EP3112796A1 - Schwenkbare halterung für einen leichten flugkörperwerfer mit ausstossrohr für einmalgebrauch - Google Patents

Schwenkbare halterung für einen leichten flugkörperwerfer mit ausstossrohr für einmalgebrauch Download PDF

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Publication number
EP3112796A1
EP3112796A1 EP16382275.2A EP16382275A EP3112796A1 EP 3112796 A1 EP3112796 A1 EP 3112796A1 EP 16382275 A EP16382275 A EP 16382275A EP 3112796 A1 EP3112796 A1 EP 3112796A1
Authority
EP
European Patent Office
Prior art keywords
support
mount
control unit
launch tube
guided
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
EP16382275.2A
Other languages
English (en)
French (fr)
Other versions
EP3112796B1 (de
Inventor
Andrés Fuentetaja Roca
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.)
Anortec SL
Original Assignee
Anortec SL
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Filing date
Publication date
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Publication of EP3112796A1 publication Critical patent/EP3112796A1/de
Application granted granted Critical
Publication of EP3112796B1 publication Critical patent/EP3112796B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • F41F3/0455—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
    • F41F3/055—Umbilical connecting means
    • 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
    • F41A27/00—Gun mountings permitting traversing or elevating movement, e.g. gun carriages
    • F41A27/06—Mechanical systems
    • 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
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
    • H01R13/629—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances
    • H01R13/633—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for disengagement only
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G1/00—Sighting devices
    • F41G1/38—Telescopic sights specially adapted for smallarms or ordnance; Supports or mountings therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G1/00—Sighting devices
    • F41G1/38—Telescopic sights specially adapted for smallarms or ordnance; Supports or mountings therefor
    • F41G1/393—Mounting telescopic sights on ordnance; Transmission of sight movements to the associated gun

