EP0541412B1 - Cargo munition ejecting a submunition by means of a piston - Google Patents
Cargo munition ejecting a submunition by means of a piston Download PDFInfo
- Publication number
- EP0541412B1 EP0541412B1 EP92402727A EP92402727A EP0541412B1 EP 0541412 B1 EP0541412 B1 EP 0541412B1 EP 92402727 A EP92402727 A EP 92402727A EP 92402727 A EP92402727 A EP 92402727A EP 0541412 B1 EP0541412 B1 EP 0541412B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- piston
- shell
- spool
- shell according
- payload
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
- F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
- F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile
Definitions
- the technical field of the present invention is that of cargo shells carrying a payload, for example one or more submunitions, and ejecting this load on the trajectory by means of a piston pushed by a gas pressure.
- Such a shell is composed in a known manner of a body provided at the rear of a belt.
- a warhead and a base are respectively screwed to the front and rear ends of the body.
- the interior of the body carries a payload composed for example of at least one submunition.
- a charge of unloading bootable by a rocket In the head of the warhead is housed a charge of unloading bootable by a rocket.
- the rocket initiates the loading charge which generates a gas pressure.
- the latter axially pushes a piston which drives the payload and the base for their ejection from the shell.
- the piston must separate from the payload after the ejection of the latter without coming to disturb its trajectory.
- the invention relates to a cargo shell intended to transport a payload and constituted by a body closed at one of its ends by a base and at the other by a warhead inside which is disposed a pyrotechnic composition generating gas intended to come to act on a piston at the time of ejection of the charge, shell characterized in that it comprises means ensuring a connection between the piston and the shell after the ejection of the payload.
- connection means comprise at least one cable, one end of which is secured to the shell at the level of the warhead and the other end of which is secured to a coil fixed to the piston, the cable being wound on the spool.
- the axis of the coil is offset relative to the axis of the shell, which avoids interference between the piston and the payload in the event of cable breakage.
- the shell comprises at least two cables winding on at least two coils regularly distributed angularly on the piston.
- the axis of the reel coincides with the axis of the shell.
- the coil (s) may be formed by one or more cylindrical extensions of the piston.
- the coil is temporarily held, for example by glue point, on a counterbore carried by a ring secured to the warhead, the piston carrying means allowing its attachment to the coil.
- the means for attaching the piston to the coil may comprise a deformable elastic ring placed in a groove in the piston.
- the coil will carry a conical profile intended to cause the elastic ring to be erased in its groove when the piston is put in place, as well as a clearance intended to receive the elastic ring which thus fixes the piston and the coil.
- a cargo shell 1 is conventionally constituted by a body 2 provided at the rear with a belt 3. At the rear end of the body 2 is screwed a base 4 while at the front end is screwed with a warhead 5.
- the warhead 5 carries a rocket 6, of the electrical or mechanical chronometric type, intended to initiate a pyrotechnic composition 7 generating gas.
- a payload composed here of three submunitions 8a, 8b and 8c, for example dispersible mines.
- a piston 9 bears on one side against the submunition 8c and on the other side against the rear end of the warhead 5 and thus delimits inside the latter a chamber 12.
- the piston 9 is linked to the cargo shell at the level of the warhead 5 by a connection means which is here a steel cable 10 of approximately one millimeter in diameter.
- a connection means which is here a steel cable 10 of approximately one millimeter in diameter.
- One end of the cable 10 carries a loop which is fixed to the warhead 5 by means of a screw (of which only the axis is shown here).
- the other end of the cable is fixed to a winding reel 11 whose axis is made integral with the piston by another screw.
- the cable is wound on the reel during the assembly of the shell.
- the base 4 is thus ejected the first followed by the first submunition 8a, the second 8b and the third 8c.
- the piston 9 which is linked to the cargo shell 1 by the cable 10 connected to the warhead 5 is detached from the submunition 8c leaving the latter continuing its trajectory without disturbance (see FIG. 2).
- the length of the cable 10 is determined as a function of the length of the body 2 in order to eject the last submunition 8c. It will therefore be at least equal to the length of the body of the cargo shell 2.
- the axis of the reel 11 is here offset relative to the axis of the cargo shell 1 which allows the piston 9 to be ejected laterally out of the trajectory of the shell in the event of cable breakage 10. On This avoids any interference with the last submunition 8c ejected.
