EP3693691A1 - Ensemble de lancement de missile et lanceur de missile comprenant ledit ensemble de lancement - Google Patents

Ensemble de lancement de missile et lanceur de missile comprenant ledit ensemble de lancement Download PDF

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Publication number
EP3693691A1
EP3693691A1 EP20153069.8A EP20153069A EP3693691A1 EP 3693691 A1 EP3693691 A1 EP 3693691A1 EP 20153069 A EP20153069 A EP 20153069A EP 3693691 A1 EP3693691 A1 EP 3693691A1
Authority
EP
European Patent Office
Prior art keywords
launching
missile
assembly
support base
container
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
EP20153069.8A
Other languages
German (de)
English (en)
Other versions
EP3693691B1 (fr
Inventor
Teodoro Andrea Dragani
Massimo CIANCHETTINI
Fabio IACOVACCI
Giovanni ASTE
Mauro Piccolo
Matteo Guidi
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 Italia SpA
Original Assignee
MBDA Italia SpA
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Filing date
Publication date
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Priority to PL20153069T priority Critical patent/PL3693691T3/pl
Publication of EP3693691A1 publication Critical patent/EP3693691A1/fr
Application granted granted Critical
Publication of EP3693691B1 publication Critical patent/EP3693691B1/fr
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Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A23/00—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
    • F41A23/34—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles
    • F41A23/42—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles for rocket throwers
    • 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
    • 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

