の側面についての断面図である。
この図は、炸薬部材を弾頭において２ヶ所に分けて展開した場合の断面図である。
FIG. 5 is a cross-sectional view of the side of the warhead in the third embodiment of the present invention.
This figure is a cross-sectional view in the case where the glaze member is developed at two locations on the warhead.
第３実施例において、炸薬部材１４を２ヶ所に分けて展開することによって、
攻撃対象物の壁等が二重構造になっている場合においても、前方の炸薬部材１４で外側の壁等を破壊し、後方の炸薬部材１４によって内側の壁等を破壊することが可能になる。
In the third embodiment, by spreading the glaze member 14 in two places,
Even when the wall or the like of the attack target has a double structure, it becomes possible to destroy the outer wall or the like with the front glaze member 14 and destroy the inner wall or the like with the rear glaze member 14. .
図６は、本発明の第４実施例における弾頭の構成図である。
図６（Ａ）は展開前の弾頭の側面における断面図、図６（Ｂ）は展開後の弾頭の側面における断面図である。
この図において、２１は発射経路、２２はタンデム子弾、２３は発射機構である。
FIG. 6 is a block diagram of a warhead in the fourth embodiment of the present invention.
6A is a cross-sectional view of the side of the warhead before deployment, and FIG. 6B is a cross-sectional view of the side of the warhead after deployment.
In this figure, 21 is a firing path, 22 is a tandem bullet, and 23 is a firing mechanism.
発射機構２３は、攻撃対象物認識センサ１８からの発射信号を発射信号受信部材（図示しない）が受信した際に、タンデム子弾２２を発射させることができる。
これによって、例えば、攻撃対象物認識センサ１８が展開信号受信部材（図示しない）と発射信号受信部材（図示しない）に信号を送信するタイミングを、多少の間隔を持たせることにより、炸薬部材１４によって壁等の攻撃対象物の表面をある程度破壊した後に、タンデム子弾２２によって内部に向けた攻撃を行うことが可能になる。
The firing mechanism 23 can fire the tandem shell 22 when a firing signal receiving member (not shown) receives a firing signal from the attack object recognition sensor 18.
Thereby, for example, the glaze member 14 sets the timing at which the attack object recognition sensor 18 transmits a signal to the deployment signal receiving member (not shown) and the firing signal receiving member (not shown) by a certain interval. After destroying the surface of an attack target such as a wall to some extent, it is possible to perform an attack directed toward the inside by the tandem shell 22.
図７は、本発明の第５実施例における弾頭の構成図であり、図８は、本発明の第６実施例における弾頭の構成図である。
この図において、２５はカバーであり、２６はロック装置である。
FIG. 7 is a block diagram of the warhead in the fifth embodiment of the present invention, and FIG. 8 is a block diagram of the warhead in the sixth embodiment of the present invention.
In this figure, 25 is a cover and 26 is a locking device.
図７のように、ロック装置１６に代えてカバー２５によって、炸薬部材１４を抑えつける形とし、かかるカバー２５を分離することによって、炸薬部材１４を展開させる形でもよい。
また、図８のように、ロック装置２６を炸薬部材１４とロケットモータ１５にかかる形で設置し、かかるロック装置２６を進行方向と逆方向にスライドさせることによって炸薬部材１４を展開させる形でもよい。
As shown in FIG. 7, the glaze member 14 may be held by a cover 25 instead of the lock device 16 and the glaze member 14 may be developed by separating the cover 25.
In addition, as shown in FIG. 8, the lock device 26 may be installed on the glaze member 14 and the rocket motor 15, and the glaze member 14 may be deployed by sliding the lock device 26 in the direction opposite to the traveling direction. .
なお、炸薬部材１４の展開する際に上記の例では、軸１２と接続部１９において接続しているが、図９のように、先端部１３の両端において接続させ、回転軸２４によって、炸薬部材１４を展開させる形でもよい。 In the above example, when the glaze member 14 is deployed, the glaze member 14 is connected to the shaft 12 and the connection portion 19. However, as shown in FIG. 14 may be developed.
