EP3910280B1 - Vorrichtung zur erkennung des fehlens einer mechanischen barriere für einen flugkörper und flugkörper mit einer solchen vorrichtung - Google Patents

Vorrichtung zur erkennung des fehlens einer mechanischen barriere für einen flugkörper und flugkörper mit einer solchen vorrichtung Download PDF

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Publication number
EP3910280B1
EP3910280B1 EP21165132.8A EP21165132A EP3910280B1 EP 3910280 B1 EP3910280 B1 EP 3910280B1 EP 21165132 A EP21165132 A EP 21165132A EP 3910280 B1 EP3910280 B1 EP 3910280B1
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EP
European Patent Office
Prior art keywords
missile
rod
cam
mechanical barrier
launch tube
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EP21165132.8A
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English (en)
French (fr)
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EP3910280A1 (de
Inventor
Edouard Martin
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MBDA France SAS
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MBDA France SAS
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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
    • F42C15/34—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by a blocking-member in the pyrotechnic or explosive train between primer and main charge
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • 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
    • 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
    • F42C15/24—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means

Definitions

  • the present invention relates to a device for detecting the absence of a mechanical barrier for a missile and a missile comprising such a device.
  • the missiles are equipped with at least one DSA safety and armament device allowing the firing of the warhead of the missile.
  • these safety and arming devices are provided with a device for detecting the missile exiting its launch tube.
  • These launch tube exit detection devices comprise a detection member, generally a rod (or a finger), intended to come into contact with the launch tube and more precisely with the inner surface of the launch tube.
  • the rod which is movable in translation in a direction radial relative to the missile, can assume different positions. Thus, when the rod is in contact with the launch tube, it assumes a given position and when it is no longer in contact with the launch tube, it assumes another given position.
  • the object of the present invention is to remedy the aforementioned drawbacks, by proposing a device for detecting the exit of a missile from its launch tube, and more generally a device for detecting the absence of a mechanical barrier for a missile, said device comprising at least a rod constrained by a first elastic element and provided with a free end capable of coming into contact with the mechanical barrier
  • the device for detecting the absence of a mechanical barrier comprises at least one activatable detection element, configured to be activated when the rod assumes the terminal entry position.
  • the detection element is activated by the rod or by the cam, when said rod assumes the terminal input position.
  • the device for detecting the absence of a mechanical barrier comprises an additional cam, called an auxiliary cam, integral with said cam and the detection element is configured to be activated by said auxiliary cam.
  • the device for detecting the absence of a mechanical barrier comprises at least one elastically constrained priming finger as well as an opening made on a peripheral part of the auxiliary cam, said priming finger is part of the sensing element and said trigger finger and said aperture are configured and positioned such that the trigger finger lodges in the aperture when the rod assumes the end-in position.
  • the mechanical barrier detection device comprises at least one sealing element arranged at the free end of the rod as well as a base comprising a bore capable of receiving said sealing element when said rod assumes the terminal entry position.
  • This configuration makes it possible to make the missile impermeable to a large majority of the impurities that it is likely to encounter during its trajectory.
  • the present invention also relates to a missile.
  • said missile comprises at least one device for detecting the absence of a mechanical barrier such as that described above.
  • the missile comprises a launch tube exit detection device and an initialization chain for the warhead of said missile, said launch tube exit detection device corresponding to said absence of mechanical barrier described above.
  • the missile comprises an initialization chain for a warhead and a device for detecting the absence of a mechanical barrier comprising at least one elastically constrained priming finger as described above , said priming finger being capable of triggering the initialization chain when it lodges in the opening provided for this purpose of the auxiliary cam.
  • the missile comprises a holding system which comprises at least one launch tube exit detection device as mentioned above and at least one holding element arranged at the free end of the rod of said at least one of said devices, said holding element being capable of coming into contact with the mechanical barrier.
  • the missile comprises a holding system comprising a single holding element and a plurality of devices for detecting the absence of a mechanical barrier, such as the one described above, the end of each of said devices being connected to said holding element.
  • the missile can comprise a plurality of holding systems.
  • the holding element corresponds to a strip.
  • the holding element corresponds to a pad.
  • the missile comprises at least one groove capable of receiving the holding element when the rod of the mechanical barrier absence detection devices take the terminal input position.