- braking means are preferably provided between the payload and the shell body or between the piston and the shell body.
- braking means are constituted for example by elastic spring blades fixed on the external cylindrical surface of the piston and which come to bear on the internal cylindrical surface of the body of the shell.
- these blades By exerting a frictional force, these blades reduce the speed of ejection of the payload and consequently the value of the inertia force to which the cable is subjected after ejection of the payload.
- the cargo shell 1 comprises a ring 13 screwed onto the warhead 5 and intended to make up for the axial play in mounting the stack of submunitions 8a, 8b, 8c.
- This ring has a hole 23 which allows the passage of gases from the pyrotechnic composition 7 to the piston 9.
- the ring 13 is screwed through the opening of the warhead 5 intended to receive the rocket 6 by means of notches 14 made on the upper face of the ring.
- the rear face of the ring 13 has a countersink 15 intended to receive in a slightly sliding manner the end of a coil 11.
- a cable 10 On this coil 11 is wound a cable 10, one of the ends of which carries a crimped head 18 which comes in a housing of complementary shape arranged on the coil 11 and ensures the securing of the latter with the cable.
- the other end of the cable is crimped in a threaded sleeve itself connected by screwing to the ring 13.
- the piston 9 carries a groove 19 in which is mounted an elastic ring 20 whose function will be explained later.
- the coil 11 has a conical profile 21 allowing during assembly to cause the elastic erasure of the ring 20 in its groove 19. After passage of the conical profile 21, the ring 20 protrudes into a clearance 22 made on the coil 11.
- the pellet is ejected first followed by the first submunition 8a, the second 8b and then the third 8c.
- the piston 9 which is linked to the cargo shell 1 by the cable 10 fixed to the ring 13 dissociates from the submunition 8c letting the latter continue its trajectory without disturbance.
Description
Le domaine technique de la présente invention est celui des obus cargo portant une charge utile, par exemple une ou plusieurs sous-munitions, et éjectant cette charge sur trajectoire au moyen d'un piston poussé par une pression de gaz.The technical field of the present invention is that of cargo shells carrying a payload, for example one or more submunitions, and ejecting this load on the trajectory by means of a piston pushed by a gas pressure.
Un tel obus est composé de façon connue d'un corps pourvu à l'arrière d'une ceinture. Une ogive et un culot sont respectivement vissés aux extrémités avant et arrière du corps. L'intérieur du corps porte une charge utile composée par exemple d'au moins une sous-munition. Dans la tête de l'ogive est logée une charge de dépotage amorçable par une fusée.Such a shell is composed in a known manner of a body provided at the rear of a belt. A warhead and a base are respectively screwed to the front and rear ends of the body. The interior of the body carries a payload composed for example of at least one submunition. In the head of the warhead is housed a charge of unloading bootable by a rocket.
A l'issue d'une durée programmée avant tir, la fusée amorce la charge de dépotage qui engendre une pression de gaz. Cette dernière pousse axialement un piston qui entraîne la charge utile et le culot en vue de leur éjection hors de l'obus.At the end of a programmed duration before firing, the rocket initiates the loading charge which generates a gas pressure. The latter axially pushes a piston which drives the payload and the base for their ejection from the shell.
Un tel type d'obus cargo est décrit par exemple par le brevet FR-A-2363077 sur lequel est fondé le préambule de la revendication indépendante 1,.Such a type of cargo shell is described for example by patent FR-A-2363077 on which the preamble of
Ces obus cargo posent des problèmes au niveau de la séparation entre la charge utile et le piston.These cargo shells pose problems in terms of the separation between the payload and the piston.
En effet, le piston doit se désolidariser de la charge utile après l'éjection de cette dernière sans venir pour autant perturber sa trajectoire.Indeed, the piston must separate from the payload after the ejection of the latter without coming to disturb its trajectory.
