EP1597534B1 - Projectile fuze - Google Patents

Projectile fuze Download PDF

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Publication number
EP1597534B1
EP1597534B1 EP03816041A EP03816041A EP1597534B1 EP 1597534 B1 EP1597534 B1 EP 1597534B1 EP 03816041 A EP03816041 A EP 03816041A EP 03816041 A EP03816041 A EP 03816041A EP 1597534 B1 EP1597534 B1 EP 1597534B1
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EP
European Patent Office
Prior art keywords
rotor
segment
dynamic pressure
membrane
ignition
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Expired - Lifetime
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EP03816041A
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German (de)
French (fr)
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EP1597534A1 (en
Inventor
Jean-Pierre Golay
Olivier Pronini
Claude Robert-Nicoud
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SN Technologies SA
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SN Technologies SA
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/28—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids
    • F42C15/29—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids operated by fluidic oscillators; operated by dynamic fluid pressure, e.g. ram-air operated

Definitions

  • the present invention relates to a projectile rocket comprising a firing device and security means for allowing the firing of the projectile only under predetermined conditions.
  • a primer rotor is rotatably mounted and rotatable to be moved from an initial safety position to at least one firing position.
  • the known device further comprises security means responsive to the dynamic air pressure due to the projectile in flight having a detector element that can be displaced under the influence of this dynamic pressure to allow firing when this dynamic pressure reaches a predetermined value corresponding to a given velocity of the projectile and to prevent ignition in the opposite case.
  • This known device is intended for a munition or bomb carried by air and dropped from this aircraft.
  • the document US 4,002,123 refers to a rocket for dropped bombs. It comprises two turbines rotated by air and which drive electrical alternators, which in turn drive a rotor-starter. A measurement of the dynamic pressure makes it possible to unlock the two turbines in order to allow an armed position of the rotor.
  • the rocket according to the invention comprises for this purpose the features of claim 1, namely that the detector element consists of a membrane housed in a connected chamber of a first side of the membrane by a conduit outside the fuse, this membrane being capable of curving under the dynamic pressure and acting on a first portion of a transmission member, a second portion is intended to cooperating with the primer rotor, the security means further comprising an acceleration detector arranged to block the firing device when the projectile acceleration is less than a second predetermined value and to release the device firing when the acceleration is equal to or greater than this second predetermined value, the membrane being arranged to control the movement of the transmission member so that on the one hand its second portion is spaced from a stop portion of the rotor allowing rotation of the rotor to said at least one firing position, when the dynamic pressure reaches the first predetermined value and after the acceleration sensor has released the primer rotor, and secondly that second portion enters into contacting the stopping portion of the rotor when the dynamic pressure has
  • the rocket is subject to at least two safety criteria, namely its acceleration and speed and secondly, its operation is permanently blocked when the dynamic pressure does not reach the predetermined value.
  • Figures 1A, 2A and 3A show the rocket in partial section in three different positions.
  • Figures 1B, 2B and 3B are plan views of the primer carrier rotor in the three different positions.
  • the rocket 10 whose outer contour is sketched in phantom in Figure 3A is intended to be mounted to the front of a projectile 11 by any suitable means, favorably by screwing. Like all rockets, it comprises a firing device 12 of which only a part is shown, in the form of a primer carrier rotor 14 rotatably mounted on a shaft 16 integral with the frame 17 of the rocket.
  • This rotor 14 comprises primers 18, 19 which can be aligned by rotation of the rotor with an unillustrated pyrotechnic chain comprising in known manner, for example, a detonator intended to communicate the firing to the explosive charge of the projectile.
  • the rotor is rotatable by a spring 15 to be moved from an initial safety position (Fig. 1B) to one or other of the ignition or firing positions (Fig. 3B). ) in which one of the instantaneous or delay primers 18, 19 is aligned in the pyrotechnic chain according to the position of a selection rod 22 cooperating with a peripheral cam 21.
  • the rocket comprises a series of safety means 30 comprising, inter alia, at least one acceleration sensor 31 arranged to block the firing device 12 when the acceleration of the projectile 11 is less than a predetermined value and release the firing device and begin the firing procedure when the acceleration is equal to or greater than this predetermined value.
