EP1597534A1 - Projectile fuze - Google Patents

Projectile fuze

Info

Publication number
EP1597534A1
EP1597534A1 EP03816041A EP03816041A EP1597534A1 EP 1597534 A1 EP1597534 A1 EP 1597534A1 EP 03816041 A EP03816041 A EP 03816041A EP 03816041 A EP03816041 A EP 03816041A EP 1597534 A1 EP1597534 A1 EP 1597534A1
Authority
EP
European Patent Office
Prior art keywords
dynamic pressure
firing
projectile
rotor
rocket
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.)
Granted
Application number
EP03816041A
Other languages
German (de)
French (fr)
Other versions
EP1597534B1 (en
Inventor
Jean-Pierre Golay
Olivier Pronini
Claude Robert-Nicoud
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SN Technologies SA
Original Assignee
SN Technologies SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SN Technologies SA filed Critical SN Technologies SA
Publication of EP1597534A1 publication Critical patent/EP1597534A1/en
Application granted granted Critical
Publication of EP1597534B1 publication Critical patent/EP1597534B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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 safety means intended to allow firing of the projectile only under predetermined conditions.
  • Rockets of this type are known, for example described in patent CH 650,330.
  • the safety means of these rockets generally comprise an acceleration detector cooperating with a timing device.
  • the object of the present invention is to create a rocket having even greater firing safety, very reliable operation, simple construction and having a small number of components.
  • the rocket according to the invention is characterized for this purpose by the fact that the safety means comprise a detection device sensitive to the dynamic air pressure due to the projectile in flight and arranged so as to authorize the firing of the projectile when this dynamic pressure reaches a predetermined dynamic pressure value corresponding to a given speed of the projectile and to prevent firing of the projectile when the dynamic pressure does not reach this predetermined pressure value.
  • the safety means comprise a detection device sensitive to the dynamic air pressure due to the projectile in flight and arranged so as to authorize the firing of the projectile when this dynamic pressure reaches a predetermined dynamic pressure value corresponding to a given speed of the projectile and to prevent firing of the projectile when the dynamic pressure does not reach this predetermined pressure value.
  • the dynamic pressure created by the projectile in flight constitutes an additional safety criterion making it possible to eliminate any risk of unwanted ignition.
  • such a device allows very high security and reliability, while having a simple construction with a small number of components.
  • said detection device comprises a detector element capable of being at least partially displaced and / or deformed under the influence of the dynamic air pressure to authorize firing when the dynamic pressure reaches the predetermined value or to prevent otherwise igniting.
  • said detector element is capable of occupying a rest position and a firing position when said dynamic pressure value is reached and by the fact that the safety means are arranged so as to permanently prevent the element detector to occupy the firing position when the dynamic pressure value is not reached after a predetermined duration from the start of the projectile shot.
  • the safety of the rocket is thus further increased by the fact that the firing mechanism is permanently blocked when the predetermined speed is not reached in a given period of time.
  • the detector element is housed in a chamber of the rocket connected by a channel terminating in an orifice located at the front part of the rocket and by the fact that it comprises a transmission member capable of allow the ignition or to interrupt the ignition procedure.
  • the dynamic pressure detection device is thus well protected from any deterioration before or during the flight.
  • said detector element comprises an elastic membrane retained at its edge in said chamber and capable of bending under dynamic pressure, this membrane acting on said transmission member constituted by a flexible blade so as to deform it and / or move it to allow firing.
  • 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 rotor in the three different positions.
  • the rocket 10 the outer contour of which is sketched in phantom in FIG. 3A, is intended to be mounted on the front part of a projectile 11 by any suitable means, favorably by screwing.
  • a firing device 12 of which only part is shown in the form of a primer rotor 14 mounted rotating on a shaft 16 secured to the frame 17 of the rocket.