C'est le but de l'invention que de proposer un obus cargo comprenant une charge utile poussée par un piston et qui permette d'éviter de tels inconvénients, ainsi l'invention a pour objet un obus cargo destiné à transporter une charge utile et constitué par un corps fermé à une de ses extrémités par un culot et à l'autre par une ogive à l'intérieur de laquelle est disposée une composition pyrotechnique génératrice de gaz destinés à venir agir sur un piston au moment de l'éjection de la charge, obus caractérisé en ce qu'il comporte des moyens assurant une liaison entre le piston et l'obus après l'éjection de la charge utile.It is the object of the invention to provide a cargo shell comprising a payload pushed by a piston and which makes it possible to avoid such drawbacks, thus the invention relates to a cargo shell intended to transport a payload and constituted by a body closed at one of its ends by a base and at the other by a warhead inside which is disposed a pyrotechnic composition generating gas intended to come to act on a piston at the time of ejection of the charge, shell characterized in that it comprises means ensuring a connection between the piston and the shell after the ejection of the payload.
La présence de tels moyens permet de désolidariser le piston de la charge utile.The presence of such means makes it possible to separate the piston from the payload.
Selon un mode particulier de réalisation, les moyens de liaison comprennent au moins un cable dont une extrémité est solidaire de l'obus au niveau de l'ogive et dont l'autre extrémité est solidaire d'une bobine fixée au piston, le cable étant enroulé sur la bobine.According to a particular embodiment, the connection means comprise at least one cable, one end of which is secured to the shell at the level of the warhead and the other end of which is secured to a coil fixed to the piston, the cable being wound on the spool.
Selon une variante de l'invention, l'axe de la bobine est décalé relativement à l'axe de l'obus, ce qui permet d'éviter les interférences entre le piston et la charge utile en cas de rupture du cable.According to a variant of the invention, the axis of the coil is offset relative to the axis of the shell, which avoids interference between the piston and the payload in the event of cable breakage.
Selon une autre variante, l'obus comporte au moins deux cables s'enroulant sur au moins deux bobines régulièrement réparties angulairement sur le piston.According to another variant, the shell comprises at least two cables winding on at least two coils regularly distributed angularly on the piston.
Selon une autre variante, l'axe de la bobine est confondu avec l'axe de l'obus.According to another variant, the axis of the reel coincides with the axis of the shell.
La ou les bobines pourront être constituées par un ou plusieurs prolongements cylindriques du piston.The coil (s) may be formed by one or more cylindrical extensions of the piston.
Selon un mode de réalisation avantageux, la bobine est maintenue de façon temporaire, par exemple par point de colle, sur un lamage porté par une bague solidaire de l'ogive, le piston portant des moyens permettant son accrochage sur la bobine.According to an advantageous embodiment, the coil is temporarily held, for example by glue point, on a counterbore carried by a ring secured to the warhead, the piston carrying means allowing its attachment to the coil.
Les moyens d'accrochage du piston sur la bobine pourront comprendre un anneau élastique déformable disposé dans une gorge du piston.The means for attaching the piston to the coil may comprise a deformable elastic ring placed in a groove in the piston.
De préférence, la bobine portera un profil conique destiné à provoquer l'effacement de l'anneau élastique dans sa gorge lors de la mise en place du piston ainsi qu'un dégagement destiné à recevoir l'anneau élastique qui solidarise ainsi le piston et la bobine.Preferably, the coil will carry a conical profile intended to cause the elastic ring to be erased in its groove when the piston is put in place, as well as a clearance intended to receive the elastic ring which thus fixes the piston and the coil.
L'invention sera mieux comprise à la lecture de la description de modes particuliers de réalisation, faite en référence aux dessins annexés dans lesquels:
- la figure 1 représente schématiquement en coupe axiale un obus cargo porteur de sous-munitions poussées par un piston selon l'invention.
- la figure 2 représente schématiquement en coupe axiale ce même obus cargo après éjection des sous-munitions.
- la figure 3 représente schématiquement en coupe axiale partielle ce même obus cargo selon un mode de réalisation préférentiel.
- Figure 1 shows schematically in axial section a cargo shell carrying submunitions pushed by a piston according to the invention.
- Figure 2 shows schematically in axial section this same cargo shell after ejection of the submunitions.
- Figure 3 shows schematically in partial axial section this same cargo shell according to a preferred embodiment.