  • This acceleration sensor cooperates with a timer device 32 which in turn releases the rotor 14 after a predetermined time delay to rotate under the effect of its spring.
  • the general construction of the rocket with regard to the firing device 12, the acceleration detector 31, the timing device 32 and the rotor 14 may for example be of the type described in the patent Swiss 650,330 the text of which forms an integral part of this application.
  • the security means 30 comprise at least a second security device 35 responsive to a second discriminatory physical phenomenon, namely the dynamic air pressure due to the projectile in flight, which is arranged in a manner to authorize the firing only when the dynamic pressure reaches a predetermined value corresponding to a given displacement speed of the projectile and to prevent it otherwise.
  • a second discriminatory physical phenomenon namely the dynamic air pressure due to the projectile in flight
  • This second safety device 35 comprises a membrane of elastic material 36, for example plastic, housed in a chamber 37.
  • the edges of the membrane are retained by the walls of the chamber 37 by insertion at the junction of a room 38 and a lower part 39 of the frame 17.
  • a channel 40 connects an orifice 41 located at the front portion 42 of the rocket chamber 37.
  • This channel 40 has a first portion 45 with a smaller section than a second portion 46 located further back. In the idle state, the first portion 45 of the channel 40 is completely closed by a plug 47.
  • the dynamic pressure exerted by the air moves the plug back into the second portion 46 and thus opens the channel 40 so that the membrane 36 is subjected to the dynamic pressure of the projectile in flight.
  • the lower portion 48 of the chamber 37 is rounded and connected to a channel 49 venting.
  • the safety device 35 further has a transmission member 50 for acting on the rotor as a function of the dynamic pressure.
  • This member is constituted by a flexible metal blade 51 mounted on the lower piece 39. An end portion 54 of the blade 51 is inserted and held between the parts 38 and 39 and disposed under the membrane 36. The blade 51 then follows the piece 39 and is extended by an end 55 in the direction of the rotor 14 to cooperate with the cam 21 provided at the periphery of the latter.
  • This cam 21 comprises a recessed portion 60 (FIGS 1A and 1B) allowing rotation of the rotor 14 when the delay device has released it. It further comprises a stop portion 61 ( Figures 2A and 2B) having a first stop 62 arranged to stop the rotor 14 in its rotation when the end 55 of the blade 51 has not been raised and a second stop 63 for holding the flexible blade 51 in its lower position in a notch 64 formed by the first and second stops.
  • the rocket operates as follows: Before the launch of the projectile, the moving elements of the rocket are in the rest position shown in Figures 1 A and 1B. After the start of the stroke, the plug 47 is rapidly moved back to open the air channel 40 so that a dynamic air pressure is established in the chamber 37. The membrane 36 and the portion 54 of the blade 51 are curved downwards when this dynamic pressure reaches a sufficient predetermined value, for example 3 bars. The flexible blade 51 then forms in its middle part an upward curved loop 66 (FIG. 3A) and its lower end 55 is raised above the level of the stop portion 61.
  • the acceleration detector 31 is activated to start the delay device 32 which after a predetermined time releases the rotation of the rotor 14. is not stopped by the blade 51 raised above the stop portion 61 and performs an angular rotation predetermined to place one or the other of the primers 18,19 in the pyrotechnic chain.
  • the rotor 14 When the speed of the projectile is too low and the dynamic pressure does not reach a sufficient value, for example less than 3 bar, but the rocket acceleration has been higher than the minimum predetermined value, the rotor 14 is set in rotation, but its rotation is stopped by the stop portion 61, FIGS. 2A and 2B. In addition, the end 55 is locked in the notch 64 under the effect of the spring 15 of the rotor 14. The firing device is thus stopped and permanently blocked and none of the primers 18, 19 is aligned with the pyrotechnic chain.
  • the safety means comprise, apart from the acceleration sensor or detectors, at least one other safety device sensitive to another discriminating factor, here the dynamic pressure due to the speed of the projectile in flight.
  • This dynamic pressure acts first on the plug 47 which thus constitutes a first safety element and then on the safety device 35 with its control blade 51.
  • the safety of ignition is thus at least doubled, while having a simple, reliable construction with few components.
  • the embodiment described above is not limiting and that it can receive any desirable modifications within the frame as defined by claim 1.
  • the security means can still present other elements, for example sensitive to rotation in the case of gyrating projectiles.