  • the missile has a launch tube exit detection device capable of triggering the retraction or deployment of holding or guiding elements, such as strips or pads, so that the various elements do not interfere with the proper functioning of said missile when it leaves the launch tube.
  • the device 1 represented schematically on the figure 1 and making it possible to illustrate the invention, has the objective of detecting the absence of a mechanical barrier 2, which can correspond to any solid surface.
  • This device 1 is intended to be installed on a missile M, and in this case, the mechanical barrier 2 is, preferably, the launch tube 16 of said missile M.
  • missile is understood to mean any self-propelled flying object which can be guided over all or part of its trajectory, by self-guiding or remote-guiding, and capable of carrying at least one warhead, in particular explosive or pyrotechnic. It may in particular be an anti-tank missile, fired from a helicopter or a drone. It can also be a medium-range missile, fired from the ground.
  • the device 1 comprises a support element, called the base 3 which comprises, in particular, usual fixing elements (not shown) configured to fix the said device 1 to the missile M.
  • the base 3 can also be fixed directly on the warhead of the missile M.
  • This base 3 is provided with a bent part 3a comprising at least one opening capable of receiving at least one bearing element 4. The latter is intended to receive at least one rod 5, said rod 5 being able to slide in said element of level 4.
  • the rod 5 has a longitudinal axis, denoted X
  • the missile M has a longitudinal axis, denoted Y ( figures 6 and 7 ).
  • Device 1 is positioned on missile M such that the X axis is oriented radially to the Y axis.
  • the device 1 also comprises an elastic element 7 intended to elastically constrain the rod 5 with respect to the base 3.
  • the rod 5 comprises a collar 6 at its end 5b.
  • the bent part 3a is provided with a flat surface parallel to the collar 6, capable of receiving the elastic element 7 in support.
  • the elastic element 7 is arranged around the rod 5 so as to come to bear on the collar 6 on the one hand and on the flat surface of the bent part 3a on the other hand. The elastic element 7 is thus compressed between the collar 6 and the bent part 3a. Consequently, the rod 5 is elastically constrained in translation along the axis X, the elastic element 7 exerting on said rod 5 a force in the direction illustrated by the arrow I.
  • the device 1 also comprises at least one cam 8, pivotally linked to the base 3.
  • This cam 8 is constrained in torsion with respect to the base 3 by an elastic element 9, shown in dotted lines on the figure 1 , 2 and 3 .
  • the elastic element 9 is configured to exert a torque on the cam 8, oriented in the direction indicated by an arrow R on the figure 2 .
  • cam 8 has a free end 8a able to come into contact with end 5b of rod 5.
  • the dimensions and shape of cam 8 are such that surface 8a of said cam 8 comes into contact with the surface of the end 5b of the rod 5 when the cam 8 pivots on its axis in the direction of the arrow R.
  • the cam 8 is therefore configured to exert a force on the rod 5 in the direction illustrated by the arrow E.
  • the base 3 also comprises a projecting element forming an abutment 10 ( figure 1 and 3 ).
  • the cam 8 is provided with a projecting element 8b capable of coming into contact with the stop 10 when the cam 8 pivots around its axis in the direction indicated by the arrow R.
  • the shape 8b is configured on the cam 8 so that said cam 8 is locked in rotation by stop 10 when it assumes a position described below.
  • the device 1 is intended to detect the exit of the missile M from the launch tube 16.
  • the method of detecting the exit of the missile M from the launch tube 16 is implemented in three stages, different elements of the device 1, in particular rod 5 and cam 8, taking a given position for each of these steps.
  • the figure 1 , 2 and 3 illustrate, respectively, the three successive data positions P1, P2 and P3.
  • the missile M is installed in the launch tube 16.
  • the rod 5, pushed by the cam 8, is in contact with the mechanical barrier 2, namely the inner wall 16a of the launch tube 16.
  • the rod 5 is elastically constrained by the elastic element 7 in the direction illustrated by the arrow I, and by the elastic element 9, through the cam 8, in the direction illustrated by the arrow E.
  • the elastic element 9 is configured to exert, via the cam 8, a greater force on the rod 5 than that exerted by the elastic element 7 on the rod 5.
  • the rod 5 is therefore forced to bear against the mechanical barrier 2 and assumes a position stable between cam 8 and mechanical barrier 2.
