JP2729868B2 - Flying object loading structure of flying object launcher - Google Patents
Flying object loading structure of flying object launcherInfo
- Publication number
- JP2729868B2 JP2729868B2 JP32498291A JP32498291A JP2729868B2 JP 2729868 B2 JP2729868 B2 JP 2729868B2 JP 32498291 A JP32498291 A JP 32498291A JP 32498291 A JP32498291 A JP 32498291A JP 2729868 B2 JP2729868 B2 JP 2729868B2
- Authority
- JP
- Japan
- Prior art keywords
- projectile
- piston
- stopper
- flying object
- guide hole
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
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- Portable Nailing Machines And Staplers (AREA)
Description
【0001】[0001]
【産業上の利用分野】本発明は、液体燃料を使用して飛
翔体を発射する飛翔体発射装置に関し、詳細には、飛翔
体発射装置の砲身に飛翔体を装填する飛翔体装填構造に
関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a projectile launching device for projecting a projectile using a liquid fuel, and more particularly to a projectile loading structure for loading a projectile onto a barrel of the projectile launching device.
【0002】[0002]
【従来の技術】従来、液体燃料を使用して飛翔体を発射
する飛翔体発射装置において、砲身の後部に砲尾を取付
け、砲尾の後部を鎖栓で密封し、砲尾の内部にピストン
機構を設けて燃料室と燃焼室とに仕切り、燃焼時にピス
トン機構の作動により燃料室から燃焼室に液体燃料を噴
射し、液体燃料の燃焼による燃焼ガス圧により砲身内の
飛翔体を発射するようにしたものが各種提案されている
(例、実開平2−127991号公報、特開平2−21
9991号公報等参照)。2. Description of the Related Art Conventionally, in a projectile launching device that uses a liquid fuel to launch a projectile, a breech is attached to the rear of the gun barrel, the rear of the breech is sealed with a chain stopper, and a piston is mounted inside the breech. A mechanism is provided to partition into a fuel chamber and a combustion chamber. During combustion, the piston mechanism operates to inject liquid fuel from the fuel chamber into the combustion chamber, and to fire a projectile in the barrel by the combustion gas pressure due to the combustion of the liquid fuel. Various proposals have been made (for example, see Japanese Utility Model Laid-Open No. 2-127991,
No. 9991).
【0003】[0003]
【発明が解決しようとする課題】ところで、飛翔体を発
射する毎に新規に飛翔体を砲身に装填するが、従来の飛
翔体発射装置については、砲身の後部に砲尾が取付けら
れているため、その都度砲尾を砲身から取外し、飛翔体
を砲身に直接装填することが一般に行なわれている。と
ころが、砲尾が大型で重量物であり、その取外し作業が
繁雑で長時間を要するため、飛翔体の装填作業を円滑か
つ迅速に行い難いという問題点がある。By the way, each time a projectile is fired, a new projectile is loaded on the barrel. However, in the conventional projectile launching apparatus, the breech is attached to the rear of the barrel. In each case, it is common practice to remove the breech from the barrel and load the projectile directly into the barrel. However, since the breech is large and heavy, and its removal operation is complicated and takes a long time, there is a problem that it is difficult to perform the operation of loading the flying object smoothly and quickly.
【0004】装填作業を円滑かつ迅速に行うために、砲
尾を開閉装置を介して砲身に取付け、開閉装置の作動に
より砲尾を開き、飛翔体を砲身に装填するようにした飛
翔体装填構造が提案されている。ところが、上記のよう
に砲尾が大型で重量物であるため、開閉装置についても
大型で高馬力のものが必要とされ、飛翔体発射装置自体
が大型化するという問題点がある。[0004] In order to perform the loading operation smoothly and quickly, the breech is mounted on the barrel via the opening and closing device, the breech is opened by the operation of the opening and closing device, and the flying body is loaded on the barrel. Has been proposed. However, since the breech is large and heavy as described above, a large and high horsepower opening / closing device is required, and there is a problem that the flying object launching device itself becomes large.
【0005】本発明は、上記従来の問題点を解決するた
めになされたものであり、その課題は、飛翔体発射装置
を大型化する必要がなく、飛翔体を円滑かつ迅速に装填
し得る飛翔体発射装置の飛翔体装填構造を提供すること
にある。SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned conventional problems, and an object of the present invention is to provide a flying device capable of loading a flying object smoothly and quickly without having to increase the size of the projectile launching device. It is an object of the present invention to provide a flying object loading structure for a body launching device.