  • This rotor 14 comprises primers 18, 19 capable of being aligned by rotation of the rotor with a pyrotechnic chain not illustrated, comprising in a known manner for example a detonator intended to communicate the firing of the explosive charge of the projectile.
  • the rotor is capable of being rotated by a spring 15 to be moved from an initial safety position (FIG. 1B) to one or the 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 detector 31 arranged so as to block the firing device 12 when the acceleration of the projectile 11 is less than a predetermined value and at release the firing device and start the firing procedure when the acceleration is equal to or greater than this predetermined value.
  • This acceleration detector cooperates with a timer device 32 which in turn frees the rotor 14 after a predetermined delay time to enter into rotation 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 Swiss patent 650,330, the text of which makes an integral part of this application.
  • the security means 30 comprise at least one second security device 35 sensitive to a second discriminatory physical phenomenon, namely the dynamic air pressure due to the projectile in flight, which is arranged so to authorize firing only when the dynamic pressure reaches a predetermined value corresponding to a given speed of movement of the projectile and to prevent it otherwise.
  • This second safety device 35 comprises a membrane of elastic material 36, for example of 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 part. upper 38 and a lower part 39 of the frame 17.
  • a channel 40 connects an orifice 41 located at the front part 42 of the rocket to the chamber 37.
  • This channel 40 has a first portion 45 with a section smaller 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 in 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 part 48 of the chamber 37 is rounded and connected to a venting channel 49.
  • the safety device 35 also has a transmission member 50 intended to act on the rotor as a function of the dynamic pressure. This member is constituted by a flexible metal blade 51 mounted on the lower part 39.
  • This cam 21 includes a recessed portion 60 (FIGS. 1 A and 1 B) allowing the rotation of the rotor 14 when the timing device has released it. It further comprises a stop portion 61 (FIGS. 2A and 2B) comprising a first stop 62 arranged so as to stop the rotor 14 in its rotation when the end 55 of the blade 51 has not been lifted and a second stop 63 intended to retain the flexible blade 51 in its low position in a notch 64 formed by the first and second stops.
  • the rocket operates in the following manner: Before the start of the projectile shot, the mobile elements of the rocket are in the rest position shown in FIGS. 1A and 1B. After the start of the shot, the cap 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 downward when this dynamic pressure reaches a predetermined value sufficient, for example 3 bars. The flexible blade 51 then forms in its middle part a loop 66 curved upwards (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 period releases the rotation of the rotor 14. The latter 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 projectile speed is too low and the dynamic pressure does not reach a sufficient value, for example less than 3 bars, but the acceleration of the rocket has been higher than the minimum predetermined value, the rotor 14 is put in rotation, but its rotation is stopped by the stop portion 61, FIGS. 2A and 2B. In addition, the end 55 is blocked in the notch 64 under the effect of the spring 15 of the rotor 14. The firing device is thus stopped and definitively blocked and none of the primers 18, 19 is aligned with the pyrotechnic chain.
  • the safety means comprise, apart from the acceleration detector (s), at least one other safety device sensitive to another factor of discrimination, 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 firing safety is thus at least doubled, while having simple, reliable and with few components.
  • the security means may also present other elements, for example sensitive to rotation in the case of gyrating projectiles.
  • the acceleration sensor could be omitted.
  • the configuration of channel 40 and chamber 37 could be very different.
  • any other dynamic pressure sensing element which can be at least partially displaced and / or deformed under the influence of the pressure.
  • dynamic such as a valve biased by a spring against a rest position, a braked impeller rotated by air under dynamic pressure.
  • the detector element can cooperate with any mechanical or electrical component of the pyrotechnic chain. In the case of an electric rocket, it may for example short-circuit the firing charge when the speed of the projectile is insufficient. It could also act on the timing device unlocking it only under the predetermined dynamic pressure conditions.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Electromagnets (AREA)
  • Air Bags (AREA)
  • Separation By Low-Temperature Treatments (AREA)
  • Control Of Combustion (AREA)
  • Fuses (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Measuring Fluid Pressure (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
  • Compositions Of Macromolecular Compounds (AREA)
  • Toys (AREA)

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

FUSEE DE PROJECTILE PROJECTILE ROCKET
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 safety means intended to allow firing of the projectile only under predetermined conditions.