  • cam 8 Once cam 8 has pushed rod 5 into position P2, said cam 8 continues to pivot until it reaches stop 10. However, cam 8 is configured to release the translation of rod 5 after said cam 8 has pivoted in the direction of arrow R, beyond position P2. The rod 5 no longer being subjected to the force of the cam 8, the elastic element 7 forces said rod 5 to move in the direction illustrated by the arrow I. The rod 5 then penetrates completely into the missile M, and is brought into position P3, called the terminal entry position, illustrated on the picture 3 .
  • the rod 5 does not protrude from the missile M outwards and presents no discomfort. Moreover, a device 1 as described previously does not eject any part during its use, since the rod 5 is retracted into the missile M once the latter has left the launch tube 16.
  • said device 1 is autonomous, since it does not require the use of an energy source such as a power supply or a pyrotechnic device. Only the mechanical energy provided by the elastic elements 7 and 9 is necessary to set in motion the various elements of the device 1 generating the retraction of the rod 5.
  • an energy source such as a power supply or a pyrotechnic device. Only the mechanical energy provided by the elastic elements 7 and 9 is necessary to set in motion the various elements of the device 1 generating the retraction of the rod 5.
  • the device 1 comprises an additional cam, called auxiliary cam 12.
  • This auxiliary cam 12 is integral with the cam 8, for example via an axis, and is therefore capable of pivoting with respect to the base 3 with said cam 8.
  • the device 1 comprises a detection element 26, and a trigger finger 13 of longitudinal axis Z which is part of this detection element 26.
  • the trigger finger 13 is housed in a blind hole 22, said hole 22 being made in the base 3.
  • This hole 22 is formed and located such that the opening 22a (or mouth) of the blind hole 22 is facing a peripheral surface 12a of the auxiliary cam 12.
  • an elastic element 21, for example a compression spring is positioned at the bottom of the hole 22 so as to exert a force on the end of the priming finger 13, in the direction of the bottom from hole 22 towards opening 22a of said hole 22. Priming finger 13 is thus elastically constrained by elastic element 21 against peripheral surface 12a of auxiliary cam 12.
  • the auxiliary cam 12 has an opening 23, for example also a blind hole, on the peripheral surface 12a.
  • This opening 23 is formed and located so that its mouth 23a is opposite the opening 22a so that the opening 23 is able to receive the priming finger 13, when the auxiliary cam 12 pivots in the direction illustrated by the arrow R and takes a given position.
  • This given position corresponds to the situation where the elements of the device 1 take the position P3 when the missile M has left the launch tube 16.
  • the missile M is provided with a warhead 17 and an initialization chain 18 of said warhead 17, represented on the figure 6 .
  • the priming finger 13 is configured to be able to trigger the initialization chain 18 when it slides in the opening 23.
  • the device 1 is able to trigger the initialization chain 18 of a warhead 17 of a missile M in the absence of the mechanical barrier 2.
  • the priming finger 13 has the advantage of allowing great flexibility as regards the positioning of said priming finger 13 with respect to the auxiliary cam 12.
  • the priming finger 13 can take a plurality of angular positions around the axis of rotation of the auxiliary cam 12.
  • the plane of the priming finger 13, defined by the axes X and Z, can also take a plurality of orientations angular relative to the plane orthogonal to the Y axis of the missile M.
  • the shape of the auxiliary cam 12 can be configured so that the peripheral surface 12a is facing the priming finger 13.
  • the auxiliary cam 12 can be made with a truncated cone shape and thus allow the priming finger 13 to be oriented at a given angle with respect to the plane orthogonal to the Y axis.
  • the detection element 26 comprises a detection means 11 represented very schematically on the figure 5 .
  • the detection means 11 can be activated and is configured to emit a signal S when the elements of the device 1 take the position P3.
  • the signal S can match, in particular, to a mechanical control capable of triggering an initialization chain of a warhead, or the deflection of elements of the missile M, such as usual wing elements or deflectors (or even the closing of a circuit electric due to the rotation of the cam 8 or the translation of the finger 5).
  • the detection element 26 is configured to be activated by the rod 5 when the latter assumes the position P3.
  • the rod 5 is, for example, provided with a projecting part or with an added part (not represented on the figure 5 ) capable of activating the detection element 26.