Definitions

  • the present invention refers to the technical field of missile or projectile launching systems and relates in particular to a missile launching assembly and a missile launcher comprising said launching assembly.
  • Missile launching assemblies comprising a plurality of launching containers, or canisters, wherein each launching container is adapted and configured to contain a respective missile for housing, transport and launching purposes, are already known.
  • a multiple launching assembly i.e. having a plurality of canisters, is for example known from the US patent 7,207,254 and is in particular represented in Figure 2 of that patent and indicated with the Anglo-Saxon expression "vertical launch pack".
  • This vertical launch pack comprises a plurality of canisters secured to each other and each housing a respective missile.
  • a further multiple launching assembly is disclosed by the European patent application EP1710530 A2 .
  • a multiple launching assembly a plurality of canisters are stacked together and secured mechanically to form launch batteries.
  • the launch batteries are in turn secured to a support base having an end portion hinged to a rear portion of a frame of a self-propelled transport vehicle to rotate along an axis orthogonal to a longitudinal axis of the vehicle, between a lowered transport position and a raised launch position under the thrust and control of a linear actuator.
  • the object of the present description is to provide a missile launching assembly that meets the aforesaid requirement.
  • the missile launcher 1 comprises, or is installed on, a land transport vehicle 5, which in the example is a military truck suitable for the transport and launching of missiles.
  • the missile launcher 1 comprises a missile launching assembly 10 which in Figures 1 and 2 is shown in the transport configuration and which in Figures 3 and 4 is shown in the launching configuration.
  • the missile launcher 1 comprises a mounting frame 2 to which the missile launching assembly 10 is pivotally coupled.
  • the missile launching assembly 10 is pivotally coupled to one end portion of the mounting frame 2 distal from the driver's cab of the transport vehicle 5.
  • the missile launching assembly 10 comprises an orientable support base 11, in particular pivotable, between a transport angular position, shown in Figures 1 and 2 , and a launching angular position, shown in Figures 3 and 4 .
  • at least one controllable actuator 3 may be provided in the missile launcher 1 to orient the support base 11.
  • the aforesaid actuator 3 comprises a linear actuator, for example a hydraulic or hydro-pneumatic actuator, having an end portion pivotally connected, e.g. hinged, to the mounting frame 2 and having an opposite end portion pivotally connected, e.g. hinged, to the missile launching assembly 10 and in particular to the support base 11.
  • the support base 11 is in the transport angular position when the missile launching assembly 10 is in the transport configuration and assumes the launching angular position when the missile launching assembly 10 assumes the launching configuration.
  • the mounting frame 2 of the missile launcher 1 comprises a plurality of support feet 4.
  • these support feet 4 are adapted and configured to assume a retracted position in the transport configuration and an extended configuration in the launching configuration in order to act in the latter configuration as support elements for the mounting frame 2 in order to stabilize the mounting frame 2 in position before launching one or more missiles.
  • Each of the support feet 4 is preferably actuated by a linear actuation system, e.g. a hydraulic actuation system.
  • the support feet 4 allow the mounting frame 2 and the launching assembly 10 to be released from joint use with the transport vehicle 5.
  • the transport vehicle 5 is not provided for in the missile launcher 1 and/or wherein the transport vehicle 5 may be detached from the remaining part of the missile launcher 1, whereby once the missile launcher 1 has been transported to the site, it may rest by means of support feet 4 directly on a supporting surface of a launch field, for example on the ground, without the interposition of the transport vehicle 5, which may thus be used to load, transport and unload on the launch field other launching assemblies, each comprising a launching frame 2 and a launching assembly 10.
  • the support feet 4 are advantageously adjustable to level the mounting frame 2 with respect to the support surface.
  • the missile launcher 1 is preferably a multiple missile launcher, i.e. it is suitable to transport and launch multiple missiles before reloading. In the particular example shown in the figures, without thereby introducing any limitations, the missile launcher 1 allows eight missiles to be transported and launched before reloading.
  • the support base 11 is for example, a flatrack platform or "flatrack support base”.
  • the support base 11 comprises at least one gripping element 12, such as a gripping arm, adapted to allow the lifting of the support base 11 by lifting means (for example a lifting arm) in order to unload the support base 11 from, or to load the support base 11 onto, the mounting frame 2 on a transport vehicle 5.
  • lifting means for example a lifting arm
  • the aforesaid lifting arm may advantageously be provided on board the missile launcher 1, in other words it may be a component integrated into the missile launcher itself.
  • the aforesaid lifting arm may be installed on the mounting frame 2.
  • the support base 11 comprises a support foot 14, which is adapted and configured to act as a support element for the support base 11 on the ground during en-bloc loading or unloading of the support base 11 from the mounting frame 2.
  • the support foot 14 comprises at least one wheel 13, preferably a pair of wheels 13, pivotally hinged to the support foot 14.
  • the support foot 14 is pivotally hinged to the support base 11 to be moved between a retracted angular position, shown in Figure 3 , and an extended angular position, shown in Figure 4 .
  • the support foot 14 in the retracted angular position, is transverse, for example perpendicular to the support base 11, while in the extended angular position the support foot 14 is parallel to the support base 11.
  • the missile launching assembly 10 comprises at least one launching frame 20 fixed to the support base 11 to be integral thereto in rotation.
  • the launching frame 20 is secured removably to the support base 11. In this way, it is advantageously possible to change the launching frame 20 by replacing it with another in order to easily modify the launching assembly 10 so that it may be suitable to support and launch ammunition of different types.
  • the missile launching assembly 10 comprises a plurality of launching frames 20 secured to the support base 11. In the example shown in the figures, the missile launching assembly 10 comprises four launching frames 20 secured to the support base 11.
  • the launching frame 20 comprises at least one pair of uprights 21, 22.
  • the launching frame 20 comprises a first pair of uprights 21 and a second pair of uprights 22.