Abstract

Fuze including safety element (30) includes an acceleration detector (31) that acts on a timer (32) coacting with a primer housing rotor (14). Rotation of the rotor can be halted by a second safety device (35) responsive to the dynamic pressure generated by the speed of the projectile (11) in flight. For this purpose, the device includes a diaphragm (36) engaging a flexible blade (51) to space apart the end (55) of the blade and the rotor when the dynamic pressure has a predetermined value, whereby a primer (18) can be moved into line in the explosive train. When the dynamic pressure is too low, the end (55) stops the rotor (14) from rotating and the firing procedure is also blocked in a notch in the rotor (14). The resulting fuze thus has highly reliable dual safety element responsive to two separate physical phenomena and having a simple construction.

Description

La présente invention concerne une fusée de projectile comprenant un dispositif de mise à feu et des moyens de sécurité destinés à permettre la mise à feu du projectile uniquement sous des conditions prédéterminées.The present invention relates to a projectile rocket comprising a firing device and security means for allowing the firing of the projectile only under predetermined conditions.

On connaît par le document US 4,526,1 p4 un dispositif de fusée et de mise à feu considéré comme état de la technique le plus proche. Dans ce dispositif connu, un rotor porte-amorce est monté tournant et susceptible d'être entraîné en rotation pour être déplacé d'une position initiale de sécurité vers au moins une position de mise à feu. Le dispositif connu comprend en outre des moyens de sécurité sensible à la pression dynamique d'air due au projectile en vol présentant un élément détecteur susceptible d'être déplacé sous l'influence de cette pression dynamique pour autoriser la mise à feu lorsque cette pression dynamique atteint une valeur prédéterminée correspondant à une vitesse donnée du projectile et pour empêcher la mise à feu dans le cas contraire.We know from the document US 4,526,1 p4 a rocket and firing device considered to be the closest state of the art. In this known device, a primer rotor is rotatably mounted and rotatable to be moved from an initial safety position to at least one firing position. The known device further comprises security means responsive to the dynamic air pressure due to the projectile in flight having a detector element that can be displaced under the influence of this dynamic pressure to allow firing when this dynamic pressure reaches a predetermined value corresponding to a given velocity of the projectile and to prevent ignition in the opposite case.

Ce dispositif connu est destiné à une munition ou bombe portée par avion et larguée de cet avion.This known device is intended for a munition or bomb carried by air and dropped from this aircraft.

Sa construction est relativement compliquée et comprend un piston coulissant dans un cylindre. Après le largage le piston est amené à armer un ressort qui fournit l'énergie de rotation pour le rotor. Ce dernier est libéré, lorsque le piston fait basculer un levier de blocage pour initier la mise à feu. Dans ce dispositif, il n'est pas fait usage conjointement d'un détecteur d'accélération qui permettrait de bloquer le dispositif lorsque l'accélération n'est pas suffisante.Its construction is relatively complicated and includes a piston sliding in a cylinder. After dropping the piston is brought to arm a spring which provides the rotational energy for the rotor. This is released when the piston tilts a lock lever to initiate firing. In this device, it is not used together with an acceleration detector that would block the device when the acceleration is not sufficient.

Le document US 4,380,197 décrit une fusée pour missiles guidés avec un dispositif de sécurité utilisant une comparaison entre les pressions statiques et dynamiques pour autoriser ou empêcher une mise à feu. Lorsque la position de mise à feu est atteinte par le rotor, le dispositif est définitivement bloqué dans la position armée.The document US 4,380,197 describes a missile rocket guided with a safety device that uses a comparison between static and dynamic pressures to allow or prevent firing. When the firing position is reached by the rotor, the device is permanently locked in the armed position.

Le document US 4,002,123 se réfère à une fusée pour bombes larguées. Il comprend deux turbines mises en rotation par l'air et qui entraînent des alternateurs électriques entraînant à leur tour un rotor porte-amorce. Une mesure de la pression dynamique permet de déverrouiller les deux turbines afin d'autoriser une position armée du rotor.The document US 4,002,123 refers to a rocket for dropped bombs. It comprises two turbines rotated by air and which drive electrical alternators, which in turn drive a rotor-starter. A measurement of the dynamic pressure makes it possible to unlock the two turbines in order to allow an armed position of the rotor.

Les dispositifs décrits dans ces trois documents antérieurs ne sont pas adaptés à des projectiles tirés. Leur construction est trop compliquée et trop fragile pour une telle utilisation. Ces dispositifs sont munis d'un nombre de pièces élevé. En outre, aucun des dispositifs décrits ne permet le blocage définitif du dispositif de mise à feu dans une position différente de la position de mise à feu, lorsque la pression dynamique, donc la vitesse du projectile n'atteint pas la valeur prédéterminée.The devices described in these three prior documents are not suitable for shots fired. Their construction is too complicated and too fragile for such use. These devices are provided with a high number of parts. In addition, none of the devices described allows the final locking of the firing device in a different position of the firing position, when the dynamic pressure, so the speed of the projectile does not reach the predetermined value.