また、前記において、本発明の実施形態について説明を行ったが、前記に開示された本発明の実施の形態は、あくまで例示であって、本発明の範囲はこれら発明の実施の形態に限定されない。本発明の範囲は、特許請求の範囲の記載によって示され、さらに特許請求の範囲の記載と均等の意味および範囲内でのすべての変更を含むものである。 In the above, embodiments of the present invention have been described. However, the embodiments of the present invention disclosed above are merely examples, and the scope of the present invention is not limited to these embodiments. . The scope of the present invention is indicated by the description of the scope of claims, and further includes meanings equivalent to the description of the scope of claims and all modifications within the scope.
１ 弾頭、２ 先端部、１１ 弾頭、１２ 軸、
１３ 先端部、１４ 炸薬部材、１４ａ 付勢機構、１５ ロケットモータ、
１６ ロック装置、１６ａ 解除機構、１７ 尾翼、
１８ 攻撃対象物認識センサ、１９ 接続部、２１ 発射経路、
２２ タンデム子弾、２３ 発射機構、２４ 回転軸、２５ カバー、
２６ ロック装置
1 warhead, 2 tip, 11 warhead, 12 axes,
13 tip part, 14 glaze member, 14a urging mechanism, 15 rocket motor,
16 lock device, 16a release mechanism, 17 tail,
18 Attack target recognition sensor, 19 connection part, 21 launch route,
22 tandem shells, 23 firing mechanism, 24 rotation axis, 25 cover,
26 Locking device
Claims (4)
先端部と、
該先端部の後端と一端が接続された軸と、
前記軸の一端と長手方向の一端が接続部において接続された１以上の炸薬部材と、
前記炸薬部材の長手方向について前記軸と平行になるように維持するロック装置を備え、
前記炸薬部材は、前記接続部を支点にして前記軸と垂直な方向に展開を行う付勢機構を有し、
前記ロック装置は、前記維持を解除させる解除機構を有する、ことを特徴とする展開弾頭 A deployment warhead that destroys an attack target,
The tip,
A shaft to which the rear end and one end of the tip are connected;
One or more glaze members in which one end of the shaft and one end in the longitudinal direction are connected at a connecting portion;
A locking device for maintaining the glaze member in parallel with the axis in the longitudinal direction;
The glaze member has a biasing mechanism that expands in a direction perpendicular to the axis with the connection portion as a fulcrum,
The deployment device has a release mechanism for releasing the maintenance.
前記ロック装置は、前記攻撃対象物認識センサからの前記展開を指示する展開信号を受信する展開信号受信部材を有し、
前記展開信号は、前記先端部が攻撃対象物までの距離が所定の値となった場合に、前記攻撃対象物認識センサから前記展開信号受信部材に送信される、ことを特徴とする請求項１に記載の展開弾頭。 The tip has an attack object recognition sensor that measures the distance to the attack object;
The locking device includes a deployment signal receiving member that receives a deployment signal that instructs the deployment from the attack object recognition sensor,
The deployment signal is transmitted from the attack target recognition sensor to the deployment signal receiving member when the distance between the tip portion and the attack target reaches a predetermined value. The deployment warhead described in.
前記発射信号は、前記先端部が攻撃対象物までの距離が所定の値となった場合に、該先端部に取り付けられた攻撃対象物認識センサから前記発射機構に送信される、ことを特徴とする請求項２に記載の展開弾頭。 The firing mechanism has a firing signal receiving member that receives a firing signal from the tip,
The firing signal is transmitted to the launching mechanism from an attack target recognition sensor attached to the tip when the distance between the tip and the attack target reaches a predetermined value. The deployment warhead according to claim 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2011067056A JP2012202597A (en) | 2011-03-25 | 2011-03-25 | Deployed warhead |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2011067056A JP2012202597A (en) | 2011-03-25 | 2011-03-25 | Deployed warhead |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2012202597A true JP2012202597A (en) | 2012-10-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| JP2011067056A Withdrawn JP2012202597A (en) | 2011-03-25 | 2011-03-25 | Deployed warhead |
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2011
- 2011-03-25 JP JP2011067056A patent/JP2012202597A/en not_active Withdrawn
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 20140603 |