En se reportant à la figure 1, un obus cargo 1 est constitué de façon classique d'un corps 2 pourvu à l'arrière d'une ceinture 3. A l'extrémité arrière du corps 2 est vissé un culot 4 tandis qu'à l'extrémité avant est vissée une ogive 5. L'ogive 5 porte une fusée 6, de type chronométrique électrique ou mécanique, destinée à réaliser l'amorçage d'une composition pyrotechnique 7 génératrice de gaz.Referring to Figure 1, a
A l'intérieur du corps 2 est disposée une charge utile, composée ici de trois sous-munitions 8a, 8b et 8c, par exemple des mines dispersables.Inside the
Ces sous-munitions sont liées en rotation au corps de l'obus cargo par des moyens tels des goupilles ou des clavettes. Un piston 9 est en appui d'un côté contre la sous-munition 8c et de l'autre coté contre l'extrémité arrière de l'ogive 5 et délimite ainsi à l'intérieur de cette dernière une chambre 12.These submunitions are linked in rotation to the body of the cargo shell by means such as pins or keys. A piston 9 bears on one side against the submunition 8c and on the other side against the rear end of the
Le piston 9 est lié à l'obus cargo au niveau de l'ogive 5 par un moyen de liaison qui est ici un cable d'acier 10 d'environ un millimètre de diamètre. Une extrémité du cable 10 porte une boucle qui est fixée à l'ogive 5 par l'intermédiaire d'une vis (dont seul l'axe est représenté ici).The piston 9 is linked to the cargo shell at the level of the
L'autre extrémité du cable est fixée à une bobine d'enroulement 11 dont l'axe est rendu solidaire du piston par une autre vis. Le cable est enroulé sur la bobine lors de l'assemblage de l'obus.The other end of the cable is fixed to a
Au moment de l'amorçage de la composition génératrice de gaz 7 par la fusée 6, une très forte pression de gaz est générée dans la chambre 12. Cette pression engendre une importante poussée sur le piston 9 qui lui-même pousse les sous-munitions 8 et le culot 4, cisaillant ainsi le filetage de maintien de ce dernier sur le corps 2.At the time of the priming of the gas-generating
Le culot 4 est ainsi éjecté le premier suivi par la première sous-munition 8a, la deuxième 8b et la troisième 8c. Le piston 9 qui est lié à l'obus cargo 1 par le cable 10 relié à l'ogive 5 se désolidarise de la sous-munition 8c laissant cette dernière poursuivre sa trajectoire sans perturbation (voir figure 2).The
La longueur du cable 10 est déterminée en fonction de la longueur du corps 2 afin d'assurer l'éjection de la dernière sous-munition 8c. Elle sera donc au minimum égale à la longueur du corps de l'obus cargo 2.The length of the
L'axe de la bobine 11 est ici décalé par rapport à l'axe de l'obus cargo 1 ce qui permet au piston 9 d'être éjecté latéralement hors de la trajectoire de l'obus en cas de rupture du cable 10. On évite ainsi toute interférence avec la dernière sous-munition 8c éjectée.The axis of the
Pour renforcer la tenue mécanique de la liaison, il est possible de prévoir plusieurs cables 10, chacun s'enroulant sur une bobine fixée au piston 9. Les bobines seront régulièrement reparties angulairement sur le piston de façon à éviter tout balourd.To strengthen the mechanical strength of the connection, it is possible to provide
Afin d'éviter la rupture du ou des cables on disposera de façon préférentielle des moyens de freinage entre la charge utile et le corps de l'obus ou entre le piston et le corps de l'obus.In order to avoid breaking the cable (s), braking means are preferably provided between the payload and the shell body or between the piston and the shell body.
Ces moyens de freinage sont constitués par exemple par des lames ressort élastiques fixées sur la surface cylindrique externe du piston et qui viennent en appui sur la surface cylindrique interne du corps de l'obus.These braking means are constituted for example by elastic spring blades fixed on the external cylindrical surface of the piston and which come to bear on the internal cylindrical surface of the body of the shell.
En exerçant une force de frottement ces lames réduisent la vitesse d'éjection de la charge utile et consécutivement la valeur de l'effort d'inertie auquel le cable se trouve soumis après éjection de la charge utile.By exerting a frictional force, these blades reduce the speed of ejection of the payload and consequently the value of the inertia force to which the cable is subjected after ejection of the payload.