La présente invention a pour but de remédier à ces inconvénients, et la fusée selon l'invention comprend à cet effet les caractéristiques figurant à la revendication 1, à savoir que l'élément détecteur est constitué par une membrane logée dans une chambre relié d'un premier côté de la membrane par un conduit à l'extérieur de la fusée, cette membrane étant susceptible de s'incurver sous la pression dynamique et d'agir sur une première portion d'un organe de transmission dont une seconde portion est destinée à coopérer avec le rotor porte-amorce, les moyens de sécurité comportant en outre un détecteur d'accélération agencé de façon à bloquer le dispositif de mise à feu lorsque l'accélération du projectile est inférieure à une seconde valeur prédéterminée et à libérer le dispositif de mise à feu lorsque l'accélération est égale ou supérieure à cette seconde valeur prédéterminée, la membrane étant agencée pour contrôler le mouvement de l'organe de transmission de façon que d'une part sa seconde portion soit écartée d'une portion d'arrêt du rotor permettant la rotation de ce rotor vers ladite au moins une position de mise à feu, lorsque la pression dynamique atteint la première valeur prédéterminée et après que le détecteur d'accélération eut libéré le rotor porte-amorce, et que d'autre part cette seconde portion entre en contact avec la portion d'arrêt du rotor lorsque la pression dynamique n'a pas atteint la première valeur prédéterminée, de manière qu'un premier élément de retenue de la portion d'arrêt arrête le rotor dans sa rotation empêchant la mise à feu, et de manière qu'un second élément de retenue de cette portion d'arrêt retienne la seconde portion de l'organe de transmission pour bloquer le dispositif de mise à feu dans une position différente de la position de mise à feu.The object of the present invention is to remedy these drawbacks, and the rocket according to the invention comprises for this purpose the features of claim 1, namely that the detector element consists of a membrane housed in a connected chamber of a first side of the membrane by a conduit outside the fuse, this membrane being capable of curving under the dynamic pressure and acting on a first portion of a transmission member, a second portion is intended to cooperating with the primer rotor, the security means further comprising an acceleration detector arranged to block the firing device when the projectile acceleration is less than a second predetermined value and to release the device firing when the acceleration is equal to or greater than this second predetermined value, the membrane being arranged to control the movement of the transmission member so that on the one hand its second portion is spaced from a stop portion of the rotor allowing rotation of the rotor to said at least one firing position, when the dynamic pressure reaches the first predetermined value and after the acceleration sensor has released the primer rotor, and secondly that second portion enters into contacting the stopping portion of the rotor when the dynamic pressure has not reached the first predetermined value, so that a first retention member of the stopping portion stops the rotor in its rotation preventing firing, and such that a second retaining member of this stopping portion retains the second portion of the transmission member to lock the firing device in a position different from the firing position.

Grâce à ces caractéristiques, on obtient une fusée possédant une sécurité encore plus grande, une construction simple et robuste ne comportant qu'un nombre de composants réduits, assurant ainsi un fonctionnement très fiable. En particulier, la fusée est soumise à au moins deux critères de sécurité, à savoir son accélération et sa vitesse et d'autre part, son fonctionnement se trouve définitivement bloqué lorsque la pression dynamique n'atteint pas la valeur prédéterminée.Thanks to these characteristics, we obtain a rocket with an even greater safety, a simple and robust construction having only a number of reduced components, thus ensuring a very reliable operation. In particular, the rocket is subject to at least two safety criteria, namely its acceleration and speed and secondly, its operation is permanently blocked when the dynamic pressure does not reach the predetermined value.

D'autres avantages ressortent des caractéristiques exprimées dans les revendications dépendantes et de la description exposant ci-après l'invention plus en détail à l'aide de dessins qui représentent schématiquement et à titre d'exemple un mode d'exécution.Other advantages emerge from the features expressed in the dependent claims and from the following description describing the invention more in detail with the aid of drawings which schematically and by way of example represent a mode of execution.

Les figures 1A, 2A et 3A représentent la fusée en coupe partielle dans trois positions différentes.Figures 1A, 2A and 3A show the rocket in partial section in three different positions.

Les figures 1B, 2B et 3B sont des vues en plan du rotor porte-amorces dans les trois positions différentes.Figures 1B, 2B and 3B are plan views of the primer carrier rotor in the three different positions.

En référence aux figures 1 A à 3A, la fusée 10 dont le contour extérieur est esquissé en traits mixtes à la figure 3A est destinée à être montée à la partie frontale d'un projectile 11 par tous moyens adéquats, favorablement par vissage. Comme toutes les fusées, elle comprend un dispositif de mise à feu 12 dont seulement une partie est représentée, sous forme d'un rotor porte-amorces 14 monté tournant sur un arbre 16 solidaire du bâti 17 de la fusée. Ce rotor 14 comprend des amorces 18,19 susceptibles d'être alignées par rotation du rotor avec une chaîne pyrotechnique non illustrée comportant de façon connue par exemple un détonateur destiné à communiquer la mise à feu à la charge explosive du projectile.Referring to Figures 1A to 3A, the rocket 10 whose outer contour is sketched in phantom in Figure 3A is intended to be mounted to the front of a projectile 11 by any suitable means, favorably by screwing. Like all rockets, it comprises a firing device 12 of which only a part is shown, in the form of a primer carrier rotor 14 rotatably mounted on a shaft 16 integral with the frame 17 of the rocket. This rotor 14 comprises primers 18, 19 which can be aligned by rotation of the rotor with an unillustrated pyrotechnic chain comprising in known manner, for example, a detonator intended to communicate the firing to the explosive charge of the projectile.