  • the pairs of uprights 21, 22 are spaced apart from each other.
  • the launching assembly 10 comprises a first launching container 100, or canister, containing a respective first missile.
  • the aforesaid launching container 100 is adapted and configured to allow an SVL (Soft Vertical Launch) of the missile contained therein and is, for example, made according to the teachings of the US patent 7,207,254 B2 .
  • the missile launching assembly 10 comprises eight launching containers 100, i.e. eight missiles. This number is not limitative but only illustrative.
  • the missile launching assembly 10 further comprises coupling elements S1, S2 through which the first launching container 100 is removably secured to the launching frame 20 between the pair of uprights 21,22.
  • each launching container 100 is removably secured to the launching frame 20 between a first pair of uprights 21 and a second pair of uprights 22.
  • the pairs of uprights 21, 22 are spaced apart from each other along an axis of prevalent longitudinal extension of the launching container 100.
  • the coupling elements S1,S2 comprise a first guide system S1 adapted and configured to allow a guided sliding of the first launching container 100 between the uprights 21,22 along a first stroke delimited between a first initial insertion position and a first final securing position. In this way, it is advantageously possible to also load a single launching container 100 into the launching frame 20 when the support base 11 is in the transport angular position, i.e. when the missile launching assembly 10 is in the transport configuration.
  • the aforesaid opposed tracks are parallel to each other.
  • the aforesaid sliders 101, 102 for example are or comprise pins, for example cylindrical, which project from two opposed side walls of the launching container 100.
  • the launching container 100 comprises a plurality of sliders, for example a first pair of opposed sliders 101 and two further pairs of opposed sliders 102.
  • the first pair of sliders 101 is spaced from the two further pairs of sliders 102 along the axis of prevalent longitudinal extension of the launching container 100.
  • the launching frame 20 comprises two pairs of uprights 21, 22 spaced apart from each other along a prevalent longitudinal extension direction of the first launching container 100 and the first guide system S1 is provided on both pairs of uprights 21, 22.
  • a launching frame 20 there are provided two pairs of opposed tracks on the two uprights 21, or front uprights 21, and two pairs of opposed tracks on the two uprights 22, or rear uprights 22, of the launching frame 20.
  • the terms 'front' and 'rear' are defined here with respect to the launching direction of the missile or missiles.
  • the aforesaid rails may be channels or openings defined in the thickness of the plate elements applied to the uprights 21, 22 or recesses made integrally in the thickness of the uprights 21, 22.
  • each track of the aforesaid pair of tracks comprises, from the initial insertion position to said final securing position, a first rectilinear segment and a second segment joined to the first rectilinear segment, the second segment being a segment inclined with respect to the first rectilinear segment or being a curvilinear segment.
  • the aforesaid expedient makes it easier to load and secure two separate launching containers 100 in a same launching frame 20, preferably in an arrangement wherein said launching containers 100 are arranged at a distance from each other in a direction perpendicular to the prevalent longitudinal extension directions of the launching containers 100.
  • the missile launching assembly 10 comprises a locking system 50 which may be actuated to be moved with respect to said pair of uprights 21,22 between a locked and a released position.
  • the locking system 50 prevents the launching container 100 from sliding, with respect to the launching frame 20, from the securing position.
  • the aforesaid locking system 50 allows the launching container 100 to slide with respect to the launching frame 20, both for the insertion of the launching container 100 into the launching frame 20 and for the extraction of the launching container 100 from the launching frame 20, for example in order to reload the launching frame 20 with a new launching container 100.
  • the locking system 50 comprises a movable arm 51 to which at least one locking element 52 is attached, which in the locked position is such that it interferes in abutment against a slider 101, 102 of the launching container 100 to prevent the slider 101, 102 from sliding inside the guide system S1, S2.
  • the aforesaid locking system 50 comprises for each upright 21, 22 a respective movable arm 51 to which two movable locking elements 52 are pivotally hinged in order to lock two launching containers 100 to the uprights 21, 22 simultaneously.
  • the movable arm 51 may be moved by means of a manual actuating lever 53, preferably pivotally hinged to the upright 21, 22 to be rotated between a released position ( Figure 10 ) and a locked position ( Figure 11 ).
  • a manual actuating lever 53 preferably pivotally hinged to the upright 21, 22 to be rotated between a released position ( Figure 10 ) and a locked position ( Figure 11 ).
  • This expedient also contributes to the quick loading and unloading of the launching container 100 from the launching frames 20.
  • the missile launching assembly 10 comprises a second launching container 100 containing a respective second missile, and the aforesaid coupling elements are such that the second launching container 100 is removably secured to the launching frame 20 between the pair of uprights 21, 22.
  • the coupling elements comprise a second guide system S2 adapted and configured to allow a guided sliding of the second launching container 100 between said uprights 21,22 along a second stroke delimited between a first initial insertion position and a second final securing position.
  • the second launching container 100 in the second final securing position, overhangs the first launching container 100 when the latter is in the first final securing position.
  • the aforesaid second stroke has a length shorter than the first stroke.
  • the second guide system S2 comprises a second pair of opposed tracks, each secured to or integrated in a respective upright of said pair of uprights 21, 22.
  • the second launching container 100 comprises a pair of sliders 101, 102 which protrude from opposite side walls of the second launching container 100 to be slidingly received in the second pair of opposed tracks.
  • the missile launching assembly 10 comprises a vibration damping system operatively interposed between the launching frame 20 and the support base 11 of the missile launching assembly 10.
  • the launching frame 20 comprises a plurality of connection plates 25 mechanically coupled to the support base 11 and a plurality of dampers operatively interposed between the connection plates 25 and the support base 11.
  • the dampers are or comprise, for example, plate-like elements made of e.g. a rubbery material to dampen vibrations. These elements are interposed and tightened between the connection plates 25 and the support base 11 and are, for example, mounted on the connection plates 25.