Selon un mode de réalisation préférentiel, en référence à la figure 3, l'obus cargo 1 comprend une bague 13 vissée sur l'ogive 5 et destinée à rattraper le jeu axial de montage de l'empilement des sous-munitions 8a, 8b, 8c. Cette bague présente un trou 23 qui autorise le passage des gaz de la composition pyrotechnique 7 vers le piston 9.According to a preferred embodiment, with reference to FIG. 3, the
Le vissage de la bague 13 s'effectue au travers de l'ouverture de l'ogive 5 destinée à recevoir la fusée 6 grâce à des encoches 14 réalisées sur la face supérieure de la bague.The
La face arrière de la bague 13 présente un lamage 15 destiné à recevoir de manière légèrement coulissante l'extrémité d'une bobine 11. Sur cette bobine 11 est enroulé un cable 10 dont l'une des extrémités porte une tête sertie 18 qui vient dans un logement de forme complémentaire aménagé sur la bobine 11 et assure la solidarisation de cette dernière avec le cable.The rear face of the
L'autre extrémité du cable est sertie dans un manchon fileté lui même relié par vissage à la bague 13.The other end of the cable is crimped in a threaded sleeve itself connected by screwing to the
Le piston 9 porte une gorge 19 dans laquelle est monté un anneau élastique 20 dont la fonction sera précisée par la suite.The piston 9 carries a
La bobine 11 comporte un profil conique 21 permettant lors du montage de provoquer l'effacement élastique de l'anneau 20 dans sa gorge 19. Après passage du profil conique 21, l'anneau 20 vient en saillie dans un dégagement 22 réalisé sur la bobine 11.The
Le montage de ce sous-ensemble s'effectue de la manière suivante:
- on monte la
bobine 11 portant lecable 10 enroulé à l'intérieur dulamage 15 de labague 13 en rajoutant quelques points de colle afin de la maintenir en place. - on visse l'ogive 5 portant la
bague 13 sur lecorps 2. - on met en place à l'intérieur du
corps 2 le piston 9 équipé de l'anneau élastique 20. - on pousse le piston 9 jusqu'à ce que l'anneau élastique 20 vienne en contact avec la
bobine 11, se trouve effacé dans sagorge 19 par le profil conique 21 puis vienne en saillie dans ledégagement 22.
- the
coil 11 is mounted carrying thecable 10 wound inside thecounterbore 15 of thering 13 by adding a few dots of adhesive in order to keep it in place. - the
warhead 5 carrying thering 13 is screwed onto thebody 2. - the piston 9 fitted with the
elastic ring 20 is placed inside thebody 2. - the piston 9 is pushed until the
elastic ring 20 comes into contact with thecoil 11, is erased in itsgroove 19 by theconical profile 21 and then projects into theclearance 22.
Ainsi la bobine 11 est rendue solidaire du piston 9.Thus the
Au moment de l'amorçage de la composition pyrotechnique 7 par la fusée 6, une très forte pression de gaz est générée dans la chambre 12. Cette pression engendre une importante poussée sur le piston 9 au travers du trou de passage 23 réalisé dans la bague 13. Le piston pousse à son tour les sous-munitions 8 et le culot 4.When the
Le déplacement du piston 9 dont la bobine 11 est solidaire grâce à l'anneau élastique 20 provoque la rupture des points de colle qui liaient la bobine à la bague 13.The displacement of the piston 9, the
Le culot est éjecté en premier suivi de la première sous-munition 8a, de la deuxième 8b puis de la troisième 8c. Le piston 9 qui est lié à l'obus cargo 1 par le cable 10 fixé à la bague 13 se désolidarise de la sous-munition 8c laissant cette dernière poursuivre sa trajectoire sans perturbation.The pellet is ejected first followed by the first submunition 8a, the second 8b and then the third 8c. The piston 9 which is linked to the
Claims (9)
- A cargo shell (1) designed to transport a payload (8a, 8b, 8c) and composed of a body (2) closed off at one of its ends by a base (4) and at the other by a nose cap (5) inside which is placed a pyrotechnic composition (7) for generating gases designed to act on a piston (9) upon ejection of the payload, a shell characterised in that it comprises means to ensure a connection between the piston (9) and the shell (1) after ejection of the payload (8a, 8b, 8c).
- A shell according to Claim 1, characterised in that the connecting means comprise at least one cable (10) wherein one end is integral with the shell at the nose cap (5) and wherein the other end is integral with a spool (11) fastened to the piston (9), the cable being wound around the spool.