On connaît des fusées de ce type par exemple décrit dans le brevet CH 650.330. Les moyens de sécurité de ces fusées comportent généralement un détecteur d'accélération coopérant avec un dispositif de temporisation.Rockets of this type are known, for example described in patent CH 650,330. The safety means of these rockets generally comprise an acceleration detector cooperating with a timing device.
La présente invention a pour but de créer une fusée possédant une sécurité de mise à feu encore plus grande, d'un fonctionnement très fiable, d'une construction simple et comportant un nombre de composants faible.The object of the present invention is to create a rocket having even greater firing safety, very reliable operation, simple construction and having a small number of components.
La fusée conformément à l'invention est caractérisée à cet effet par le fait que les moyens de sécurité comportent un dispositif de détection sensible à la pression dynamique d'air due au projectile en vol et agencé de façon à autoriser la mise à feu du projectile lorsque cette pression dynamique atteint une valeur de pression dynamique prédéterminée correspondant à une vitesse donnée du projectile et à empêcher la mise à feu du projectile lorsque la pression dynamique n'atteint pas cette valeur de pression prédéterminée.The rocket according to the invention is characterized for this purpose by the fact that the safety means comprise a detection device sensitive to the dynamic air pressure due to the projectile in flight and arranged so as to authorize the firing of the projectile when this dynamic pressure reaches a predetermined dynamic pressure value corresponding to a given speed of the projectile and to prevent firing of the projectile when the dynamic pressure does not reach this predetermined pressure value.
La pression dynamique créée par le projectile en vol constitue un critère de sécurité supplémentaire permettant d'éliminer tous risques de mise à feu indésirée. En outre, un tel dispositif permet une sécurité et fiabilité très grandes, tout en ayant une construction simple avec un faible nombre de composants.The dynamic pressure created by the projectile in flight constitutes an additional safety criterion making it possible to eliminate any risk of unwanted ignition. In addition, such a device allows very high security and reliability, while having a simple construction with a small number of components.
Favorablement, ledit dispositif de détection comprend un élément détecteur susceptible d'être au moins partiellement déplacé et /ou déformé sous l'influence de la pression dynamique d'air pour autoriser la mise à feu lorsque la pression dynamique atteint la valeur prédéterminée ou pour empêcher la mise à feu dans le cas contraire. Ces caractéristiques assurent un fonctionnement particulièrement fiable.Favorably, said detection device comprises a detector element capable of being at least partially displaced and / or deformed under the influence of the dynamic air pressure to authorize firing when the dynamic pressure reaches the predetermined value or to prevent otherwise igniting. These features ensure particularly reliable operation.
De façon avantageuse, ledit élément détecteur est susceptible d'occuper une position de repos et une position de mise à feu lorsque ladite valeur de pression dynamique est atteinte et par le fait que les moyens de sécurité sont agencés de façon à empêcher définitivement l'élément détecteur d'occuper la position de mise à feu lorsque la valeur de pression dynamique n'est pas atteinte après une durée prédéterminée à compter du départ du coup du projectile.Advantageously, said detector element is capable of occupying a rest position and a firing position when said dynamic pressure value is reached and by the fact that the safety means are arranged so as to permanently prevent the element detector to occupy the firing position when the dynamic pressure value is not reached after a predetermined duration from the start of the projectile shot.
La sécurité de la fusée est ainsi encore augmentée du fait que le mécanisme de mise à feu est définitivement bloqué lorsque la vitesse prédéterminée n'est pas atteinte dans un laps de temps donné.The safety of the rocket is thus further increased by the fact that the firing mechanism is permanently blocked when the predetermined speed is not reached in a given period of time.