  • the vibration damping system advantageously allows the ammunition to be protected against vibrations and shock induced during the logistical transport and during loading and/or unloading of the launching assembly 10.
  • the missile launching assembly 10 further comprises a controllable mechanical locking system to assume an activation and deactivation state, wherein in the activation state the mechanical locking system allows the launching frame 20 to be mechanically coupled to the support base 11 to cancel out the effects of the vibration damping system.
  • the aforesaid mechanical locking system makes it possible to bypass the aforesaid plurality of dampers, creating a rigid mechanical connection between the launching frame 20 and the support base 11.
  • the aforesaid mechanical locking system is such that the launching frame 20 and the support base 11 are brought into a hard mounting-type mutual coupling configuration.
  • the aforesaid mechanical locking system comprises at least one pin sliding between an extended and a retracted position, wherein the pin is for example provided on board the support base 11 and wherein, when the mechanical locking system is in the activated state, the pin is in the extended position and is operatively interposed between the support base 11 and the launching frame 20, for example to be at least partially received in a matching seat 26 provided on the launching frame 20, for example provided on the connection plates 25.
  • the aforesaid mechanical locking system may be manually activated and deactivated.
  • the proposed missile launching assembly 10 fully achieves its objects in terms of overcoming the drawbacks of the known art.
  • missile launcher 1 has been shown operatively coupled to a transport vehicle 5, in particular a land-based vehicle, such a missile launcher in an alternative configuration may be constructed as a stand-alone system equipped with a mounting frame 2, directly installable on a support surface that allows it to be secured to a bearing surface that may be secured to any land or naval transport vehicle.
  • the missile launcher 1 comprises an electrical power supply system 30 installed on board the mounting frame 2 comprising an electric generator adapted and configured to make the missile launcher 1 autonomous from external power sources.
  • the aforesaid electrical power supply system 30 allows the missile launcher 1 to be supplied with all the electrical power required to perform its functions (deployment from the transport configuration to the launching configuration and vice versa, fire, surveillance, etc.).
  • the aforesaid power supply system further comprises an interface that allows the connection of the power supply system to an external electrical power supply line, for example to a three-phase, 400V line at 50Hz.
  • the power supply system 30 comprises an uninterruptible power supply - UPS - adapted and configured to power the missile launcher 1 in the event of an electric generator failure.
  • the missile launcher further comprises a radiocommunications system 40 installed on board the mounting frame 2 and adapted and configured to allow two-way remote data communication between the missile launcher 1 and a remote unit such as a remote control and command center.
  • the radiocommunications system comprises at least one telescopically extendable support shaft 41 installed on the mounting frame 2. This support shaft 41 for example supports at least one antenna of the aforesaid radiocommunications system.
  • FIG 12 shows the launching assembly 10, wherein numbers identical to the preceding embodiments are used for the same corresponding parts.
  • the support base 11 comprises, at the rear end RE, a support foot 14, adapted and configured to act as a support element for the support base 11 on the ground during en-bloc loading or unloading of the support base 11 from the mounting frame 2.
  • the support foot 14 comprises at least one wheel 13, preferably a pair of wheels 13, pivotally hinged to the support foot 14.
  • the support base 11 comprises, at the front end FE, at least one gripping element 12, as illustrated in one of the preceding embodiments.
  • the ends FE and RE are defined along the direction D, indicated with an arrow in Figure 12 , and representing the main extension direction of the launching assembly.
  • the gripping element 12 also comprises two front wheels or rollers 15, which are inclined with respect to the plane of the base 11.
  • the inclination is about 45 degrees.
  • This or another inclination of the wheels is used to slide the launching assembly onto a loader (not shown) that has a raised guide with correspondingly inclined walls.
  • the wheels 15 are arranged in such a way that they are symmetrical with respect to an axis D' (not shown) parallel to the axis D and central with respect to the size of the launching assembly with respect to the axis D.
  • one or more additional wheel assemblies 16,17 may be hinged to the support foot 14 (more precisely, to the frame that constitutes or supports it). These additional wheel assemblies may be secured to the opposite side with respect to the side of the frame of the support foot 14 where the wheels 13 are hinged.
  • Each wheel assembly may have one or more wheels.
  • Such a plane is defined as a plane which, in use, is parallel to the plane of the loader or to the ground. In any case, even if the support base 11 is contoured, it is always possible to define a plane with respect to which the directions mentioned above are defined, and this plane will be defined expediently with respect to the plane of the loader, the ground or any other plane on which the loading assembly is placed or moved.
  • wheel assemblies 16,17 may be expediently secured directly to the support base 11, and not to the support foot 13, so that they are not affected by the rotation of the latter.
  • the one or more wheel assemblies 16,17 also have the function of moving the launching assembly on the guides of the loader.
  • the wheels 17, which according to a particular aspect are placed on the outer side of the wheels 16, are used to provide a side register of the launching assembly 10.
  • the design of the launching assembly and in particular the position of the front rollers (identified with the number 15 in the drawings) and the lifting arm (identified with the number 12) allows the system to be unloaded onto a support vehicle equipped with a floor panel slightly longer than the Flatrack itself (of the order of a few cm). Essentially, with the system according to the invention, one no longer needs large areas to unload the Flatrack and this is a great advantage for the sector.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP20153069.8A 2019-02-05 2020-01-22 Ensemble de lancement de missile et lanceur de missile comprenant ledit ensemble de lancement Active EP3693691B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL20153069T PL3693691T3 (pl) 2019-02-05 2020-01-22 Zespół wyrzutni rakiet i wyrzutnia rakiet zawierająca wymieniony zespół wyrzutni