【0006】[0006]
【課題を解決するための手段】上記課題を解決するため
に、本発明では、砲身の後部に砲尾を取付け、砲尾の後
部を鎖栓で密封し、砲尾の内部にピストン機構を設けて
燃料室と燃焼室とに仕切り、燃焼時にピストン機構の作
動により燃料室から燃焼室に液体燃料を噴射し、液体燃
料の燃焼による燃焼ガス圧により砲身内の飛翔体を発射
するようにした飛翔体発射装置の飛翔体装填構造であつ
て、ピストン機構は鎖栓に貫通状に設けたピストンを有
し、ピストンに砲身と同軸に飛翔体案内孔を貫通状に形
成し、飛翔体案内孔に挿入した飛翔体を砲身の飛翔体起
動位置まで押込むとともに飛翔体案内孔を緊塞する内側
鎖栓をピストンに着脱可能に固定するようになつてい
る。In order to solve the above problems, according to the present invention, a breech is attached to a rear part of a barrel, a rear part of the breech is sealed with a stopper, and a piston mechanism is provided inside the breech. The fuel is divided into a fuel chamber and a combustion chamber, and during combustion, liquid fuel is injected from the fuel chamber into the combustion chamber by the operation of a piston mechanism, and the projectile in the barrel is fired by the combustion gas pressure due to the combustion of the liquid fuel. A projectile loading structure of a body launching device, wherein a piston mechanism has a piston penetratingly provided in a chain stopper, and a projectile guiding hole is formed in the piston coaxially with a barrel, and a projecting hole is formed in the projecting hole. The inserted projectile is pushed down to the projectile launching position of the gun barrel, and the inner stopper that closes the projectile guide hole is detachably fixed to the piston.
【0007】ピストン機構は、鎖栓に貫通状に設けたピ
ストンが進退可能であり、ピストンノーズにより燃料室
と燃焼室とに仕切るようになつたもの、鎖栓に貫通状に
設けたピストンを内側ピストンとし、内側ピストンの外
方に外側ピストンを設け、両者のピストンノーズを係合
して燃料室と燃焼室とに仕切るようになつたもの等でも
よい。ピストンは、飛翔体を飛翔体案内孔に落下挿入す
る飛翔体挿入口を後部側壁に設けたものでもよい。[0007] The piston mechanism is such that a piston provided in a spigot is capable of moving forward and backward, and is divided into a fuel chamber and a combustion chamber by a piston nose. The piston may be provided with an outer piston provided outside the inner piston, and the piston nose of both may be engaged to partition the fuel chamber and the combustion chamber. The piston may be provided with a projectile insertion port for dropping and inserting the projectile into the projectile guide hole on the rear side wall.
【0008】内側鎖栓は、飛翔体案内孔に係合する鎖栓
本体と、飛翔体案内孔を緊塞する緊塞機構と、鎖栓本体
をピストンに着脱可能に固定する鎖栓ロツク機構とを備
えたものであつてもよい。The inner stopper includes a stopper main body engaged with the flying object guide hole, a closing mechanism for closing the flying object guide hole, and a stopper locking mechanism for detachably fixing the stopper body to the piston. May be provided.
【0009】緊塞機構は、鎖栓本体に一体的に設け、弾
性的に外方に拡大し飛翔体案内孔に密着する自緊シール
と、自緊シールの内側に密着して設け、自緊シールを弾
性的に押圧する緊塞用弾性体と、緊塞用弾性体と鎖栓本
体を貫通して設け、緊塞用弾性体を後方に押圧する鎖栓
ロツドと、鎖栓ロツドの前後位置を調整する鎖栓ロツド
保持機構とを備えたものであつてもよい。The closing mechanism is provided integrally with the stopper body, and is provided with a self-tightening seal which expands elastically outward and is in close contact with the flying object guide hole, and is provided in close contact with the inside of the self-tightening seal. A closing elastic body that elastically presses the seal, a stopper rod that is provided through the closing elastic body and the stopper body, and presses the closing elastic body rearward, and front and rear positions of the stopper rod. May be provided with a stopper rod holding mechanism for adjusting the pressure.
【0010】[0010]
【実施例】本発明の実施例を図により説明する。図1は
第1実施例の概念的な説明図で、1は飛翔体発射装置、
2は砲身、3は弾丸等の飛翔体、4は砲尾である。BRIEF DESCRIPTION OF THE DRAWINGS FIG. FIG. 1 is a conceptual explanatory view of a first embodiment, where 1 is a flying object launching device,
2 is a gun barrel, 3 is a projectile such as a bullet, and 4 is a breech.
