EP3910280A1 - 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
EP3910280A1
EP3910280A1 EP21165132.8A EP21165132A EP3910280A1 EP 3910280 A1 EP3910280 A1 EP 3910280A1 EP 21165132 A EP21165132 A EP 21165132A EP 3910280 A1 EP3910280 A1 EP 3910280A1
Authority
EP
European Patent Office
Prior art keywords
rod
missile
cam
mechanical barrier
finger
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
EP21165132.8A
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English (en)
French (fr)
Other versions
EP3910280B1 (de
Inventor
Edouard Martin
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 France SAS
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MBDA France SAS
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Filing date
Publication date
Application filed by MBDA France SAS filed Critical MBDA France SAS
Publication of EP3910280A1 publication Critical patent/EP3910280A1/de
Application granted granted Critical
Publication of EP3910280B1 publication Critical patent/EP3910280B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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 security and armament device allowing the firing of the military charge of the missile.
  • these safety and armament devices are provided with a device for detecting the exit of the missile from its launch tube.
  • These launch tube exit detection devices include 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 radial direction relative to the missile, can take different positions. Thus, when the rod is in contact with the launch tube, it takes a given position and when it is no longer in contact with the launch tube it takes 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 input 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 priming finger and said opening are configured and positioned so that the priming finger engages in the opening when the rod assumes the terminal entry 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 suitable for receiving said sealing element. when said rod assumes the terminal entry position.
  • This configuration makes it possible to seal the missile against 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 a warhead initialization chain of said missile, said launch tube exit detection device corresponding to said launch tube detection device. absence of mechanical barrier described above.
  • the missile comprises an initialization chain for a military charge and a device for detecting the absence of a mechanical barrier comprising at least one priming finger elastically constrained as described above. , said priming finger being able to trigger the initialization chain when it is housed 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 retaining element being able to come 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 that described above, the end of each of said devices being linked to said retaining element.
  • the missile can include a plurality of holding systems.
  • the holding element corresponds to a strip.
  • the retaining element corresponds to a pad.
  • the missile comprises at least one groove capable of receiving the retaining element when the rod of the devices for detecting the absence of a mechanical barrier take the terminal entry position.
  • the missile has a launch tube exit detection device capable of triggering the reentry or deployment of support or guide elements, such as strips or bearings, so that the various elements do not interfere with the proper functioning of said missile when it leaves the launch tube.
  • the device 1 shown schematically on the figure 1 and making it possible to illustrate the invention, aims to detect 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 autoguiding or remote guiding, and capable of transporting at least one military charge, 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 said device 1 to the missile M.
  • the base 3 can also be fixed directly to the warhead of the missile M.
  • This base 3 is provided with a bent part 3a comprising at least one opening capable of accommodating 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. bearing 4.
  • the rod 5 has a longitudinal axis, denoted X
  • the missile M has a longitudinal axis, denoted Y ( figures 6 and 7 ).
  • the device 1 is positioned on the 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 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 X axis, the elastic element 7 exerting a force on said rod 5 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 figures. figures 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 .
  • the cam 8 has a free end 8a capable of coming into contact with the end 5b of the rod 5.
  • the dimensions and the shape of the cam 8 are such that the 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 a stop 10 ( figures 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 about its axis in the direction indicated by the arrow R.
  • the form 8b is configured on the cam 8 so that said cam 8 is locked in rotation by stopper 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 for detecting the exit of the missile M from the launch tube 16 is implemented in three stages, different elements of the process. device 1, in particular the rod 5 and the cam 8, taking a given position for each of these steps.
  • the figures 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 takes a position stable between cam 8 and mechanical barrier 2.
  • the cam 8 Once the cam 8 has pushed the rod 5 to position P2, said cam 8 continues to pivot until it reaches the stop 10. However, the cam 8 is configured to release the translation of the rod 5 after said cam 8 has rotated 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 input position, illustrated on figure 3 .
  • the rod 5 does not protrude from the missile M outwards and does not present any hindrance.
  • a device 1 as described previously does not eject any part during its use, since the rod 5 has entered 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 an electric power supply or a pyrotechnic device. Only the mechanical energy supplied by the elastic elements 7 and 9 is necessary for the setting in motion of the various elements of the device 1 generating the retraction of the rod 5.
  • an energy source such as an electric power supply or a pyrotechnic device. Only the mechanical energy supplied by the elastic elements 7 and 9 is necessary for the setting in motion of the various elements of the device 1 generating the retraction of the rod 5.
  • the device 1 comprises an additional cam, called the 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 priming finger 13 of longitudinal axis Z which forms part of this detection element 26.