Selon un mode d'exécution préféré, l'élément détecteur est logé dans une chambre de la fusée reliée par un canal aboutissement à un orifice situé à la partie frontale de la fusée et par le fait qu'il comprend un organe de transmission susceptible de permettre la mise à feu ou d'interrompre la procédure de mise à feu.According to a preferred embodiment, the detector element is housed in a chamber of the rocket connected by a channel terminating in an orifice located at the front part of the rocket and by the fact that it comprises a transmission member capable of allow the ignition or to interrupt the ignition procedure.
Le dispositif de détection à pression dynamique est ainsi bien protégé de toute détérioration avant ou pendant le vol.The dynamic pressure detection device is thus well protected from any deterioration before or during the flight.
Très favorablement, ledit élément détecteur comprend une membrane élastique retenue à sa bordure dans ladite chambre et susceptible de s'incurver sous la pression dynamique, cette membrane agissant sur ledit organe de transmission constitué par une lame flexible de façon à la déformer et/ou de la déplacer pour permettre la mise à feu.Very favorably, said detector element comprises an elastic membrane retained at its edge in said chamber and capable of bending under dynamic pressure, this membrane acting on said transmission member constituted by a flexible blade so as to deform it and / or move it to allow firing.
Cette construction est particulièrement simple et fiable permettant d'obtenir une fusée à sécurité doublée et d'un prix de revient très modéré. 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.This construction is particularly simple and reliable, making it possible to obtain a rocket with double safety and a very moderate cost price. Other advantages appear from the characteristics expressed in the dependent claims and from the description setting out below the invention more in detail with the aid of drawings which schematically represent an example of an embodiment.
Les figures 1 A, 2A et 3A représentent la fusée en coupe partielle dans trois positions différentes. Les figures 1 B, 2B et 3B sont des vues en plan du rotor porte-amorces dans les trois positions différentes.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 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.With reference to FIGS. 1A to 3A, the rocket 10, the outer contour of which is sketched in phantom in FIG. 3A, is intended to be mounted on the front part of a projectile 11 by any suitable means, favorably by screwing. Like all rockets, it includes a firing device 12 of which only part is shown, in the form of a primer rotor 14 mounted rotating on a shaft 16 secured to the frame 17 of the rocket. This rotor 14 comprises primers 18, 19 capable of being aligned by rotation of the rotor with a pyrotechnic chain not illustrated, comprising in a known manner for example a detonator intended to communicate the firing of 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 1 B) 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 capable of being rotated by a spring 15 to be moved from an initial safety position (FIG. 1B) to one or the 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. 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.The rocket comprises a series of safety means 30 comprising, inter alia, at least one acceleration detector 31 arranged so as to block the firing device 12 when the acceleration of the projectile 11 is less than a predetermined value and at release the firing device and start the firing procedure when the acceleration is equal to or greater than this predetermined value. This acceleration detector cooperates with a timer device 32 which in turn frees the rotor 14 after a predetermined delay time to enter into rotation 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 Swiss patent 650,330, the text of which makes 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. 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. 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. 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.Aside from the acceleration detector, the security means 30 comprise at least one second security device 35 sensitive to a second discriminatory physical phenomenon, namely the dynamic air pressure due to the projectile in flight, which is arranged so to authorize firing only when the dynamic pressure reaches a predetermined value corresponding to a given speed of movement of the projectile and to prevent it otherwise. This second safety device 35 comprises a membrane of elastic material 36, for example of 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 part. upper 38 and a lower part 39 of the frame 17. A channel 40 connects an orifice 41 located at the front part 42 of the rocket to the chamber 37. This channel 40 has a first portion 45 with a section smaller 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 in 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 part 48 of the chamber 37 is rounded and connected to a venting channel 49. The safety device 35 also has a transmission member 50 intended to act on the rotor as a function of the dynamic pressure. This member is constituted by a flexible metal blade 51 mounted on the lower part 39. An end portion 54 of this blade 51 is inserted and held between the parts 38 and 39 and disposed under the membrane 36. The blade 51 then follows the part 39 and is extended by one 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 1 B) 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 includes a recessed portion 60 (FIGS. 1 A and 1 B) allowing the rotation of the rotor 14 when the timing device has released it. It further comprises a stop portion 61 (FIGS. 2A and 2B) comprising a first stop 62 arranged so as to stop the rotor 14 in its rotation when the end 55 of the blade 51 has not been lifted and a second stop 63 intended to retain the flexible blade 51 in its low 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 1 B. 