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IT102019000001627A IT201900001627A1 (it) 2019-02-05 2019-02-05 Gruppo di lancio missilistico e lanciatore missilistico comprendente detto gruppo di lancio

Publications (2)

Publication Number Publication Date
EP3693691A1 true EP3693691A1 (fr) 2020-08-12
EP3693691B1 EP3693691B1 (fr) 2022-03-02

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EP20153069.8A Active EP3693691B1 (fr) 2019-02-05 2020-01-22 Ensemble de lancement de missile et lanceur de missile comprenant ledit ensemble de lancement

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EP (1) EP3693691B1 (fr)
ES (1) ES2917598T3 (fr)
IT (1) IT201900001627A1 (fr)
PL (1) PL3693691T3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU206042U1 (ru) * 2021-03-16 2021-08-17 Хаджи-Мурат Хасанович Байсиев Противоградовая ракетная пусковая установка
RU211047U1 (ru) * 2021-12-28 2022-05-18 Федеральное государственное казенное военное образовательное учреждение высшего образования "ВОЕННАЯ АКАДЕМИЯ МАТЕРИАЛЬНО-ТЕХНИЧЕСКОГО ОБЕСПЕЧЕНИЯ имени генерала армии А.В. Хрулева" Складной сотовый пакет направляющих для реактивных снарядов

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6060045A (ja) * 1983-09-09 1985-04-06 Shin Meiwa Ind Co Ltd 荷役車両
EP1710530A2 (fr) 2005-04-07 2006-10-11 MBDA ITALIA S.p.A. Conteneur pour le transport et le lancement vertical d'une roquette, méthode de fabrication d'un tel conteneur et rampe de lancement
US7207254B2 (en) 2001-03-27 2007-04-24 Mbda Uk Limited Launching of missiles
JP4384968B2 (ja) * 2004-11-25 2009-12-16 新明和工業株式会社 誘導弾発射機におけるブラスト遮蔽装置
KR101138154B1 (ko) * 2008-12-18 2012-04-23 두산디에스티주식회사 로켓 포드 탑재 시스템
JP2016016758A (ja) * 2014-07-09 2016-02-01 株式会社Ｉｈｉエアロスペース 移動制御装置
JP2017007400A (ja) * 2015-06-17 2017-01-12 株式会社Ｉｈｉエアロスペース 自走飛翔体発射装置

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT201800004993A1 (it) * 2018-05-02 2019-11-02 Gruppo di lancio missilistico e lanciatore missilistico comprendente detto gruppo di lancio

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6060045A (ja) * 1983-09-09 1985-04-06 Shin Meiwa Ind Co Ltd 荷役車両
US7207254B2 (en) 2001-03-27 2007-04-24 Mbda Uk Limited Launching of missiles
JP4384968B2 (ja) * 2004-11-25 2009-12-16 新明和工業株式会社 誘導弾発射機におけるブラスト遮蔽装置
EP1710530A2 (fr) 2005-04-07 2006-10-11 MBDA ITALIA S.p.A. Conteneur pour le transport et le lancement vertical d'une roquette, méthode de fabrication d'un tel conteneur et rampe de lancement
KR101138154B1 (ko) * 2008-12-18 2012-04-23 두산디에스티주식회사 로켓 포드 탑재 시스템
JP2016016758A (ja) * 2014-07-09 2016-02-01 株式会社Ｉｈｉエアロスペース 移動制御装置
JP2017007400A (ja) * 2015-06-17 2017-01-12 株式会社Ｉｈｉエアロスペース 自走飛翔体発射装置

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU206042U1 (ru) * 2021-03-16 2021-08-17 Хаджи-Мурат Хасанович Байсиев Противоградовая ракетная пусковая установка
RU211047U1 (ru) * 2021-12-28 2022-05-18 Федеральное государственное казенное военное образовательное учреждение высшего образования "ВОЕННАЯ АКАДЕМИЯ МАТЕРИАЛЬНО-ТЕХНИЧЕСКОГО ОБЕСПЕЧЕНИЯ имени генерала армии А.В. Хрулева" Складной сотовый пакет направляющих для реактивных снарядов

Also Published As

Publication number Publication date
ES2917598T3 (es) 2022-07-11
PL3693691T3 (pl) 2022-05-30
IT201900001627A1 (it) 2020-08-05
EP3693691B1 (fr) 2022-03-02

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