【0011】砲尾4は、その内部に燃料室5と燃焼室6
が形成されており、前端を砲身2にねじ結合し、後端に
鎖栓7をねじ結合し、中間に燃料室5と燃焼室6とに仕
切るピストン機構のピストン8を前後動可能に設けてい
る。燃料室5は、燃焼室6よりも大径で、その壁面が所
定の形状に形成されており、後述するようにピストン8
の後退時にピストンノーズ13との間で間隙を生じ、燃
料室5内の液体燃料を所定割合で噴射する漏孔を形成す
るようになつている。燃料室5には燃料注入口9が形成
されており、発射毎に液体燃料を注入し充填するように
なつている。燃焼室6には、点火装置10が接続され、
またその壁面には逆火安全溝11が形成されている。こ
の逆火安全溝11は、燃料室5に燃焼室6から火炎が入
り込む逆火現象が生じた時に、燃料室5内の液体燃料の
瞬間的燃焼(爆轟)を抑制するためのものであり、燃料
室5の燃焼ガス圧を解放するようになつている。これに
より、燃料室5内の液体燃料の爆轟を抑制するととも
に、爆轟による砲尾4、ピストン8等の破損を防止する
ことができる。The breech 4 has a fuel chamber 5 and a combustion chamber 6 therein.
The front end is screw-connected to the barrel 2, the rear end is screw-connected to the chain stopper 7, and a piston 8 of a piston mechanism that partitions the fuel chamber 5 and the combustion chamber 6 is provided in the middle so as to be movable back and forth. I have. The fuel chamber 5 has a larger diameter than the combustion chamber 6 and has a predetermined wall surface.
At the time of retreat, a gap is formed between the piston nose 13 and a leak hole for injecting the liquid fuel in the fuel chamber 5 at a predetermined ratio. A fuel injection port 9 is formed in the fuel chamber 5 so that liquid fuel is injected and filled every time the fuel is fired. An ignition device 10 is connected to the combustion chamber 6,
A backfire safety groove 11 is formed on the wall surface. The flashback safety groove 11 is for suppressing instantaneous combustion (detonation) of liquid fuel in the fuel chamber 5 when a flashback phenomenon occurs in which a flame enters the fuel chamber 5 from the combustion chamber 6. The pressure of the combustion gas in the fuel chamber 5 is released. Thus, the detonation of the liquid fuel in the fuel chamber 5 can be suppressed, and damage to the breech 4, the piston 8, and the like due to the detonation can be prevented.
【0012】鎖栓7は、上記のように砲尾4にねじ結合
されており、鎖栓駆動装置12により回転駆動すること
により前後方向に移動するようになつている。そして、
鎖栓7が燃料室5の後部を区画するものであることか
ら、鎖栓7の前後方向の移動により燃料室5の容積が変
更することになり、飛翔体3の飛翔距離、初速度等の飛
翔特性に応じた液体燃料の貯留量を調整することができ
る。The chain stopper 7 is screwed to the breech 4 as described above, and is driven to rotate by the chain stopper driving device 12 so as to move in the front-rear direction. And
Since the stopper 7 partitions the rear part of the fuel chamber 5, the volume of the fuel chamber 5 is changed by the forward and backward movement of the stopper 7, and the flying distance of the flying object 3, the initial velocity, and the like are changed. The storage amount of the liquid fuel can be adjusted according to the flight characteristics.
【0013】ピストン8は、ピストンノーズ13が燃焼
室6の壁面に密封状で係合し、ピストン軸14が鎖栓7
に密封状で前後動可能に支持されており、ピストン軸1
4にピストン駐退機15を連結し、燃焼直前にはピスト
ンノーズ13が燃焼室6の壁面に密封状で係合する始動
位置に保持するようになつている。ピストン軸14には
砲身2と同軸に飛翔体3を挿入案内する飛翔体案内孔1
6を貫通状に形成し、ピストン軸14の後部側壁に飛翔
体3を飛翔体案内孔16に落下挿入する飛翔体挿入口1
7を形成し、飛翔体案内孔16に内側鎖栓18を装着し
て緊塞するようになつており、これにより飛翔体装填構
造が構成されている。The piston 8 has a piston nose 13 hermetically engaged with the wall of the combustion chamber 6 and a piston shaft 14
The piston shaft 1
4 is connected to a piston parking / removal unit 15 so that the piston nose 13 is maintained at a starting position in which the piston nose 13 is engaged with the wall surface of the combustion chamber 6 in a sealing manner immediately before combustion. The projectile guide hole 1 for inserting and guiding the projectile 3 coaxially with the barrel 2 is provided on the piston shaft 14.