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 in the following manner: Before the start of the projectile shot, the mobile elements of the rocket are in the rest position shown in FIGS. 1A and 1B. After the start of the shot, the cap 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 downward when this dynamic pressure reaches a predetermined value sufficient, for example 3 bars. The flexible blade 51 then forms in its middle part a loop 66 curved upwards (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 period releases the rotation of the rotor 14. The latter 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 projectile speed is too low and the dynamic pressure does not reach a sufficient value, for example less than 3 bars, but the acceleration of the rocket has been higher than the minimum predetermined value, the rotor 14 is put in rotation, but its rotation is stopped by the stop portion 61, FIGS. 2A and 2B. In addition, the end 55 is blocked in the notch 64 under the effect of the spring 15 of the rotor 14. The firing device is thus stopped and definitively 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 detector (s), at least one other safety device sensitive to another factor of discrimination, 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 firing safety is thus at least doubled, while having simple, reliable and 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. Dans une version simplifiée, le détecteur d'accélération pourrait être supprimé. La configuration du canal 40 et de la chambre 37 pourrait être très différente. Au lieu d'une membrane 36, on pourra prévoir tout autre élément détecteur de pression dynamique qui puisse être au moins partiellement déplacé et /ou déformé sous l'influence de la pression dynamique, tel qu'un clapet sollicité par un ressort contre une position de repos, une roue à ailettes freinée mise en rotation par l'air sous pression dynamique. L'élément détecteur pourra coopérer avec tout composant mécanique ou électrique de la chaîne pyrotechnique. Dans le cas d'une fusée électrique, il pourra par exemple court-circuiter la charge de mise à feu lorsque la vitesse du projectile est insuffisante. Il pourrait également agir sur le dispositif de temporisation le débloquant uniquement sous les conditions de pression dynamique prédéterminées. It is understood that the embodiment described above has no limiting character and that it can receive any desirable modifications within the framework as defined by claim 1. In particular, the security means may also present other elements, for example sensitive to rotation in the case of gyrating projectiles. In a simplified version, the acceleration sensor could be omitted. The configuration of channel 40 and chamber 37 could be very different. Instead of a membrane 36, it is possible to provide any other dynamic pressure sensing element which can be at least partially displaced and / or deformed under the influence of the pressure. dynamic, such as a valve biased by a spring against a rest position, a braked impeller rotated by air under dynamic pressure. The detector element can cooperate with any mechanical or electrical component of the pyrotechnic chain. In the case of an electric rocket, it may for example short-circuit the firing charge when the speed of the projectile is insufficient. It could also act on the timing device unlocking it only under the predetermined dynamic pressure conditions.

Claims

REVENDICATIONS
1. Fusée de projectile comprenant un dispositif de mise à feu (12) et des moyens de sécurité (30) destinés à permettre la mise à feu du projectile uniquement sous des conditions prédéterminées, caractérisée par le fait que les moyens de sécurité comportent un dispositif de détection (35) sensible à la pression dynamique d'air due au projectile (11) en vol et agencé de façon à autoriser la mise à feu du projectile lorsque cette pression dynamique atteint une valeur de pression dynamique prédéterminée correspondant à une vitesse donnée du projectile et à empêcher la mise à feu du projectile lorsque la pression dynamique n'atteint pas cette valeur de pression prédéterminée.1. Projectile rocket comprising a firing device (12) and safety means (30) intended to allow firing of the projectile only under predetermined conditions, characterized in that the safety means comprise a device detection (35) sensitive to the dynamic air pressure due to the projectile (11) in flight and arranged so as to authorize the firing of the projectile when this dynamic pressure reaches a predetermined dynamic pressure value corresponding to a given speed of the and to prevent firing of the projectile when the dynamic pressure does not reach this predetermined pressure value.
