EP3093609B1 - Système de démarrage pour un missile guide et missile guide pour un tel système de démarrage - Google Patents

Système de démarrage pour un missile guide et missile guide pour un tel système de démarrage Download PDF

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Publication number
EP3093609B1
EP3093609B1 EP16169297.5A EP16169297A EP3093609B1 EP 3093609 B1 EP3093609 B1 EP 3093609B1 EP 16169297 A EP16169297 A EP 16169297A EP 3093609 B1 EP3093609 B1 EP 3093609B1
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EP
European Patent Office
Prior art keywords
guided missile
firing pin
missile
launch tube
pin element
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.)
Active
Application number
EP16169297.5A
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German (de)
English (en)
Other versions
EP3093609A1 (fr
Inventor
Stefan Lehmann
Jörg Lutzenberger
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.)
MBDA Deutschland GmbH
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MBDA Deutschland GmbH
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
Priority claimed from DE102015009823.3A external-priority patent/DE102015009823B4/de
Application filed by MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Priority to PL16169297T priority Critical patent/PL3093609T3/pl
Publication of EP3093609A1 publication Critical patent/EP3093609A1/fr
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Publication of EP3093609B1 publication Critical patent/EP3093609B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0819—Primers or igniters for the initiation of rocket motors, i.e. pyrotechnical aspects thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/045—Rocket or torpedo launchers for rockets adapted to be carried and used by a person, e.g. bazookas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/052—Means for securing the rocket in the launching apparatus