  • the detection element 26 is configured to be activated by the cam 8 when the rod 5 takes the position P3.
  • the cam 8 is, for example, provided with a projecting part or with an opening located on its periphery (such as, in particular, the opening 23 represented on the figures 4A and 4B ) capable of activating the detection element 26.
  • the detection element 26 is configured to be activated by the auxiliary cam 12 when the latter takes the position P3.
  • the auxiliary cam 12 is, for example, provided with a projecting part or with an opening located on its periphery, such as the opening 23 represented on the figures 4A and 4B , capable of activating the detection element 26.
  • the mechanical barrier 2 can, for example, transmit vibrations or jolts to the rod 5 when the missile M is mounted in the launch tube 16. These movements are only transmitted to the cam 8 (and if necessary to the auxiliary cam 12), but not to the detection element 26 (such as the priming finger 13). This has the effect of avoiding in particular preventing deterioration of the detection element 26, or false detection on the part of of the latter and therefore (in the extreme case) an untimely triggering of the warhead 17 of the missile M.
  • the bent part 3a of the base 3 has a bore 14 on its face oriented in the direction illustrated by the arrow E.
  • the rod 5 is provided, at its free end 5a, with a sealing element 15 , for example an O-ring.
  • Bore 14 is configured in such a way as to be able to accommodate sealing element 15.
  • sealing element 15 is housed in bore 14.
  • the sealing element 15 thus prevents a liquid or dust from entering the missile M.
  • This embodiment also makes it possible to dampen any possible rebound of the rod 5, during retraction, and also to limit the vibrations of said rod 5 when it is in position P3.
  • Device 1 is therefore intended to be mounted on a missile M.
  • device 1 is preferably a device for detecting the exit of missile 1 from its launch tube 16. It It can also be a device for detecting the absence of another element, in particular of support, for example a rail intended to receive or carry the missile M while waiting for it to be fired.
  • the figures 6 and 7 illustrate two examples of a weapon system 25.
  • the weapon system 25 comprises the missile M provided with at least one device 1, the launch tube 16, and all usual means of propulsion and launch of such a missile M, said usual means not being represented on the figure 6 and 7 .
  • the weapon system 25 therefore comprises, in particular, the missile M provided with a device 1, as well as the warhead 17 and the initialization chain 18 capable of triggering said warhead 17.
  • the priming finger 13 (not shown in the figure 6 ) forms part of the detection element 26.
  • the initialization chain 18 of the warhead 17 of the missile M is activated by the priming finger 13 (which functions as described above with reference to the figures 4A and 4B ).
  • the weapon system 25 comprises, in particular, a missile M provided with a holding system 24.
  • This holding system 24 comprises at least one device 1, and at least one holding element 19 arranged at the end 5a of the rod 5 and able to come into contact with the inner wall 16a of the launch tube 16.
  • the retaining element 19 is pressed against the inner wall 16a of the launch tube 16. As soon as the missile M is propelled out of the launch tube 16, various elements of the device 1 take position P3. The rod 5 then penetrates completely into the missile M, carrying with it the holding element 19.
  • the holding element 19 corresponds to a strip.
  • strip is meant a longitudinal element capable of coming into contact with the inner wall 16a of the launch tube 16 in order to perform a functional action for the missile M, such as a guiding action during the propulsion of said missile M
  • the inner wall 16a of the launch tube 16 can be provided with the usual support or guide elements such as grooves, tabs, or guide fingers, capable of receiving the ruler to form a system of guidance.
  • the holding system 24 comprises a plurality of holding elements 19 distributed for example around the outer face of the missile M.
  • the holding system 24 can guide the missile M out of the launch tube 16 during the propulsion phase, and the holding element(s) 19 are retracted into the missile M after said missile M has left said launch tube 16.
  • the missile M is provided, on its peripheral surface, with a groove 20 capable of receiving said holding element 19 so that the latter does not protrude from said missile M in the retracted position.
  • the missile M therefore has a holding system 24 that is retractable in the throat 20 when said missile M has left the launch tube 16, and does not include any protruding element likely to represent a hindrance to the proper functioning of said missile M.
  • the holding element corresponds to a pad.
  • pad is meant one or more elements of variable shapes and sizes, generally made of elastic material, intended, in particular, to hold the missile M or part of the missile M in place in a damped manner, and thus to protect it from shocks.