Le rotor est susceptible d'être entraîné en rotation par un ressort 15 pour être déplacé d'une position initiale de sécurité (figure 1B) vers l'une ou l'autre des positions d'ignition ou de mise à feu (fig. 3B) dans laquelle l'une des amorces instantanée ou à retard 18,19 est alignée dans la chaîne pyrotechnique selon la position d'une tige de sélection 22 coopérant avec une came périphérique 21.The rotor is rotatable by a spring 15 to be moved from an initial safety position (Fig. 1B) to one or other of the ignition or firing positions (Fig. 3B). ) in which one of the instantaneous or delay primers 18, 19 is aligned in the pyrotechnic chain according to the position of a selection rod 22 cooperating with a peripheral cam 21.

La fusée comprend une série de moyens de sécurité 30 comportant, entre autres, au moins un détecteur d'accélération 31 agencé de façon à bloquer le dispositif de mise à feu 12 lorsque l'accélération du projectile 11 est inférieure à une valeur prédéterminée et à libérer le dispositif de mise à feu et à commencer la procédure de mise à feu lorsque l'accélération est égale ou supérieure à cette valeur prédéterminée.The rocket comprises a series of safety means 30 comprising, inter alia, at least one acceleration sensor 31 arranged to block the firing device 12 when the acceleration of the projectile 11 is less than a predetermined value and release the firing device and begin the firing procedure when the acceleration is equal to or greater than this predetermined value.

Ce détecteur d'accélération coopère avec un dispositif temporisateur 32 qui à son tour libère le rotor 14 après une durée de temporisation prédéterminée pour entrer en rotation sous l'effet de son ressort.This acceleration sensor cooperates with a timer device 32 which in turn releases the rotor 14 after a predetermined time delay to rotate under the effect of its spring.

La construction générale de la fusée en ce qui concerne le dispositif de mise à feu 12, le détecteur d'accélération 31, le dispositif de temporisation 32 et le rotor 14 pourra par exemple être du type décrit dans le brevet suisse 650.330 dont le texte fait partie intégrante de la présente demande.The general construction of the rocket with regard to the firing device 12, the acceleration detector 31, the timing device 32 and the rotor 14 may for example be of the type described in the patent Swiss 650,330 the text of which forms an integral part of this application.

Mis à part le détecteur d'accélération, les moyens de sécurité 30 comportent au moins un second dispositif de sécurité 35 sensible à un second phénomène physique discriminatoire, à savoir la pression dynamique d'air due au projectile en vol, qui est agencé de façon à autoriser la mise à feu uniquement lorsque la pression dynamique atteint une valeur prédéterminée correspondant à une vitesse de déplacement donnée du projectile et à l'empêcher dans le cas contraire.Apart from the acceleration detector, the security means 30 comprise at least a second security device 35 responsive to a second discriminatory physical phenomenon, namely the dynamic air pressure due to the projectile in flight, which is arranged in a manner to authorize the firing only when the dynamic pressure reaches a predetermined value corresponding to a given displacement speed of the projectile and to prevent it otherwise.

Ce second dispositif de sécurité 35 comprend une membrane en matière élastique 36, par exemple de la matière plastique, logée dans une chambre 37. Les bords de la membrane sont retenus par les parois de la chambre 37 par insertion à la jonction d'une pièce supérieure 38 et d'une pièce inférieure 39 du bâti 17. Un canal 40 relie un orifice 41 situé à la partie frontale 42 de la fusée à la chambre 37. Ce canal 40 possède une première portion 45 avec une section plus petite qu'une seconde portion 46 située plus en arrière. A l'état de repos, la première portion 45 du canal 40 est entièrement obturée par un bouchon 47. Lorsque le projectile est en vol, la pression dynamique exercée par l'air déplace le bouchon en arrière dans la seconde portion 46 et ouvre ainsi le canal 40 de façon que la membrane 36 soit soumise à la pression dynamique du projectile en vol.This second safety device 35 comprises a membrane of elastic material 36, for example plastic, housed in a chamber 37. The edges of the membrane are retained by the walls of the chamber 37 by insertion at the junction of a room 38 and a lower part 39 of the frame 17. A channel 40 connects an orifice 41 located at the front portion 42 of the rocket chamber 37. This channel 40 has a first portion 45 with a smaller section than a second portion 46 located further back. In the idle state, the first portion 45 of the channel 40 is completely closed by a plug 47. When the projectile is in flight, the dynamic pressure exerted by the air moves the plug back into the second portion 46 and thus opens the channel 40 so that the membrane 36 is subjected to the dynamic pressure of the projectile in flight.