Definitions

  • the present invention relates to a guided missile launch system. Furthermore, the invention relates to a guided missile for use in such a missile launch system.
  • the guided missile launch system is particularly shoulder-based and thus portable for a single user.
  • DE 31 30 963 A1 describes a trigger device for a portable, recoilless anti-tank weapon with a tube with propellant charge, a shaped charge projectile and a primer.
  • the extraction device and the pipe are detachably connected to each other.
  • Object of the invention to provide a guided missile launch system that allows for simple and cost-effective production and assembly safe handling of the missile.
  • the object is achieved by the features of the independent claim.
  • a missile launch system comprising a launch tube and a handle.
  • the launch tube has a steering missile space, which is designed to receive a missile.
  • the starting pipe has a cartridge chamber, which is designed to receive a maneuvering cartridge.
  • both the guided missile space and the cartridge space have a connection to an environment of the launch tube.
  • the guided missile space and the cartridge space are completely separated from each other. Ignition of the maneuver cartridge thus does not lead to an ignition of the missile.
  • the handle is anmontierbar, wherein the handle is also separable from the launch tube at any time.
  • the handle has a striker system for igniting the maneuver cartridge.
  • the guided missile launch system has increased safety in handling. If the starting pipe is separated from the handle, an accidental ignition of the maneuver cartridge is not possible because the associated firing pin system is present in the separate handle.
  • the starting pipe has an opening in which a firing pin element is arranged.
  • the firing pin protrudes into the missile space.
  • the opening of the launch tube thus connects the steering missile space with an environment of the launch tube.
  • the firing pin element advantageously the opening is completely closed.
  • the engagement of the firing pin element in the steering missile space makes it possible to engage the firing pin element in an ignition opening of the guided missile. Since the firing pin element thus engages both in the opening of the launch tube and in the ignition opening of the missile, an axial centering of the opening of the launch tube and the ignition opening of the missile takes place.
  • the missile thus has a predefined orientation within the launch tube.
  • the firing pin member has a collar over which the firing pin member is fixed within the launch tube.
  • a complete implementation of the firing pin element is thus prevented by the opening of the starting pipe. This prevents the risk of accidental ignition of the missile.
  • the collar is designed as a tear-off. If a sufficient force is applied to the firing pin element, the collar fails, as a result of which the firing pin element can be completely transferred from the opening of the launch tube into the firing opening of the guided missile. Within the firing opening of the guided missile, the firing pin element can finally initiate an ignition of the guided missile.
  • the grip piece has a gas channel.
  • the gas passage of the maneuver cartridge space is connected to the firing pin member when the handle is mounted on the launch tube.
  • a gas pressure is created within the gas passage that exerts a resultant force on the striker element.
  • a displacement of the firing pin element takes place in the ignition opening of the guided missile, so that the firing pin element ignites the guided missile.
  • the gas passage is disposed inside the grip, ignition of the maneuver cartridge in the case where the grip is not mounted on the launch tube does not result in displacement of the striker member because the gas passage is absent. In this case, only the gas pressure from the maneuver cartridge would be delivered to an environment of the missile launch system. It can be seen that thus the reliability and safety in handling the missile launch system are significantly increased.
  • the guided missile launch system on an additional element.
  • a gas channel is attached in the additional element.
  • the additional element is particularly advantageous movably mounted on the handle and in particular swung out of the handle or swiveled into the handle.
  • Operational safety is therefore increased in two stages. If the handle is separated from the starting pipe, it is not possible to ignite the maneuver cartridge due to the lack of firing pin system. Nevertheless, if the maneuver cartridge ignited inadvertently, so there is no connection to the missile space, so that the ignition of the maneuver cartridge has no effect on the missile itself. Only with a combination of handle and launch tube ignition of the maneuver cartridge is possible.
  • the launch tube preferably has an additional locking element.
  • the additional locking element of the missile is lockable in the launch tube of the missile launch system.
  • a further manual locking is provided, whereby the missile is held securely and reliably within the missile space.
  • a maneuver cartridge is permanently installed.
  • the maneuver cartridge is not removable by a user. This ensures that the maneuver cartridge is always present, so that a lack of operational capability of the missile launch system is excluded due to a missing maneuver cartridge. Also, an unintentional ignition of the maneuver cartridge is difficult within the launch tube, so there is no risk that the maneuver cartridge is ignited accidentally.
  • the invention further relates to a guided missile for use in a guided missile launch system as previously described.
  • the guided missile has an ignition opening.
  • a firing pin element of the guided missile launch system is insertable.
  • the missile is fixable in a launch tube of the missile launch system.
  • the firing pin element therefore advantageously has the task of keeping the guided missile within the launch tube of the guided missile launch system in a predefined orientation and simultaneously locking it. The lock can only be released when the firing pin element is fully inserted into the ignition opening, whereby the missile is ignited.
  • the ignition opening leads to a thermal battery of the missile.
  • the ignition opening leads to a primer of the thermal battery. In this way it is possible that with the firing pin element on the primer of the thermal battery is beatable. Once the firing pin element strikes the primer cap, the thermal battery is ignited, energizing the missile. This leads to a start of the missile from the guided missile launch system.
  • FIG. 1 schematically shows a guided missile launch system 1 according to an embodiment of the invention.
  • the guided missile launch system 1 comprises a launch tube 2 and a handle 7.
  • the handle 7 is separated from the starting pipe 2.
  • FIG. 2 shows the guided missile launch system 1 from FIG. 1 , wherein the handle 7 is mounted on the starting pipe 2.
  • the guided missile launch system 1 is particularly suitable for launching shoulder-mounted missiles 4.
  • the launch tube 2 serves as a logistic package for the guided missile and to launch the missile. 4
  • the handle 7 is in particular connected only to launch the missile 4 with the launch tube 2 and is used to handle the missile launch system 1, the securing of the missile 4 and the initiation of the ignition process.
  • the guided missile 4 is mounted in the launch tube 2 and locked and secured by two independent locking mechanisms.
  • a first locking mechanism is present such that the guided missile 4 is manually locked to the launch tube.
  • a second locking mechanism consists in a firing pin element 9, which is arranged both within an opening of the starting pipe 2 and within an ignition opening 10 of the guided missile 4.
  • the ignition opening 10 serves as an interface of the missile for initiating and thus for firing the missile. 4
  • the initiation of the guided missile 4 takes place by the targeted application of a arranged in a thermal battery 13 of the missile 4 Anzündhütchens 15 by the firing pin element 9.
  • the firing pin member 9 must be accelerated to pitch on the primer 15. This is initiated by a maneuver cartridge 6.
  • the maneuvering cartridge 6 is arranged within a cartridge chamber 5 of the starting pipe 2.
  • the cartridge chamber 5 is separated from the guided missile space 3.
  • the cartridge chamber 5 has an opening, so that the cartridge chamber 5 is opened to an environment of the starting pipe 2 out.
  • the maneuvering cartridge 6 is advantageously arranged fixedly within the cartridge chamber 5, so that removal of the maneuvering cartridge 6 by a user of the guided missile launching system 1 is not possible.
  • the handle 7 Only by inserting the handle 7 in the launch tube 2 of the maneuver cartridge chamber 5 is connected to the firing pin member 9.
  • the handle 7 has a gas channel 12.
  • the gas channel 12 connects the cartridge chamber 5 with the missile space 3 only when the handle is mounted on the launch tube 2. If the handle 7 is mounted on the starting pipe 2, then the maneuvering cartridge 6 can be ignited in order to generate an overpressure within the gas channel 12. This overpressure within the gas channel 12 finally leads to an acceleration of the firing pin element 9.
  • a conventional striker system 8 is present.
  • a striker system 8 may for example be installed in handguns.
  • the firing pin element 8 is completely integrated within the grip piece 7, so that the firing pin system 8 can be separated from the launch tube 2 together with the grip piece 7. In this way, the product safety is substantially increased, since an unintentional ignition of the maneuver cartridge 6 is prevented. Only by mounting the handle 7 on the Starting pipe 2, the firing pin system 8 is aligned axially to the maneuver cartridge 6 to allow ignition of the maneuver cartridge 6. At the same time established by the insertion of the handle 7 of the gas channel 12 between the cartridge chamber 5 and firing pin member 9 so that an ignition of the maneuver cartridge 6 leads to an acceleration of the firing pin member 9.
  • FIG. 3 a detail view of the guided missile launch system 1 is shown.
  • the guided missile launch system 1 is shown such that the grip 7 is mounted on the launch tube 2.
  • the firing pin element 9 engages in the ignition opening 10 of the guided missile 4.
  • This ignition opening 10 is aligned axially with an opening within the starting pipe 2, so that the firing pin element 9 is inserted in alignment both in the opening of the starting pipe 2 and in the ignition opening 10 of the guided missile 4.
  • the firing pin element 9 In order to prevent the firing pin element 9 from being displaced unintentionally out of its position, the firing pin element 9 has a collar 11 which rests against the launch tube 2 outside the guided-body space 3. About a locking ring 14 of the collar 11 is fixed. Thus, a movement of the firing pin member 9 is prevented.
  • the firing pin member 9 therefore serves as a Verrieglung for the missile 4, since the at least partially engaging the firing pin member 9 in the ignition opening 10 prevents displacement of the missile 4 within the missile space 3 of the launch tube 2. This locking can be achieved only by igniting the maneuver cartridge 6, since this ignition leads to a displacement of the firing pin member 9, whereby the firing pin member 9 is disposed completely within the ignition opening 10.
  • the collar 11 is formed as a tear-off. If the gas pressure inside the gas channel 12 is increased by igniting the maneuver cartridge 6, this leads to a tearing off of the collar 11, as a result of which the firing pin element 9 becomes displaceable. Due to the pressure within the gas channel 12, therefore, an acceleration of the firing pin element 9 takes place in the ignition opening 10 of the guided missile 4 into it. This case is in FIG. 4 shown.
  • FIG. 4 the firing pin system 8 was triggered, whereby the maneuver cartridge 6 was ignited. This is analogous to the firing of a handgun instead.
  • the maneuver cartridge 6 By igniting the maneuver cartridge 6, an overpressure within the gas channel 12 is generated. This overpressure acts on the firing pin element 9. As soon as the overpressure reaches a predefined pressure, the collar 11 of the firing pin element 9 fails FIG. 5 shown.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (8)