  • Such a holding system corresponds to a damping system and is retractable, in the same way as for the previous embodiment.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Geophysics And Detection Of Objects (AREA)

Claims (15)

  1. Vorrichtung zur Erkennung des Fehlens einer mechanischen Barriere für einen Flugkörper, wobei die Vorrichtung (1) mindestens eine Stange (5) aufweist, die durch ein erstes elastisches Element (7) belastet wird und mit einem sogenannten freien Ende (5a) versehen ist, das in Lage ist, mit einer mechanischen Barriere (2) in Kontakt zu kommen,
    dadurch gekennzeichnet, dass sie zusätzlich mindestens einen Nocken (8) aufweist, der durch ein zweites elastisches Element (9) belastet wird, wobei die Stange (5) und der Nocken (8) derart konfiguriert sind, dass die Stange (5) die eine oder die beiden der folgenden Positionen einnehmen kann:
    - eine sogenannte anfängliche Eingangsposition (P1), in der die Stange (5) in einer stabilen Position zwischen einerseits dem Nocken (8) und andererseits der mechanischen Barriere (2) gehalten wird;
    - eine sogenannte Ausgangsposition (P2), in welche die Stange (5) unter der Wirkung des Nockens (8) durch eine Verschiebung in der Richtung (E) des freien Endes (5a) bei Abwesenheit der mechanischen Barriere (2) gebracht wird; und
    - eine sogenannte endgültige Eingangsposition (P3), in welche die Stange (5) unter der Wirkung des ersten elastischen Elements (7) nach Freigabe der Verschiebung der Stange (5) durch den Nocken (8) gebracht wird.
  2. Vorrichtung nach Anspruch 1,
    dadurch gekennzeichnet, dass sie mindestens ein aktivierbares Erkennungselement (26) aufweist, das konfiguriert ist, um aktiviert zu werden, wenn die Stange (5) die endgültige Eingangsposition (P3) einnimmt.
  3. Vorrichtung nach Anspruch 2,
    dadurch gekennzeichnet, dass das Erkennungselement (26) derart konfiguriert ist, dass es durch eines der folgenden Elemente aktiviert wird:
    - die Stange (5);
    - den Nocken (8).
  4. Vorrichtung nach Anspruch 2,
    dadurch gekennzeichnet, dass er einen zusätzlichen Nocken aufweist, den sogenannten Hilfsnocken (12), der mit dem Nocken (8) fest verbunden ist, und dass das Erkennungselement (26) derart konfiguriert ist, dass es durch den Hilfsnocken (12) aktiviert wird.
  5. Vorrichtung nach Anspruch 4,
    dadurch gekennzeichnet, dass sie mindestens einen elastisch belasteten Zündfinger (13) sowie eine Öffnung (23) aufweist, die an einem Umfangsteil (12a) des Hilfsnockens (12) ausgebildet ist, und dass der Zündfinger (13) Teil des Erkennungselements (26) ist und dass der Zündfinger (13) und die Öffnung (23) derart konfiguriert und positioniert sind, dass der Zündfinger (13) in der Öffnung (23) aufgenommen wird, wenn die Stange (5) die endgültige Eingangsposition (P3) einnimmt.
  6. Vorrichtung nach einem der vorstehenden Ansprüche,
    dadurch gekennzeichnet, dass sie mindestens ein Dichtungselement (15) aufweist, das am freien Ende (5a) der Stange (5) angeordnet ist, sowie eine Basis (3), die eine Bohrung (14) aufweist, die in der Lage ist, das Dichtungselement (15) zu empfangen, wenn die Stange (5) die endgültige Eingangsposition (P3) einnimmt.
  7. Flugkörper,
    dadurch gekennzeichnet, dass er mindestens eine Vorrichtung (1) nach einem der Ansprüche 1 bis 6 aufweist.
  8. Flugkörper nach Anspruch 7, wobei der Flugkörper (M) eine Vorrichtung (1) zur Erkennung des Austritts aus dem Abschussrohr und eine Kette (18) zur Initialisierung einer militärischen Ladung (17) umfasst,
    dadurch gekennzeichnet, dass die Vorrichtung zur Erkennung des Austritts eines Abschussrohrs der Vorrichtung (1) nach einem der Ansprüche 1 bis 6 entspricht.