6 is formed in a penetrating shape, and a projectile insertion port 1 for dropping and inserting the projectile 3 into the projectile guide hole 16 on the rear side wall of the piston shaft 14.
7 is formed, and the inside stopper 18 is attached to the projectile guide hole 16 so as to be tightly closed, thereby constituting a projectile loading structure.
【0014】内側鎖栓18は、飛翔体案内孔16に挿入
した飛翔体3を砲身2の飛翔体起動位置に押込み得る寸
法を有する鎖栓本体19を備え、鎖栓本体19に飛翔体
案内孔16を緊塞する緊塞機構20と、ピストン8に着
脱可能に固定する鎖栓ロツク機構21が設けられてい
る。The inner stopper 18 is provided with a stopper body 19 having a size capable of pushing the projectile 3 inserted into the projectile guide hole 16 into the projectile launching position of the gun barrel 2. A closing mechanism 20 for closing the 16 and a stopper lock mechanism 21 for detachably fixing to the piston 8 are provided.
【0015】緊塞機構20は、鎖栓本体19の前端部に
外方に弾性変形可能なリツプ構造の自緊シール22を一
体的に形成し、自緊シール22の内側にゴム材等からな
る緊塞用弾性体23を配置し、緊塞用弾性体23を鎖栓
本体19に貫通して装着した鎖栓ロツド24により後方
に押圧するように支持し、鎖栓ロツド24を鎖栓本体1
9に鎖栓ロツド保持機構25で連結し、鎖栓ロツド24
を鎖栓本体19に対して前後方向に位置調整するように
なつている。そして、緊塞作動については、鎖栓ロツド
保持機構25により鎖栓ロツド24を後方に移動し、緊
塞用弾性体23を後方に押圧して外方に変形し、これに
より自緊シール22が外方に拡大し、飛翔体案内孔16
に密着して緊塞する。燃焼時には、燃焼ガス圧により自
緊シール22が外方に押圧され、飛翔体案内孔16をさ
らに強く緊塞することになる。一方、緊塞解除作動につ
いては、鎖栓ロツド保持機構25により鎖栓ロツド24
を前方に移動すると、緊塞用弾性体23の押圧が解除さ
れ、自緊シール22が弾性的に復元し飛翔体案内孔16
から離れ、緊塞を解除することになる。The closing mechanism 20 is formed integrally with a self-sealing seal 22 having a lip structure that can be elastically deformed outward at the front end of the stopper body 19, and is made of a rubber material or the like inside the self-sealing seal 22. An elastic body 23 for closing is arranged, and the elastic body 23 for closing is supported so as to be pressed backward by a stopper rod 24 which is inserted through and attached to the stopper body 19, and the stopper rod 24 is supported by the stopper body 1.
9 with a lock rod holding mechanism 25, and a lock rod 24.
Is adjusted in the front-rear direction with respect to the stopper body 19. As for the closing operation, the stopper rod 24 is moved rearward by the stopper rod holding mechanism 25, and the closing elastic body 23 is pressed rearward to be deformed outward. The flying object guide hole 16 expands outward.
Closely adhered to. At the time of combustion, the self-tightening seal 22 is pressed outward by the combustion gas pressure, thereby closing the flying object guide hole 16 more strongly. On the other hand, with regard to the release operation, the stopper rod holding mechanism 25 operates the stopper rod 24.
Is moved forward, the pressing of the closing elastic body 23 is released, the self-tightening seal 22 is elastically restored, and the flying object guide hole 16 is restored.
You will be released from the custody.
【0016】なお、鎖栓ロツド24は、前端部が前方外
向きの傾斜面を有する円錐台状であり、傾斜面が緊塞用
弾性体23に密着して設けられている。また、前端面が
自緊シール22より前方に突出して設けられ、飛翔体3
の装填時に飛翔体3に当接するようになつている。鎖栓
ロツド保持機構25は、鎖栓ロツド24を後方に弾性付
勢する圧縮バネ26と、鎖栓ロツド24の前後位置を調
節するキヤツプ27とを鎖栓ロツド24と鎖栓本体19
との間に設けてなるものであるが、鎖栓ロツド24を鎖
栓本体19に対して前後方向に位置調整可能に連結する
構造、例えば、鎖栓ロツド24と鎖栓本体19とをねじ
結合するようにしたものでもよい。The stopper rod 24 is shaped like a truncated cone having a front outwardly inclined surface facing forward and the inclined surface is provided in close contact with the elastic body 23 for closing. Further, the front end face is provided so as to protrude forward from the self-tightening seal 22, and the flying object 3 is provided.