2. Fusée selon la revendication 1 , caractérisée par le fait que ledit dispositif de détection (35) comprend un élément détecteur (36) susceptible d'être au moins partiellement déplacé et /ou déformé sous l'influence de la pression dynamique d'air pour autoriser la mise à feu lorsque la pression dynamique atteint la valeur prédéterminée ou pour empêcher la mise à feu dans le cas contraire.2. Rocket according to claim 1, characterized in that said detection device (35) comprises a detector element (36) capable of being at least partially displaced and / or deformed under the influence of the dynamic air pressure to authorize ignition when the dynamic pressure reaches the predetermined value or to prevent ignition otherwise.
3. Fusée selon la revendication 2, caractérisée par le fait que ledit élément détecteur (36,50) est susceptible d'occuper une position de repos et une position de mise à feu lorsque ladite valeur de pression dynamique est atteinte et par le fait que les moyens de sécurité (30) sont agencés de façon à empêcher définitivement l'élément détecteur (36,50) d'occuper la position de mise à feu lorsque la valeur de pression dynamique n'est pas atteinte après une durée prédéterminée à compter du départ du coup du projectile. 3. Rocket according to claim 2, characterized in that said detector element (36.50) is capable of occupying a rest position and a firing position when said dynamic pressure value is reached and by the fact that the safety means (30) are arranged so as to permanently prevent the detector element (36,50) from occupying the firing position when the dynamic pressure value is not reached after a predetermined period from departure of the projectile.
4. Fusée selon la revendication 2 ou 3, caractérisée par le fait que ledit élément détecteur (36) est logé dans une chambre (37) de la fusée reliée par un canal (40) à un orifice (41) situé à la partie frontale (42) de la fusée et par le fait qu'il comprend un organe de transmission (50) susceptible de permettre la mise à feu ou d'interrompre la procédure de mise à feu.4. Rocket according to claim 2 or 3, characterized in that said detector element (36) is housed in a chamber (37) of the rocket connected by a channel (40) to an orifice (41) located at the front part (42) of the rocket and by the fact that it comprises a transmission member (50) capable of allowing the firing or of interrupting the firing procedure.
5. Fusée selon la revendication 4, caractérisée par le fait que l'élément détecteur comprend une membrane (36,50) élastique retenue à sa bordure dans ladite chambre (37) et susceptible de s'incurver sous la pression dynamique , cette membrane agissant sur ledit organe de transmission (50) constitué par une lame flexible (51) de façon à la déformer et/ou la déplacer pour permettre la mise à feu.5. Rocket according to claim 4, characterized in that the detector element comprises an elastic membrane (36,50) retained at its edge in said chamber (37) and capable of curving under dynamic pressure, this membrane acting on said transmission member (50) constituted by a flexible blade (51) so as to deform and / or move it to allow firing.
6. Fusée selon l'une des revendications 2 à 5, caractérisée par le fait que l'élément détecteur (36,50) coopère avec un élément mécanique mobile (14) susceptible d'être déplacé d'une position initiale vers au moins une position d'ignition après le départ du coup du projectile, l'élément détecteur (36,50) étant agencé de façon à empêcher l'élément mécanique mobile d'être déplacé jusqu'à la position d'ignition lorsque la valeur de pression dynamique n'est pas atteinte et de façon à s'écarter de l'élément mécanique mobile pour que ce dernier puisse atteindre la position d'ignition lorsque la valeur de pression dynamique est atteinte.6. Rocket according to one of claims 2 to 5, characterized in that the detector element (36.50) cooperates with a mobile mechanical element (14) capable of being moved from an initial position to at least one ignition position after the start of the projectile shot, the detector element (36,50) being arranged so as to prevent the movable mechanical element from being moved to the ignition position when the dynamic pressure value is not reached and so as to move away from the movable mechanical element so that the latter can reach the ignition position when the dynamic pressure value is reached.