  9. Flugkörper nach Anspruch 8, der eine Vorrichtung (1) nach Anspruch 5 aufweist,
    dadurch gekennzeichnet, dass der Zündfinger (13) in der Lage ist, die Initialisierungskette (18) der militärischen Ladung (17) des Flugkörpers (M) auszulösen, wenn er in der Öffnung (23) des Hilfsnockens (12) aufgenommen wird.
  10. Flugkörper nach einem der Ansprüche 7 bis 9, der mindestens ein Haltesystem (24) aufweist,
    dadurch gekennzeichnet, dass das Haltesystem (24) mindestens eine Vorrichtung (1) nach einem der Ansprüche 1 bis 6 und mindestens ein Halteelement (19) aufweist, das am freien Ende (5a) der Stange (5) der mindestens einen Vorrichtung (1) angeordnet ist, wobei das Halteelement (19) in der Lage ist, mit der mechanischen Barriere (2) in Kontakt zu kommen.
  11. Flugkörper nach Anspruch 10,
    dadurch gekennzeichnet, dass das Haltesystem (24) ein einzelnes Halteelement (19) und eine Vielzahl von Vorrichtungen (1) nach einem der Ansprüche 1 bis 6 aufweist, wobei das freie Ende (5a) der Stange (5) jeder der Vorrichtungen (1) mit dem Halteelement (19) verbunden ist.
  12. Flugkörper nach einem der Ansprüche 10 und 11,
    dadurch gekennzeichnet, dass er eine Vielzahl von Haltesystemen (24) aufweist.
  13. Flugkörper nach einem der Ansprüche 10 bis 12,
    dadurch gekennzeichnet, dass er mindestens eine Nut (20) aufweist, die in der Lage ist, das Halteelement (19) zu empfangen, wenn die Stange (5) der Vorrichtung(en) (1) zur Erkennung des Fehlens einer mechanischen Barriere die endgültige Eingangsposition (P3) einnimmt.
  14. Flugkörper nach einem der Ansprüche 10 bis 13,
    dadurch gekennzeichnet, dass das Halteelement (19) einer Leiste entspricht.
  15. Flugkörper nach einem der Ansprüche 10 bis 13,
    dadurch gekennzeichnet, dass das Halteelement einem Füllstück entspricht.
EP21165132.8A 2020-05-12 2021-03-26 Vorrichtung zur erkennung des fehlens einer mechanischen barriere für einen flugkörper und flugkörper mit einer solchen vorrichtung Active EP3910280B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR2004527A FR3110228B1 (fr) 2020-05-12 2020-05-12 DIspositif de détection d'absence de barrière mécanique pour missile et missile comportant un tel dispositif.

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EP3910280A1 EP3910280A1 (de) 2021-11-17
EP3910280B1 true EP3910280B1 (de) 2022-07-27

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US (1) US11940260B2 (de)
EP (1) EP3910280B1 (de)
ES (1) ES2928201T3 (de)
FR (1) FR3110228B1 (de)
IL (1) IL297956A (de)
PL (1) PL3910280T3 (de)
WO (1) WO2021229158A1 (de)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2704033A (en) * 1951-10-09 1955-03-15 Casper J Koeper Rocket fuze
US3894491A (en) * 1974-03-13 1975-07-15 Us Navy Automatic porting mechanism
US5166458A (en) * 1991-01-11 1992-11-24 Daewoo Precision Ind., Ltd. Firing mechanism for fast shooting pistol
FR2737001B1 (fr) * 1995-07-20 1997-08-29 Giat Ind Sa Dispositif de stabilisation pour arme a feu individuelle
KR100241868B1 (ko) * 1996-01-31 2000-03-02 유무성 포탄 이송 장치
KR100753488B1 (ko) * 2006-06-09 2007-08-31 국방과학연구소 미사일 발사가이드 장치

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WO2021229158A1 (fr) 2021-11-18
FR3110228A1 (fr) 2021-11-19
FR3110228B1 (fr) 2022-05-13
PL3910280T3 (pl) 2022-11-21
US20230184526A1 (en) 2023-06-15
IL297956A (en) 2023-01-01
EP3910280A1 (de) 2021-11-17
ES2928201T3 (es) 2022-11-16
US11940260B2 (en) 2024-03-26

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