The abutment comes into contact with the flying object 3 at the time of loading. The lock rod holding mechanism 25 includes a compression spring 26 that elastically urges the lock rod 24 rearward and a cap 27 that adjusts the front and rear positions of the lock rod 24.
The stopper rod 24 is connected to the stopper body 19 so that the position thereof can be adjusted in the front-rear direction. For example, the stopper rod 24 and the stopper body 19 are screwed together. It is also possible to use one that does so.
【0017】鎖栓ロツク機構21は、鎖栓本体19に設
けたロツク腕28をロツクピン29でピストン軸14に
連結するようになつているが、他の手段によつてもよ
い。Although the lock stopper mechanism 21 connects the lock arm 28 provided on the stopper main body 19 to the piston shaft 14 with the lock pin 29, other means may be used.
【0018】第1実施例は上記のように構成されてお
り、発射作動とともに飛翔体3の装填作業を次に説明す
る。図1に示す状態において、砲身2の飛翔体起動位置
に飛翔体3が気密状に装填されており、燃焼室6は飛翔
体3とピストン8とにより気密状になつている。点火装
置10を作動すると燃焼室6内の圧力が上昇し、これに
よりピストン8がピストン駐退機15に抗して後退し、
ピストンノーズ13と燃料室5の壁面との間に間隙(漏
孔)が生じる。一方、燃料室5の液体燃料がピストンノ
ーズ13の後退により加圧され、上記間隙から燃焼室6
に噴射し、燃焼室6で燃焼して高圧の燃焼ガス圧を発生
し、飛翔体3を発射する。The first embodiment is configured as described above, and the loading operation of the flying object 3 together with the firing operation will be described below. In the state shown in FIG. 1, the flying object 3 is hermetically loaded at the projectile starting position of the barrel 2, and the combustion chamber 6 is made airtight by the flying object 3 and the piston 8. When the ignition device 10 is actuated, the pressure in the combustion chamber 6 increases, whereby the piston 8 retreats against the piston parking unit 15,
A gap (leakage) occurs between the piston nose 13 and the wall surface of the fuel chamber 5. On the other hand, the liquid fuel in the fuel chamber 5 is pressurized by the retraction of the piston nose 13, and
And the fuel is combusted in the combustion chamber 6 to generate a high combustion gas pressure, and the projectile 3 is fired.
【0019】発射後、新規に飛翔体3を装填するが、ま
ずピストン駐退機15によりピストン8を図1に示す始
動位置まで前進し、燃料室5と燃焼室6とを密封状に仕
切る。次いで、鎖栓ロツド保持機構25により鎖栓ロツ
ド24を前進し、緊塞機構20を緊塞解除状態にする。
すなわち、キヤツプ27を回転し前進すると、鎖栓ロツ
ド24の後端がキヤツプ27により押され、圧縮バネ2
6に抗して前進する。鎖栓ロツド24の前進により緊塞
用弾性体23を押圧する力が減少し、緊塞用弾性体23
と自緊シール22が弾性的に復元し、その緊塞状態が解
除される。After the launch, the flying object 3 is newly loaded. First, the piston 8 is advanced to the starting position shown in FIG. 1 by the piston parking / retreating device 15, and the fuel chamber 5 and the combustion chamber 6 are partitioned in a sealed manner. Next, the stopper rod 24 is advanced by the stopper rod holding mechanism 25, and the closing mechanism 20 is brought into the closed state.
That is, when the cap 27 is rotated and moved forward, the rear end of the stopper plug 24 is pushed by the cap 27 and the compression spring 2
Go ahead against 6. As the stopper rod 24 advances, the force for pressing the closing elastic body 23 decreases, and the closing elastic body 23
Then, the self-tightening seal 22 is elastically restored, and the closed state is released.