- A shell according to Claim 2, characterised in that the axis of the spool is offset with respect to the axis of the shell.
- A shell according to Claim 3, characterised in that it comprises at least two cables wound around at least two spools evenly distributed at an angle on the piston.
- A shell according to Claim 2, characterised in that the axis of the spool and the axis of the shell are one and the same.
- A shell according to one of Claims 2 to 5, characterised in that the spool or spools are formed of one or several cylindrical extensions of the piston.
- A shell according to Claim 5, characterised in that the spool (11) is held in place temporarily, for example by a spot of glue, on a countersink (15) carried by a ring (13) integral with the shell (5), the piston (9) carrying means to enable it to be hooked onto the spool (11).
- A shell according to Claim 7, characterised in that the means to hook the piston (9) onto the spool (11) comprise a deformable flexible ring (20) placed in a groove (19) of the piston (9).
- A shell according to Claim 8, characterised in that the spool (11) has a tapered profile (21) designed to cause the flexible ring (20) to slip into the groove (19) when the piston is put into place as well as a cut away part (22) designed to accommodate the flexible ring (20) thereby making the piston (9) and the spool (11) integral with one another.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9113673 | 1991-11-06 | ||
| FR9113673A FR2683309B1 (en) | 1991-11-06 | 1991-11-06 | CARGO SHELL EJECTING A USEFUL LOAD USING A PISTON. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0541412A1 EP0541412A1 (en) | 1993-05-12 |
| EP0541412B1 true EP0541412B1 (en) | 1995-12-27 |
Family
ID=9418659
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP92402727A Expired - Lifetime EP0541412B1 (en) | 1991-11-06 | 1992-10-06 | Cargo munition ejecting a submunition by means of a piston |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US5287810A (en) |
| EP (1) | EP0541412B1 (en) |
| DE (1) | DE69207157T2 (en) |
| FR (1) | FR2683309B1 (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2722872B1 (en) * | 1994-07-19 | 1996-10-04 | Lacroix Soc E | PYROTECHNIC DEVICE FOR LAUNCHING AT LEAST ONE PROJECTILE |
| DE59704496D1 (en) * | 1996-03-08 | 2001-10-11 | Diehl Stiftung & Co | Method and device for moving a large-caliber payload over a site |
| US6470805B1 (en) * | 2001-04-30 | 2002-10-29 | The United States Of America As Represented By The Secretary Of The Navy | Fire retardant bio-friendly practice munition |
| US7168368B1 (en) * | 2004-05-06 | 2007-01-30 | The United States Of America As Represented By The Secretary Of The Navy | Apparatus for expelling a payload from a warhead |
| US10809045B1 (en) | 2018-05-10 | 2020-10-20 | The United States Of America As Represented By The Secretary Of The Air Force | Forward firing fragmentation (FFF) munition including fragmentation adjustment system and associated methods |
| US11561075B2 (en) * | 2018-12-13 | 2023-01-24 | The United States Of America, As Represented By The Secretary Of The Navy | Projectile with pyrotechnically timed release of a secondary payload |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US854624A (en) * | 1907-02-02 | 1907-05-21 | Charles H Banks | Means for throwing life-lines. |
| US2274655A (en) * | 1937-03-18 | 1942-03-03 | Bickel Erich | Aerial multimine |
| US2973712A (en) * | 1959-02-11 | 1961-03-07 | Bendix Corp | High altitude sounding projectile |
| US3092358A (en) * | 1961-09-20 | 1963-06-04 | Jr James H Potts | Parachute pack opener |
| DE2140875A1 (en) * | 1971-08-14 | 1973-02-22 | Messerschmitt Boelkow Blohm | DEVICE FOR RECOIL-FREE AND SNAP-FREE SHOOTING OF BULLETS |
| SE416078B (en) * | 1976-08-23 | 1980-11-24 | Foerenade Fabriksverken | DEVICE FOR SUSPENSION AND SEPARATION OF MULTIPLE BODIES OF A GRANATE OR SIMILAR |
| DE2824203A1 (en) * | 1978-06-02 | 1979-12-06 | Diehl Gmbh & Co | BULLET WITH A MOUNTAINABLE IGNITION |
| DE3705078C1 (en) * | 1987-02-18 | 1988-04-21 | Rheinmetall Gmbh | Bullet with brake parachute |
| DE3924397A1 (en) * | 1989-07-24 | 1991-02-07 | Rheinmetall Gmbh | CARRIER FLOOR |
| US5160800A (en) * | 1991-04-24 | 1992-11-03 | The United States Of America As Represented By The Secretary Of The Navy | Obturator retaining means |