La partie inférieure 48 de la chambre 37 est arrondie et reliée à un canal 49 de mise à l'air. Le dispositif de sécurité 35 présente en outre un organe de transmission 50 destiné à agir sur le rotor en fonction de la pression dynamique.The lower portion 48 of the chamber 37 is rounded and connected to a channel 49 venting. The safety device 35 further has a transmission member 50 for acting on the rotor as a function of the dynamic pressure.

Cet organe est constitué par une lame métallique flexible 51 montée sur la pièce inférieure 39. Une portion terminale 54 de cette lame 51 est insérée et maintenue entre les pièces 38 et 39 et disposée sous la membrane 36. La lame 51 suit ensuite la pièce 39 et se prolonge par une extrémité 55 en direction du rotor 14 pour coopérer avec la came 21 prévue à la périphérie de ce dernier.This member is constituted by a flexible metal blade 51 mounted on the lower piece 39. An end portion 54 of the blade 51 is inserted and held between the parts 38 and 39 and disposed under the membrane 36. The blade 51 then follows the piece 39 and is extended by an end 55 in the direction of the rotor 14 to cooperate with the cam 21 provided at the periphery of the latter.

Cette came 21 comprend une portion évidée 60 (fig. 1 A et 1B) permettant la rotation du rotor 14 lorsque le dispositif de temporisation l'a libéré. Elle comprend en outre une portion d'arrêt 61 (figures 2A et 2B) comportant une première butée 62 agencée de façon à arrêter le rotor 14 dans sa rotation lorsque l'extrémité 55 de la lame 51 n'a pas été levée et une seconde butée 63 destinée à retenir la lame flexible 51 dans sa position basse dans une encoche 64 formée par la première et la seconde butées.This cam 21 comprises a recessed portion 60 (FIGS 1A and 1B) allowing rotation of the rotor 14 when the delay device has released it. It further comprises a stop portion 61 (Figures 2A and 2B) having a first stop 62 arranged to stop the rotor 14 in its rotation when the end 55 of the blade 51 has not been raised and a second stop 63 for holding the flexible blade 51 in its lower position in a notch 64 formed by the first and second stops.

La fusée fonctionne de la manière suivante : Avant le départ du coup du projectile, les éléments mobiles de la fusée se trouvent dans la position de repos représentée aux figures 1 A et 1B. Après le départ du coup, le bouchon 47 est rapidement reculé pour ouvrir la canal d'air 40 de façon qu'une pression dynamique d'air s'établit dans la chambre 37. La membrane 36 et la portion 54 de la lame 51 sont incurvées vers le bas lorsque cette pression dynamique atteint une valeur prédéterminée suffisante, par exemple 3 bars. La lame flexible 51 forme alors dans sa partie médiane une boucle 66 incurvée vers le haut (figure 3A) et son extrémité inférieure 55 est levée au dessus du niveau de la portion d'arrêt 61.The rocket operates as follows: Before the launch of the projectile, the moving elements of the rocket are in the rest position shown in Figures 1 A and 1B. After the start of the stroke, the plug 47 is rapidly moved back to open the air channel 40 so that a dynamic air pressure is established in the chamber 37. The membrane 36 and the portion 54 of the blade 51 are curved downwards when this dynamic pressure reaches a sufficient predetermined value, for example 3 bars. The flexible blade 51 then forms in its middle part an upward curved loop 66 (FIG. 3A) and its lower end 55 is raised above the level of the stop portion 61.

En admettant que l'accélération du projectile possède une valeur prédéterminée suffisante, par exemple 2500g, le détecteur d'accélération 31 est activé pour mettre en marche le dispositif de temporisation 32 qui après une durée prédéterminée libère la rotation du rotor 14. Celui-ci n'est pas arrêté par la lame 51 levée au dessus de la portion d'arrêt 61 et effectue une rotation angulaire prédéterminée pour placer l'une ou l'autre des amorces 18,19 dans la chaîne pyrotechnique.Assuming that the acceleration of the projectile has a sufficient predetermined value, for example 2500 g, the acceleration detector 31 is activated to start the delay device 32 which after a predetermined time releases the rotation of the rotor 14. is not stopped by the blade 51 raised above the stop portion 61 and performs an angular rotation predetermined to place one or the other of the primers 18,19 in the pyrotechnic chain.

Lorsque la vitesse du projectile est trop basse et la pression dynamique n'atteint pas une valeur suffisante, par exemple inférieure à 3 bars, mais que l'accélération de la fusée a été plus élevée que la valeur prédéterminée minimale, le rotor 14 est mis en rotation, mais sa rotation est arrêtée par la portion d'arrêt 61, figures 2A et 2B. En outre, l'extrémité 55 est bloquée dans l'encoche 64 sous l'effet du ressort 15 du rotor 14. Le dispositif de mise à feu est ainsi arrêté et définitivement bloqué et aucune des amorces 18,19 n'est alignée avec la chaîne pyrotechnique.When the speed of the projectile is too low and the dynamic pressure does not reach a sufficient value, for example less than 3 bar, but the rocket acceleration has been higher than the minimum predetermined value, the rotor 14 is set in rotation, but its rotation is stopped by the stop portion 61, FIGS. 2A and 2B. In addition, the end 55 is locked in the notch 64 under the effect of the spring 15 of the rotor 14. The firing device is thus stopped and permanently blocked and none of the primers 18, 19 is aligned with the pyrotechnic chain.