Definitions

  • the present invention relates to the field of swiveling supports, also called mounts, provided for supporting lightweight missile launchers having a single-use launch tube, said mount being equipped with two degrees of freedom with respect to two rotational axes perpendicular to one another, by means of a first support articulated with respect to a base about a vertical axis, and a second support articulated with respect to the first support about a horizontal axis, thereby allowing a missile launcher anchored on said second support to move by means of lateral rotation or by means of vertical rolling.
  • Missile launchers having a single-use launch tube are well known. They are also known to have a reusable control unit suitable for being easily and quickly coupled to the mentioned launch tube to allow aiming and firing the missile from said control unit, or also to optionally allow guiding the fired missile. These missile launchers are lightweight and allow being carried by one or two users and being fired by supporting them on a tripod or even on the shoulder of the user in some models. An example of missile launchers of this type could be those marketed by the company Rafael, under the trademark known as Spike.
  • Swiveling mounts adapted for supporting missile launchers of this type are also known by means of patent documents US3389637 and GB 1223922 , for example.
  • the present invention relates to a swiveling mount for a lightweight missile launcher having a single-use launch tube equipped with a reusable control unit that allows locating the target, firing the missile and/or guiding the missile.
  • Missile launchers of this type are designed to be carried by one or two soldiers and consist of a single-use launch tube containing a self-propelled missile and the mentioned control unit containing the optical and/or electronic elements that allow the user to locate the target, as well as the missile trigger mechanism.
  • the control unit can also optionally contain instruments that allow guiding the missile in flight towards the target.
  • Both the launch tube and the control unit have complementary connectors that allow said elements to be carried separately but, in order to use them, the launch tube must be coupled both mechanically and electrically to the control unit, therefore becoming integral, allowing a user to hold the missile launcher on their shoulder, or to arrange it on a mount, to then aim and fire of the missile towards a target.
  • the launch tube which no longer has a missile, can be separated from the control unit and replaced with another new launch tube that allows firing again.
  • Missile launchers of this type do not experience recoil because the missile is self-propelled, and they are furthermore provided for separately carrying the launch tube and control unit; for these reasons, the mentioned connectors are not very resistant and are not sized to withstand prolonged vibrations or large inertial loads. This limitation prevents being able to carry the control unit attached to the launch tube, because the connectors would end up breaking, and prevents arranging said missile launcher ready for use assembled in a mount, for example on a vehicle, thus being unviable the rapid use thereof against a quickly approaching enemy.
  • the purpose of the present invention is to provide a swiveling mount that allows holding the control unit and the launch tube in a disarmed position, i.e., both elements uncoupled from one another, allowing carrying said swiveling mount with said missile launcher in the disarmed position, preventing the connectors from becoming worn, and said swiveling mount allowing a quick attachment of the launch tube with the control unit through said connectors, therefore being in an armed position, and allowing the missile launcher to be used by means of a simple and quick operation, thereby allowing a quick reaction to a threat.
  • the proposed mentioned swiveling mount includes:
  • the base on which the first support is fixed can be, for example, a coupling configuration provided in a military vehicle.
  • Said mount is also intended to include vibration absorption devices that reduce vibrations transmitted to the missile launcher coupled thereto.
  • Said devices can be elastomeric elements, for example, arranged between the base and the vehicle, or in other locations.
  • the proposed swiveling mount furthermore incorporates:
  • the second support of the swiveling mount incorporates control unit anchors in which the control unit of the missile launcher is to be fixed, and furthermore the second support of the mount incorporates a guided carriage on which launch tube anchors in which the launch tube of the missile launcher is to be fixed are arranged, complementarily to the control unit of the missile launcher fixed directly on the second support.
  • the inverse embodiment in which the control unit is fixed on the guided carriage is also contemplated.
  • said guided carriage can move with respect to the rest of the second support in a guided manner by means of the guiding elements, moving the launch tube of the missile launcher with respect to the control unit of the missile launcher between the disarmed position, in which both parts are uncoupled from one another, and the armed position, in which both parts are coupled through the mentioned connectors and ready to be fired.
  • anchors can be of very different types, being able to be, for example, belts, clamps, pins, screws, or anchors produced by the interaction of complementary geometries, such as rib and slot configurations.
  • the guided carriage allows lateral movement and axial movement with respect to the axis defined by the firing direction. These two directions of movement combined provide a bolt-type movement or a movement in an L-shaped path, which allows the coupling of the launch tube with the control unit to take place by means of the lateral insertion of the connectors and the sliding thereof in the firing direction.
  • other coupling paths are also contemplated, such as a U-shaped path or others.
  • the lateral movement of the guided carriage is intended to follow a curved path, which allows the lateral insertion path of the connectors of the launch tube with respect to the connectors of the control unit to be more like the one it would follow if it were done manually by the user of the missile launcher.
  • a lever is connected to the guided carriage and allows a user to actuate the guided movement by means of operating said lever, which makes it easier for the user to put the missile launcher in the armed position or disarmed position, operating the lever with just one hand.
  • Said lever optionally projects from a lower face of the guided carriage and the second support.
  • the guiding elements include the lever attached to the guided carriage and a cam slot integrated in the second support defining the trajectory of the lever.
  • Retaining means that allow locking the position of the guided carriage in the disarmed position and/or in the armed position are also provided.
  • the disarmed position keeps the control unit and the launch tube physically disconnected and separated from one another, which protects the connectors attaching said control unit with the launch tube from breaking or becoming worn as a result of vibrations or shaking, for example while it is carried on board a vehicle. Therefore, as a result of said mount, the missile launcher can be carried on board a vehicle fixed to the mount in the disarmed position, without the risk of becoming damaged, and at the same time allowing being able to put the missile launcher in the armed position in a few seconds, which allows quickly reacting to a threat.
  • references to geometric position such as, for example, parallel, perpendicular, tangent, etc. allow deviations of up to ⁇ 5° with respect to the theoretical position defined by said nomenclature.
  • the present invention relates to a swiveling mount for a lightweight missile launcher 40 having a single-use launch tube 42 and a reusable control unit 41, the control unit 41 being what allows locating the target and firing, and also optionally being responsible for guiding the missile in flight to the target.
  • the launch tube 42 is attached to the control unit 41 by means of connectors 43 that are complementary and can be coupled to one another located both in the control unit 41 and in the launch tube 42.
  • Said connectors 43 allow both mechanically holding the launch tube 42 attached to the control unit 41 and electrically connecting both halves of the missile launcher 40 to one another, allowing ignition of the missile, among other functions thereof, to be controlled from the control unit 41.
  • the proposed mount 1 consists of a first support 11 articulated with respect to a base 2 about a vertical axis EV, providing freedom of horizontal angular rotation.
  • Said first support 11 has a vertical side arm, with an upper end approximately parallel to said vertical axis EV, at the end of which there is attached in an articulated manner a second support 21, which is articulated about a horizontal axis EH, allowing a second degree of freedom of the mount 1 in a pivoting direction.
  • Control unit anchors 22 provided for detachably fixing the mentioned control unit 41 of the missile launcher 40 to the second support 21 are arranged on said second support 21, the shape and position of said control unit anchors 22 being complementary to the shape and position of the control unit 41 in the operative position (armed or disarmed), or a part thereof.
  • Said second support 21 also holds a guided carriage 30 which, by means of guiding elements 32, 33, 34, 35, can move with respect to the rest of the second support 21 following a path determined by said guiding elements 32, 33, 34, 35.
  • the path determined by said guiding elements 32, 33, 34, 35 will depend on the path required for the attachment and connection of the control unit 41 with the launch tube 42, typically being an L-shaped bolt-type path, but other different paths can be contemplated, for example a U-shaped path.
  • Launch tube anchors 31 provided for precisely and securely fixing said launch tube 42 to the guided carriage 30 are arranged on said guided carriage 30.
  • said launch tube anchors 31 consist of adjustable quick-closing clamps that clamp said launch tube 42 against the guided carriage 30.
  • the guided carriage 30 and the guiding elements 32, 33, 34, 35 consist of a pair of parallel walls perpendicular to the firing direction DD defined by the launch tube 42, said walls being arranged on the second support 21, each equipped with side guiding slots 34.
  • the ends of two cylindrical shafts 35 parallel to one another and with respect to the firing direction DD are inserted in said side guiding slots 34, allowing lateral movement, with respect to the firing direction DD, of said two cylindrical shafts 35, following the path defined by the side guiding slots 34, which are curved in this case.
  • Both cylindrical shafts 35 are connected to one another to maintain a constant distance between them, and they preferably have bearings to make their movement along the side guiding slots 34 easier.
  • the guided carriage 30 is arranged on said cylindrical shafts 35, attached thereto by means of skids provided for sliding along said cylindrical shafts 35, allowing axial movement of the guided carriage 30 in the firing direction DD.
  • the guided carriage 30 has a lever 32 attached to its lower face and projecting downwards through a cam slot 33 made in the second support 21. Interaction between the lever 32 and the cam slot 33 defines the path of the guided carriage 30 between the armed position, in which the launch tube 42 is coupled to the control unit 41, and the disarmed position, in which said components of the missile launcher 40 are uncoupled and separated from one another, which allows the missile launcher 40 to be carried safely without the risk of vibrations from being carried damaging the connectors 43.
  • the path defined by the lever 32 and the cam slot 33 obviously must be contained within the freedom of movement allowed both by the side guiding slots 34 and by cylindrical shafts 35.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP16382275.2A 2015-07-01 2016-06-15 Schwenkbare halterung für einen leichten flugkörperwerfer mit ausstossrohr für einmalgebrauch Active EP3112796B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ES201530950A ES2585603B1 (es) 2015-07-01 2015-07-01 Afuste orientable para lanzamisiles ligero de tubo lanzador de un solo uso