-
1991
- 1991-11-06 FR FR9113673A patent/FR2683309B1/en not_active Expired - Fee Related
-
1992
- 1992-10-06 EP EP92402727A patent/EP0541412B1/en not_active Expired - Lifetime
- 1992-10-06 DE DE69207157T patent/DE69207157T2/en not_active Expired - Fee Related
- 1992-11-06 US US07/972,842 patent/US5287810A/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| FR2683309A1 (en) | 1993-05-07 |
| US5287810A (en) | 1994-02-22 |
| FR2683309B1 (en) | 1993-12-31 |
| DE69207157T2 (en) | 1996-06-05 |
| DE69207157D1 (en) | 1996-02-08 |
| EP0541412A1 (en) | 1993-05-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1092940A1 (en) | Igniting device for a propellant charge | |
| EP0434505B1 (en) | Peripheral jacket for a tube launched guided missile | |
| EP0541411A1 (en) | Device for ejecting submunitions from the shell of a cargomunition | |
| EP0541412B1 (en) | Cargo munition ejecting a submunition by means of a piston | |
| EP0694753A1 (en) | Pyrotechnic device for launching at least one projectile | |
| EP0640204B1 (en) | Telescoped round-type ammunition | |
| EP0594482B1 (en) | Case for a propellant charge | |
| WO1989009919A1 (en) | Separation device for the aerodynamic braking of a body | |
| FR2919269A1 (en) | Arming rope mounting device for e.g. airplane, has belt winder with sheave comprising groove for receiving arming rope at winding stage and for storing rope and allowing extraction and deployment of winder during dropping of para-cargo | |
| EP0401114B1 (en) | Holding device for a projectile in relation to a telescoped ammunition case | |
| CH657699A5 (en) | ARTIFICIAL TRIGGERING DEVICE FOR LIGHTNING LIGHTNING. | |
| EP0653604B1 (en) | Stabilising for deployment device for a rocket type projectile | |
| EP3638973B1 (en) | Aerodynamic braking device for a payload casing | |
| EP0756151A1 (en) | Ignition system for a propulsive charge of a submunition ejected from a cargo munition | |
| EP1376045A1 (en) | Adaptive device for a projectile fired from a launching tube | |
| EP2569591A1 (en) | Guided munition protected by an aerodynamic cap | |
| EP0767356B1 (en) | Spin braking system for a cargo ammunition submissile | |
| EP3910280B1 (en) | Device for detecting absence of mechanical barrier for a missile and missile comprising such a device | |
| EP0724132A1 (en) | Safety and arming device for a projectile fuse | |
| EP0775887A1 (en) | Retainer for the case of an explosive charge | |
| FR2691799A1 (en) | Chemical self destruct system for sub-munition of carrier shell | |
| BE530432A (en) | ||
| FR2699662A1 (en) | Impact detector for firing mechanism of impact-detonating munition | |
| EP0685059B1 (en) | Safety device for locking a striker, and methods for fabricating such device | |
| FR2672673A1 (en) | Priming device for a subprojectile |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
| AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): DE IT NL SE |
|
| 17P | Request for examination filed |
Effective date: 19930623 |
|
| 17Q | First examination report despatched |
Effective date: 19950508 |
|
| GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
| AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE IT NL SE |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 19951227 Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRE;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.SCRIBED TIME-LIMIT Effective date: 19951227 |
|
| REF | Corresponds to: |
Ref document number: 69207157 Country of ref document: DE Date of ref document: 19960208 |
|
| NLV1 | Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act | ||
| PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
| STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
| 26N | No opposition filed | ||
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 19980925 Year of fee payment: 7 |
|
| PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 19981021 Year of fee payment: 7 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: THE PATENT HAS BEEN ANNULLED BY A DECISION OF A NATIONAL AUTHORITY Effective date: 19991030 |
|
| EUG | Se: european patent has lapsed |
Ref document number: 92402727.9 |
|
| PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20000801 |