【0020】緊塞機構20を緊塞解除状態にした後、ロ
ツクピン29を抜いてロツク腕28とピストン8との連
結を外し、鎖栓ロツク機構21を解除する。そして、内
側鎖栓18を飛翔体案内孔16から抜出し、飛翔体3を
飛翔体挿入口17から飛翔体案内孔16に挿入する。飛
翔体3を飛翔体案内孔16に挿入した後、内側鎖栓18
を飛翔体案内孔16に挿入し飛翔体3を押込む。これに
より、飛翔体3は、飛翔体案内孔16内を勢いよく滑走
し、砲身2の飛翔体起動位置に装填される。飛翔体3を
装填した後、鎖栓ロツク機構21により内側鎖栓18を
ピストン8に固定し、鎖栓ロツド保持機構25により鎖
栓ロツド24を後方に移動し、緊塞機構20を緊塞作動
する。自緊シール22は、緊塞用弾性体23に押圧され
飛翔体案内孔16に密着するが、外方に弾性変形可能な
リツプ構造であるため、液体燃料の燃焼時に発生する燃
焼ガス圧によつても外方に拡大し、飛翔体案内孔16に
強く密着し緊塞する。以上のようにして飛翔体3を装填
した後、液体燃料を燃料注入口9から燃料室に注入し、
図1に示す発射直前状態にする。After the closing mechanism 20 is released from the closed state, the locking pin 29 is removed to disconnect the locking arm 28 from the piston 8, and the stopper locking mechanism 21 is released. Then, the inner stopper 18 is pulled out from the projectile guide hole 16, and the projectile 3 is inserted into the projectile guide hole 16 from the projectile insertion port 17. After the projectile 3 is inserted into the projectile guide hole 16, the inner stopper 18
Is inserted into the flying object guide hole 16 and the flying object 3 is pushed. As a result, the flying object 3 slides vigorously in the flying object guide hole 16 and is loaded at the projectile starting position of the barrel 2. After the projectile 3 is loaded, the inner stopper 18 is fixed to the piston 8 by the stopper lock mechanism 21, the stopper rod 24 is moved backward by the stopper lock holding mechanism 25, and the closing mechanism 20 is closed. I do. The self-tightening seal 22 is pressed by the closing elastic body 23 and closely adheres to the flying object guide hole 16, but has a lip structure capable of elastically deforming outward. In this case, it also expands outward, and tightly adheres to and closes to the flying object guide hole 16. After loading the flying object 3 as described above, liquid fuel is injected into the fuel chamber from the fuel inlet 9,
The state immediately before firing shown in FIG. 1 is set.
【0021】次ぎに、図2に示す第2実施例は、燃料室
5と燃焼室6とに仕切るピストン機構が内側ピストン3
0と外側ピストン31からなる飛翔体発射装置1に適用
したものである。内側ピストン30は、ピストンノーズ
32の端部が後方外向きに傾斜したテーパ面であり、ピ
ストン軸33を鎖栓7に密封状に装着し、前後動するよ
うになつている。外側ピストン31は、ピストンノーズ
34の端部が前方外向きに傾斜したテーパ面であり、内
側ピストンのピストンノーズ32に当接して燃料室5と
燃焼室6とに仕切るように砲尾4の壁面に案内支持され
るとともに、後部が砲尾4と鎖栓7で画成され、窒素ガ
ス等を収納した圧力室35に装着されている。そして、
内側ピストン30と外側ピストン31は、各ピストンノ
ーズ32、34の受圧面積比、燃焼ガス圧とピストン駐
退機15及び圧力室35との圧力バランス等により、前
者30の方が速く後退するようになつている。これによ
り、各ピストンノーズ32、34間に間隙(漏孔)が生
じ、この間隙を通つて燃料室5から液体燃料が燃焼室6
に噴射する。また、飛翔体の装填構造については、内側
ピストンのピストン軸33に飛翔体案内孔16を形成
し、飛翔体案内孔16に内側鎖栓18を装着してなり、
第1実施例と同様に飛翔体3を装填するようになつてい
る。Next, in a second embodiment shown in FIG. 2, the piston mechanism for partitioning the fuel chamber 5 and the combustion chamber 6
This is applied to a flying object launching device 1 comprising a zero and an outer piston 31. The inner piston 30 has a tapered surface in which the end of a piston nose 32 is inclined rearward and outward, and the piston shaft 33 is mounted on the stopper 7 in a sealed manner so as to move back and forth. The outer piston 31 has a tapered surface in which an end of a piston nose 34 is inclined outward and forward, and a wall surface of the breech 4 so as to abut the piston nose 32 of the inner piston to partition the fuel chamber 5 and the combustion chamber 6. And a rear part thereof is defined by a breech 4 and a stopper 7 and is mounted in a pressure chamber 35 containing nitrogen gas or the like. And
The inner piston 30 and the outer piston 31 are set so that the former 30 retreats faster due to the pressure receiving area ratio of each piston nose 32, 34, the combustion gas pressure and the pressure balance between the piston parking and closing machine 15 and the pressure chamber 35. I'm sorry. As a result, a gap (leakage) is created between the piston nose 32, 34, and liquid fuel is discharged from the fuel chamber 5 through the gap to the combustion chamber 6 through the gap.