Ainsi, les moyens de sécurité comportent, mis à part le ou les détecteurs d'accélération, au moins un autre dispositif de sécurité sensible à un autre facteur de discrimination, ici la pression dynamique due à la vitesse du projectile en vol. Cette pression dynamique agit tout d'abord sur le bouchon 47 qui constitue ainsi un premier élément de sécurité et ensuite sur le dispositif de sécurité 35 avec sa lame de commande 51. La sécurité de mise à feu est ainsi au moins doublée, tout en disposant d'une construction simple, fiable et comportant peu de composants.Thus, the safety means comprise, apart from the acceleration sensor or detectors, at least one other safety device sensitive to another discriminating factor, here the dynamic pressure due to the speed of the projectile in flight. This dynamic pressure acts first on the plug 47 which thus constitutes a first safety element and then on the safety device 35 with its control blade 51. The safety of ignition is thus at least doubled, while having a simple, reliable construction with few components.

Il est bien entendu que le mode de réalisation décrit ci-dessus ne présente aucun caractère limitatif et qu'il peut recevoir toutes modifications désirables à l'intérieur du cadre tel que défini par la revendication 1. En particulier, les moyens de sécurité pourront encore présenter d'autres éléments, par exemple sensibles à la rotation dans le cas de projectiles girants.It is understood that the embodiment described above is not limiting and that it can receive any desirable modifications within the frame as defined by claim 1. In particular, the security means can still present other elements, for example sensitive to rotation in the case of gyrating projectiles.

Claims (7)

  1. Projectile fuze with an ignition device (12) with at least one detonator carrier rotor (14) rotatably mounted and able to be rotated by a spring (15) so as to be displaced from an initial security position to at least one ignition position, and with means of security (30) including a security device (35) that is responsive to the dynamic air pressure caused by the projectile in flight, and has a detector element (36) able to be displaced and/or deformed under the influence of this dynamic pressure so as to allow ignition when this dynamic pressure attains a predetermined first value that corresponds to a given speed of the projectile, and inhibit ignition in the opposite case, characterised in that the detector element consists of a membrane (36) housed in a chamber (37) that on a first side of the membrane is connected to the outside of the projectile by a channel (40), this membrane (36) being able to warp under the dynamic pressure and act upon a first segment (54) of a transmission element of which a second segment (55) is intended to cooperate with the detonator carrier rotor (14), the means of security (30) including in addition an acceleration detector (31) arranged so as to block the ignition device (12) when the acceleration of the projectile (11) falls short of a predetermined second value, and to liberate the ignition device (12) when the acceleration is equal to or higher than this predetermined second value, the membrane (36) being arranged so as to control the movement of the transmission element (50) in such a way that,
    a) on the one hand its second segment (55) be spread away from a stopping segment (61) of rotor (14) and authorise rotation of this rotor toward said at least one ignition position, when the dynamic pressure attains the predetermined first value and the acceleration detector has liberated the detonator carrier rotor (14), and
    b) on the other hand this second segment (55) come in contact with the stopping segment (61) of rotor (14) so long as the dynamic pressure has not attained the predetermined first value, so that a first retaining element (62) of the stopping segment (61) stops rotation of the rotor thus inhibiting the ignition, and so that a second retaining element (63, 64) of this stopping segment (61) holds back the second segment (55) of the transmission element (50) so as to block the ignition device (12) in a position other than the ignition position.
  2. Fuze according to claim 1, characterised in that the transmission element (50) consists of a flexible strip (51) having a first segment (54) disposed underneath the membrane (36) so as to warp together with the membrane in such a way that its second segment (55) be spread away from the stopping segment (61) of rotor (14) when the dynamic pressure attains the predetermined first value.
  3. Fuze according to claim 1 or 2, characterised in that the second retaining element (63, 64) is arranged so as to keep the second segment (55) unter the influence of spring (15) driving the rotor (14) once the acceleration detector (31) has liberated rotor (14).
  4. Fuze according to claim 1, characterised in that on a second side of the membrane (36), the chamber (37) has a rounded portion (48) connected with an aeration channel (49).
  5. Fuze according to one of claims 1 to 4, characterised in that the security device (35) includes a first and a second part (38, 39) joined together and holding between them the membrane (36) and the first segment (54) of the transmission element.
  6. Fuze according to one of claims 1 to 5, characterised in that the acceleration detector (31) cooperates with a time delay element (32) arranged so as to control the ignition procedure and the rotation of the detonator carrier rotor (14).
  7. Fuze according to claim 1, characterised in that it comprises a plug (47) that in a position of rest sits in a first segment (45) of said channel (40) blocked by it but can be displaced by the dynamic pressure to a second segment (46) of the channel not blocked by it.
EP03816041A 2003-02-27 2003-02-27 Projectile fuze Expired - Lifetime EP1597534B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IB2003/000745 WO2004076962A1 (en) 2003-02-27 2003-02-27 Projectile fuze