  1. Système de démarrage pour missile guidé (1), comprenant un tube de démarrage (2) comportant une chambre de missile guidé (3) pour recevoir un missile guidé (4) et comportant une chambre de munition (5) pour recevoir une munition de manoeuvre (6), et une poignée (7) pouvant être montée sur le tube de démarrage (2) et être séparée du tube de démarrage (2) avec un système de percuteur (8) pour allumer la munition de manoeuvre (6), dans lequel le tube de démarrage (2) présente une ouverture dans laquelle un élément de percuteur (9) est disposé, dans lequel l'élément de percuteur (9) fait saillie dans la chambre de missile guidé (3), de telle sorte qu'avec l'élément de percuteur (9) il est possible de venir en prise dans une ouverture d'allumage (10) du missile guidé (4), dans lequel soit la poignée (7) présente un canal gazeux (12) qui relie la chambre de munition de manoeuvre (5) à l'élément de percuteur (9) lorsque la poignée (7) est montée sur le tube de démarrage (2), soit un élément supplémentaire est prévu, qui présente un canal gazeux (12) qui relie la chambre de munition de manoeuvre (5) à l'élément de percuteur (9) lorsque la poignée (7) est montée sur le tube de démarrage (2) et l'élément supplémentaire est inséré dans le tube de démarrage (2) ou la poignée (7).
  2. Système de démarrage pour missile guidé (1) selon la revendication 1, caractérisé en ce que l'élément de percuteur (9) présente une collerette (11) qui permet de fixer l'élément de percuteur (9) dans le tube de démarrage (2).
  3. Système de démarrage pour missile guidé (1) selon la revendication 2, caractérisé en ce que la collerette (11) est réalisée sous la forme d'un élément arrachable.
  4. Système de démarrage pour missile guidé (1) selon une des revendications 1 à 3, caractérisé en ce que, avec l'élément de percuteur (9), le système de démarrage (4) est verrouillable dans le tube de démarrage (2).
  5. Système de démarrage pour missile guidé (1) selon une des revendications précédentes, caractérisé en ce que le tube de démarrage (2) présente un élément de verrouillage qui permet de verrouiller le missile guidé (4) dans la chambre de missile guidé (3).
  6. Système de démarrage pour missile guidé (1) selon une des revendications précédentes, caractérisé en ce que, dans la chambre de munition (5), une munition de manoeuvre (6) est solidairement installée, de telle sorte que la munition de manoeuvre (6) ne peut pas être extraite par un utilisateur.
  7. Missile guidé (4) destiné à être utilisé dans un système de démarrage pour missile guidé (1) selon une des revendications précédentes, caractérisé en ce que le missile guidé (4) présente une ouverture d'allumage (10) dans laquelle un élément de percuteur (9) du système de démarrage pour missile guidé (1) peut être introduit pour fixer le missile guidé (4) dans un tube de démarrage (2) du système de démarrage pour missile guidé (1).
  8. Missile guidé (4) selon la revendication 7, caractérisé en ce que les ouvertures d'allumage (10) conduisent à une batterie thermique (13) du missile guidé (4) de telle sorte que l'élément de percuteur (9) est percutable sur une amorce en enclume (15) de la batterie thermique (13).
EP16169297.5A 2015-05-12 2016-05-12 Système de démarrage pour un missile guide et missile guide pour un tel système de démarrage Active EP3093609B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL16169297T PL3093609T3 (pl) 2015-05-12 2016-05-12 System startowy pocisku naprowadzanego oraz pocisk naprowadzany dla takiego systemu startowego