Publications (2)

Publication Number Publication Date
EP3112796A1 true EP3112796A1 (de) 2017-01-04
EP3112796B1 EP3112796B1 (de) 2018-03-14

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ID=56203290

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16382275.2A Active EP3112796B1 (de) 2015-07-01 2016-06-15 Schwenkbare halterung für einen leichten flugkörperwerfer mit ausstossrohr für einmalgebrauch

Country Status (2)

Country Link
EP (1) EP3112796B1 (de)
ES (2) ES2585603B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107388893A (zh) * 2017-09-01 2017-11-24 西北工业大学 一种小型火箭弹发射装置

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112113465A (zh) * 2019-06-21 2020-12-22 北京紫玉伟业电子科技有限公司 一种单兵防空导弹发射支架

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2913960A (en) * 1956-03-07 1959-11-24 Harvey Herbert Light weight t-20 shoulder stock for 3.5 inch rocket launcher
US4128039A (en) * 1975-12-03 1978-12-05 Skliris Lewis E Rocket launching mechanism
EP0221783A1 (de) * 1985-10-31 1987-05-13 British Aerospace Public Limited Company Befestigungsmechanismus
NL1008288C1 (nl) * 1997-02-19 1998-08-20 Buck Chem Tech Werke Meervoudige lanceerinrichting voor vanaf de schouder af te schieten geleide projectielen.

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1266665B (de) * 1966-06-15 1968-04-18 Boelkow Gmbh Abschuss- und Lenkvorrichtung fuer aus Abschussrohren startende, rueckstossgetriebene Flugkoerper mit loesbarem Visiertraeger
CH528058A (fr) * 1970-08-06 1972-09-15 Sarmac Sa Caisson de transport et de tir pour projectiles autopropulsés
DE3929567C1 (de) * 1989-09-06 1991-02-07 Souriau Electric Gmbh, 4006 Erkrath, De
GB9516804D0 (en) * 1995-08-16 1995-10-18 Amp Great Britain Umbilical cord for projectile launching device

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2913960A (en) * 1956-03-07 1959-11-24 Harvey Herbert Light weight t-20 shoulder stock for 3.5 inch rocket launcher
US4128039A (en) * 1975-12-03 1978-12-05 Skliris Lewis E Rocket launching mechanism
EP0221783A1 (de) * 1985-10-31 1987-05-13 British Aerospace Public Limited Company Befestigungsmechanismus
NL1008288C1 (nl) * 1997-02-19 1998-08-20 Buck Chem Tech Werke Meervoudige lanceerinrichting voor vanaf de schouder af te schieten geleide projectielen.

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107388893A (zh) * 2017-09-01 2017-11-24 西北工业大学 一种小型火箭弹发射装置
CN107388893B (zh) * 2017-09-01 2019-04-19 西北工业大学 一种小型火箭弹发射装置

Also Published As

Publication number Publication date
ES2671800T3 (es) 2018-06-08
ES2585603A1 (es) 2016-10-06
EP3112796B1 (de) 2018-03-14
ES2585603B1 (es) 2017-01-19

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