Publications (2)

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EP1597534A1 EP1597534A1 (en) 2005-11-23
EP1597534B1 true EP1597534B1 (en) 2007-10-10

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Application Number Title Priority Date Filing Date
EP03816041A Expired - Lifetime EP1597534B1 (en) 2003-02-27 2003-02-27 Projectile fuze

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US (1) US7490551B2 (en)
EP (1) EP1597534B1 (en)
AT (1) ATE375495T1 (en)
AU (1) AU2003209529A1 (en)
CA (1) CA2517200C (en)
DE (1) DE60316848T2 (en)
DK (1) DK1597534T3 (en)
ES (1) ES2295703T3 (en)
HK (1) HK1083695A1 (en)
WO (1) WO2004076962A1 (en)

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Publication number Priority date Publication date Assignee Title
US8291825B2 (en) 2009-09-10 2012-10-23 Alliant Techsystems Inc. Methods and apparatuses for electro-mechanical safety and arming of a projectile
US9068807B1 (en) * 2009-10-29 2015-06-30 Lockheed Martin Corporation Rocket-propelled grenade
US9140528B1 (en) 2010-11-16 2015-09-22 Lockheed Martin Corporation Covert taggant dispersing grenade
US9423222B1 (en) 2013-03-14 2016-08-23 Lockheed Martin Corporation Less-than-lethal cartridge
US9200876B1 (en) 2014-03-06 2015-12-01 Lockheed Martin Corporation Multiple-charge cartridge
RU2748828C1 (en) * 2020-05-12 2021-05-31 Российская Федерация в лице Министерства обороны РФ Method and device for initiating an air-dynamic steering drive of a guided aerial bomb, a method for checking the readiness of an air-dynamic steering drive before dropping a guided aerial bomb, an air-dynamic steering gear and control equipment for an air-dynamic steering drive of an aerial bomb

Family Cites Families (11)

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Publication number Priority date Publication date Assignee Title
US3382805A (en) * 1967-01-31 1968-05-14 Navy Usa Air responsive delay arming device
US3927617A (en) * 1969-01-22 1975-12-23 Us Navy Post-launch dual pressure sensitive arming device
US3804020A (en) * 1973-04-17 1974-04-16 Avco Corp Safing and arming system for a projectile fuze and fluidic control means for use therewith
US3961577A (en) * 1975-05-12 1976-06-08 The United States Of America As Represented By The Secretary Of The Navy Air driven energy storing fuze safing and arming mechanism
US4002123A (en) * 1975-07-11 1977-01-11 The United States Of America As Represented By The Secretary Of The Army Dual channel redundant fuze
US4188886A (en) * 1978-05-26 1980-02-19 The United States Of America As Represented By The Secretary Of The Navy Pressure probe for safety-arming device
US4380197A (en) * 1978-05-26 1983-04-19 The United States Of America As Represented By The Secretary Of The Navy Safety and arming device/contact fuze
US4526104A (en) * 1982-10-14 1985-07-02 The United States Of America As Represented By The Secretary Of The Navy Safety-arming device
CH650330A5 (en) 1983-03-07 1985-07-15 Mefina Sa ROCKET HEAD FOR PROJECTILE.
DE3828949A1 (en) * 1988-08-26 1990-03-08 Messerschmitt Boelkow Blohm SECURITY DEVICE
CH693116A5 (en) 1998-06-24 2003-02-28 Miltec S A Projectile fuse has safety mechanism with dynamic air pressure detector incorporating elastic membrane and flexible strip

Also Published As

Publication number Publication date
EP1597534A1 (en) 2005-11-23
DE60316848D1 (en) 2007-11-22
DK1597534T3 (en) 2008-02-11
US20060196382A1 (en) 2006-09-07
HK1083695A1 (en) 2006-07-07
AU2003209529A1 (en) 2004-09-17
CA2517200A1 (en) 2004-09-10
DE60316848T2 (en) 2008-07-17
ES2295703T3 (en) 2008-04-16
ATE375495T1 (en) 2007-10-15
US7490551B2 (en) 2009-02-17
WO2004076962A1 (en) 2004-09-10
CA2517200C (en) 2011-02-08

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