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015005954 2015-05-12
DE102015009823.3A DE102015009823B4 (de) 2015-05-12 2015-07-28 Startsystem für einen Lenkflugkörper sowie Lenkflugkörper für ein derartiges Startsystem

Publications (2)

Publication Number Publication Date
EP3093609A1 EP3093609A1 (fr) 2016-11-16
EP3093609B1 true EP3093609B1 (fr) 2018-09-26

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Application Number Title Priority Date Filing Date
EP16169297.5A Active EP3093609B1 (fr) 2015-05-12 2016-05-12 Système de démarrage pour un missile guide et missile guide pour un tel système de démarrage

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EP (1) EP3093609B1 (fr)
PL (1) PL3093609T3 (fr)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1311021A (en) * 1918-05-25 1919-07-22 Lawrence Y Spear Fixed ammunition for non-recoil guns.
FR1206603A (fr) * 1949-06-14 1960-02-10 Tech De Rech S Ind & Mecanique Matériel toutes missions pour lancement de projectiles auto-propulsés
DE1107561B (de) * 1959-11-12 1961-05-25 Diehl Fa Vorrichtung zum Zuenden einer Geschosstreibladung
DE3130963C2 (de) * 1981-08-05 1986-02-06 Heckler & Koch Gmbh, 7238 Oberndorf Abzugsvorrichtung für eine Panzerfaust
DE8508837U1 (de) * 1985-03-25 1985-07-04 Nico-Pyrotechnik Hanns-Jürgen Diederichs GmbH & Co KG, 2077 Trittau Panzerabwehrwaffe
DE3841568A1 (de) * 1988-12-09 1990-06-13 Nico Pyrotechnik Anzuendvorrichtung, insbesondere fuer eine treibladung einer rueckstossfreien panzerabwehrwaffe

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Publication number Publication date
PL3093609T3 (pl) 2019-03-29
EP3093609A1 (fr) 2016-11-16

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