7. Fusée selon la revendication 6, caractérisée par le fait que l'élément mécanique mobile est constitué par un rotor porte-amorce(s) (14) dont la périphérie coopère avec une portion (55) de la lame flexible (51) et par le fait que cette périphérie comprend un premier élément de retenue (62) empêchant la rotation du rotor jusqu'à la position d'ignition lorsque la portion de la lame flexible (51) n'est pas suffisamment écartée et un deuxième élément de retenue (63,64) agencé de façon à empêcher la lame flexible (51) de s'écarter lorsque la rotation du rotor (14) a été arrêtée par la lame flexible (51).7. Rocket according to claim 6, characterized in that the movable mechanical element is constituted by a primer holder rotor (s) (14) whose periphery cooperates with a portion (55) of the flexible blade (51) and by the fact that this periphery comprises a first retaining element (62) preventing rotation of the rotor to the ignition position when the portion of the flexible blade (51) is not sufficiently apart and a second retaining element (63,64) arranged so as to prevent the flexible blade (51) from moving away when the rotation of the rotor (14) has been stopped by the flexible blade (51).
8. Fusée selon l'une des revendications précédentes, caractérisée par le fait qu'elle comprend au moins un détecteur d'accélération (31) agencé de façon à autoriser ou à empêcher la procédure de mise à feu selon que l'accélération du projectile a atteint ou non une valeur prédéterminée.8. Rocket according to one of the preceding claims, characterized in that it comprises at least one acceleration detector (31) arranged so as to authorize or prevent the firing procedure depending on whether the acceleration of the projectile whether or not it reached a predetermined value.
9. Fusée selon les revendications 7 et 8, caractérisée par le fait que le détecteur d'accélération (31) coopère avec un organe de temporisation (32) agencé de façon à contrôler la procédure de mise à feu et la rotation du rotor porte-amorce (14).9. Rocket according to claims 7 and 8, characterized in that the acceleration detector (31) cooperates with a timing member (32) arranged so as to control the firing procedure and the rotation of the carrier rotor primer (14).
10. Fusée selon l'une des revendications 4 à 9, caractérisée par le fait qu'il comprend un bouchon (47) logé dans la position de repos dans une première portion (45) dudit canal (40) qu'il obture et susceptible d'être déplacé par la pression dynamique vers une seconde portion (46) du canal qu'il n'obture pas. 10. Rocket according to one of claims 4 to 9, characterized in that it comprises a plug (47) housed in the rest position in a first portion (45) of said channel (40) which it closes and can to be moved by dynamic pressure to a second portion (46) of the channel that it does not close.
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

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

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AT (1) ATE375495T1 (en)
AU (1) AU2003209529A1 (en)
CA (1) CA2517200C (en)
DE (1) DE60316848T2 (en)
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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

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CA2517200A1 (en) 2004-09-10
DE60316848T2 (en) 2008-07-17
DE60316848D1 (en) 2007-11-22
US20060196382A1 (en) 2006-09-07
EP1597534B1 (en) 2007-10-10
US7490551B2 (en) 2009-02-17
ES2295703T3 (en) 2008-04-16
WO2004076962A1 (en) 2004-09-10
ATE375495T1 (en) 2007-10-15
DK1597534T3 (en) 2008-02-11
HK1083695A1 (en) 2006-07-07
AU2003209529A1 (en) 2004-09-17
CA2517200C (en) 2011-02-08

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