  • the priming 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 so that the opening 22a (or mouth) of the blind hole 22 faces 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 to the opening 22a of said hole 22.
  • the priming finger 13 is thus elastically constrained by the elastic element 21 against the peripheral surface 12a of the 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 in front of 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, shown on the figure. 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 military charge 17 of a missile M in the absence of the mechanical barrier 2.
  • the production of the priming finger 13, as described above, has the advantage of allowing great flexibility with regard to the positioning of said priming finger 13 relative 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 X and Z axes, can also take a plurality of orientations angular with respect 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 produced in the shape of a truncated cone and thus allow the starter 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 shown very schematically on the figure. 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 correspond, in particular, to a mechanical control capable of triggering an initialization chain of a military charge, or the deflection of elements of the missile M, such as usual airfoil elements or deflectors (or even the closing of a circuit electric due to the rotation of the cam 8 or to the translation of the finger 5).
  • the detection element 26 is configured to be activated by the rod 5 when the latter takes the position P3.
  • the rod 5 is, for example, provided with a projecting part or with an insert (not shown in 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 assumes 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 shown in 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 situated on its periphery, such as the opening 23 shown in the figures. 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 transmitted only to the cam 8 (and where appropriate 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 a deterioration of the detection element 26, or a false detection by the part. of the latter and therefore (in the extreme case) an untimely triggering of the military charge 17 of the missile M.
  • the angled part 3a of the base 3 comprises 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.
  • the bore 14 is configured so as to be able to accommodate the sealing element 15.
  • the sealing element 15 is housed in the bore 14.
  • the sealing element 15 thus prevents a liquid or dust from entering the missile M.
  • This embodiment also makes it possible to damp any possible rebound of the rod 5, during the retraction, and also of limit the vibrations of said rod 5 when it is in position P3.
  • the device 1, as described above, is therefore intended to be mounted on a missile M.
  • the device 1 is, preferably, a device for detecting the exit of missile 1 from its launch tube 16. It may also be a device for detecting the absence of another element, in particular a support, for example a rail intended to receive or carry the missile M while awaiting its firing.
  • 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 launching tube 16, and all usual means of propulsion and launching of such missile M, said usual means not being shown on the figure 6 and 7 .
  • FIGS. 6 and 7 respectively represent two particular embodiments of a weapon system 25 provided with the missile M
  • the weapon system 25 therefore comprises, in particular, the missile M provided with a device 1, as well as the military charge 17 and the initialization chain 18 capable of triggering said military charge 17.
  • the priming finger 13 (not shown in the figure figure 6 ) is 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 operates as described above with reference to the figures 4A and 4B ).
  • the weapon system 25 comprises, in particular, a missile M provided with a retaining system 24.
  • This retaining system 24 comprises at least one device 1, and at least one retaining 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, bringing with it the retaining element 19.
  • the retaining element 19 corresponds to a strip.
  • the term “strip” is understood to mean a longitudinal element capable of coming into contact with the inner wall 16a of the launch tube 16 for the purpose of performing 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 launching tube 16 may be provided with usual support or guide elements such as grooves, tongues, or guide fingers, capable of accommodating the strip to form a system of guidance.
  • the retaining system 24 comprises a plurality of retaining elements 19 distributed for example around the outer face of the missile M.
  • the retaining system 24 can guide the missile M out of the launch tube 16 during the propulsion phase, and the holding element or elements 19 are retracted into the missile M after the exit of said missile M from 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 retractable retaining system 24 in the groove 20 when said missile M has come out of the launch tube 16, and not comprising any protruding element capable of hindering the proper functioning of said M missile.
  • the retaining element corresponds to a pad.
  • the term “pad” is understood to mean one or more elements of variable shapes and sizes, generally made of elastic material, intended, in particular, to hold the missile M or a part of the missile M in place in a damped manner, and thus to protect it from shocks.
  • Such a support 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)
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.

Publications (2)

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

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP21165132.8A Active EP3910280B1 (de) 2020-05-12 2021-03-26 Vorrichtung zur erkennung des fehlens einer mechanischen barriere für einen flugkörper und flugkörper mit einer solchen vorrichtung

Country Status (7)

Country Link
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)

Citations (3)

* 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
US20070283800A1 (en) * 2006-06-09 2007-12-13 Tae-Hak Park Missile launch and guidance apparatus

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Patent Citations (3)

* 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
US20070283800A1 (en) * 2006-06-09 2007-12-13 Tae-Hak Park Missile launch and guidance apparatus

Also Published As

Publication number Publication date
ES2928201T3 (es) 2022-11-16
FR3110228B1 (fr) 2022-05-13
PL3910280T3 (pl) 2022-11-21
FR3110228A1 (fr) 2021-11-19
IL297956A (en) 2023-01-01
US11940260B2 (en) 2024-03-26
US20230184526A1 (en) 2023-06-15
EP3910280B1 (de) 2022-07-27
WO2021229158A1 (fr) 2021-11-18

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