Spray. Further, with respect to the loading structure of the flying object, the flying object guide hole 16 is formed in the piston shaft 33 of the inner piston, and the inner stopper 18 is attached to the flying object guide hole 16,
The flying object 3 is loaded as in the first embodiment.
【0022】図3に示す第3実施例は、内側ピストン3
0を鎖栓7に固定機構36により固定し、外側ピストン
31を砲尾4の壁面に案内支持し、外側ピストン31の
移動により液体燃料を噴射するようにした点、各ピスト
ンノーズ32、34の端部が円筒面で係合するようにし
た点を除けば、飛翔体の装填構造も含めて第2実施例と
同様に構成されている。The third embodiment shown in FIG.
0 is fixed to the stopper 7 by the fixing mechanism 36, the outer piston 31 is guided and supported on the wall surface of the breech 4, and the liquid fuel is injected by the movement of the outer piston 31. The configuration is the same as that of the second embodiment, including the structure for loading a flying object, except that the ends are engaged with a cylindrical surface.
【0023】[0023]
【発明の効果】本発明によれば、飛翔体装填構造を鎖栓
に貫通状に設けたピストンに設けていることから、飛翔
体発射装置を大型化する必要がない。また、飛翔体の装
填作業は、飛翔体を飛翔体案内孔に挿入し、内側鎖栓に
より押込んで砲身の飛翔体起動位置に装填し、飛翔体案
内孔を緊塞機構により緊塞して燃焼室を気密状に保持す
ることにより行う。従つて、発射機能を何等損ねること
がなく、従来よりもはるかに小さい操作力で円滑かつ迅
速に装填することが可能になつた。According to the present invention, since the projectile loading structure is provided on the piston penetrating the chain stopper, there is no need to increase the size of the projectile launching device. The loading operation of the projectile is performed by inserting the projectile into the projectile guide hole, pushing it in with the inner stopper and loading it at the projectile launching position of the gun barrel, closing the projectile guide hole by the closing mechanism, and burning. This is done by keeping the chamber airtight. Therefore, the firing function can be smoothly and quickly loaded with much smaller operation force than before without impairing the firing function.
【図1】本発明の第1実施例を説明する縦断面図であ
る。FIG. 1 is a longitudinal sectional view for explaining a first embodiment of the present invention.
【図2】本発明の第2実施例を説明する縦断面図であ
る。FIG. 2 is a longitudinal sectional view illustrating a second embodiment of the present invention.
【図3】本発明の第3実施例を説明する縦断面図であ
る。FIG. 3 is a longitudinal sectional view illustrating a third embodiment of the present invention.
1 飛翔体発射装置 2 砲身 3 飛翔体 4 砲尾 5 燃料室 6 燃焼室 7 鎖栓 8 ピストン 16 飛翔体案内孔 17 飛翔体挿入口 18 内側鎖栓 19 鎖栓本体 20 緊塞機構 21 鎖栓ロツク機構 22 自緊シール 23 緊塞用弾性体 24 鎖栓ロツド 25 鎖栓ロツド保持機構 30 内側ピストン 31 外側ピストン REFERENCE SIGNS LIST 1 flying object launching device 2 gun barrel 3 flying object 4 breech 5 fuel chamber 6 combustion chamber 7 stopper 8 piston 16 flying object guide hole 17 projectile insertion port 18 inner stopper 19 stopper stopper body 20 closing mechanism 21 stopper stopper Mechanism 22 Self-tightening seal 23 Elastic body for closing 24 Chain stopper rod 25 Chain stopper rod holding mechanism 30 Inner piston 31 Outer piston
Claims (6)
を鎖栓で密封し、砲尾の内部にピストン機構を設けて燃
料室と燃焼室とに仕切り、燃焼時にピストン機構の作動
により燃料室から燃焼室に液体燃料を噴射し、液体燃料
の燃焼による燃焼ガス圧により砲身内の飛翔体を発射す
る飛翔体発射装置の飛翔体装填構造であつて、ピストン
機構は鎖栓に貫通状に設けたピストンを有し、ピストン
に砲身と同軸に飛翔体案内孔を貫通状に形成し、飛翔体
案内孔に挿入した飛翔体を砲身の飛翔体起動位置に押込
むとともに飛翔体案内孔を緊塞する内側鎖栓をピストン
に着脱可能に固定することを特徴とする飛翔体発射装置
の飛翔体装填構造。1. A breech is attached to the rear of the barrel, the rear of the breech is sealed with a stopper, and a piston mechanism is provided inside the breech to partition into a fuel chamber and a combustion chamber. Injecting liquid fuel from the fuel chamber into the combustion chamber, and firing the projectile in the gun barrel by the combustion gas pressure due to the combustion of the liquid fuel, the projectile loading structure of the projectile launcher, the piston mechanism penetrates the stopper A projectile guide hole is formed in the piston coaxially with the barrel, and the projectile inserted into the projectile guide hole is pushed into the projectile launching position of the gun barrel and the projectile guide hole is formed. A projectile loading structure for a projectile launching device, characterized in that an inner spigot that closes off the plug is detachably fixed to a piston.
ピストンが進退可能であり、ピストンノーズにより燃料
室と燃焼室とに仕切るようになつている請求項1記載の
飛翔体発射装置の飛翔体装填構造。2. The projectile launching apparatus according to claim 1, wherein the piston mechanism is configured such that a piston provided in a penetrating manner in the stopper can move forward and backward, and separates into a fuel chamber and a combustion chamber by a piston nose. Flying object loading structure.
ピストンを内側ピストンとし、内側ピストンの外方に外
側ピストンを設け、両者のピストンノーズを係合して燃
料室と燃焼室とに仕切るようになつている請求項1記載
の飛翔体発射装置の飛翔体装填構造。3. A piston mechanism, wherein a piston provided in a penetrating manner in a stopper is used as an inner piston, an outer piston is provided outside the inner piston, and both piston nose are engaged to form a fuel chamber and a combustion chamber. 2. The flying object loading structure of the flying object launching device according to claim 1, wherein the projectile is configured to partition.
下挿入する飛翔体挿入口を後部側壁に設けてなるもので
ある請求項1、2又は3記載の飛翔体発射装置の飛翔体
装填構造。4. A projectile loading device for a projectile launching device according to claim 1, wherein the piston has a projectile insertion opening for dropping and inserting the projectile into the projectile guide hole on the rear side wall. Construction.
栓本体と、飛翔体案内孔を緊塞する緊塞機構と、鎖栓本
体をピストンに着脱可能に固定する鎖栓ロツク機構とを
備えている請求項1、2、3又は4記載の飛翔体発射装
置の飛翔体装填構造。5. An inner stopper according to claim 1, wherein said stopper is a stopper body for engaging said projectile guide hole, a closing mechanism for closing said projectile guide hole, and a stopper lock for detachably fixing said stopper body to said piston. The projectile loading structure of the projectile launching device according to claim 1, further comprising a mechanism.
弾性的に外方に拡大して飛翔体案内孔に密着する自緊シ
ールと、自緊シールの内側に密着して設け、自緊シール
を弾性的に押圧する緊塞用弾性体と、緊塞用弾性体と鎖
栓本体を貫通して設け、緊塞用弾性体を後方に押圧する
鎖栓ロツドと、鎖栓ロツドの前後位置を調節する鎖栓ロ
ツド保持機構とを備えている請求項5記載の飛翔体発射
装置の飛翔体装填構造。6. The closing mechanism is provided integrally with the stopper body,
A self-sealing seal that elastically expands outward and closely adheres to the flying object guide hole; a sealing elastic body that is provided closely inside the self-sealing seal and elastically presses the self-sealing seal; 6. A stopper rod provided to penetrate the elastic body for use and the stopper body to press the elastic body for closing backward, and a stopper rod holding mechanism for adjusting a front and rear position of the stopper rod. A flying object loading structure of the flying object launching device according to the above description.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP32498291A JP2729868B2 (en) | 1991-10-04 | 1991-10-04 | Flying object loading structure of flying object launcher |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP32498291A JP2729868B2 (en) | 1991-10-04 | 1991-10-04 | Flying object loading structure of flying object launcher |
Publications (2)
Publication Number | Publication Date |
---|---|
JPH0599591A JPH0599591A (en) | 1993-04-20 |
JP2729868B2 true JP2729868B2 (en) | 1998-03-18 |
Family
ID=18171809
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP32498291A Expired - Lifetime JP2729868B2 (en) | 1991-10-04 | 1991-10-04 | Flying object loading structure of flying object launcher |
Country Status (1)
Country | Link |
---|---|
JP (1) | JP2729868B2 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN115342685A (en) * | 2022-07-30 | 2022-11-15 | 成都云鼎智控科技有限公司 | Assembly structure and transmitting device formed by same |
-
1991
- 1991-10-04 JP JP32498291A patent/JP2729868B2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
JPH0599591A (en) | 1993-04-20 |
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