• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Adjustable saddle for launcher light launcher single use. Adjustable upholstery intended to support a reusable control unit of a missile launcher and a single-use launcher tube complementary to the control unit both in the armed position, in which both components are coupled through connectors and ready to fire, as in the disassembled position, in which both components are separated and uncoupled, for safe transport, by means of a first rotating support, a second tilting support joined to the first support, and a guided carriage mounted on the second support, the unit being control anchored to the second support and the launch tube attached to the guided carriage, allowing the relative movement of the launching tube with respect to the control unit by means of the movement of the guided carriage. (Machine-translation by Google Translate, not legally binding)
    公开号:ES2585603A1
    申请号:ES201530950
    申请日:2015-07-01
    公开日:2016-10-06
    发明作者:Andrés FUENTEJADA ROCA
    申请人:Anortec SL；
    IPC主号:
    专利说明:

    5
    10
    fifteen
    twenty
    25
    30
    DESCRIPTION
    ADJUSTABLE FIT FOR LIGHT PIPE LAUNCHER LAUNCHER
    ONLY USE
    Technique Field
    The present invention concerns the field of adjustable, or adjustable, brackets, intended for the support of single-use light launchers with a single-use launcher tube, said aft provided with two degrees of freedom with respect to two axis of rotation perpendicular to each other, by means of a first articulated support with respect to a base around a vertical axis, and a second articulated support with respect to the first support around a horizontal axis, thus allowing a missile launcher anchored on said second support to move by means of a lateral rotation or by means of a vertical swing.
    State of the art
    Single-use launcher tube launchers are widely known. It is also known that they have a reusable control unit suitable to be easily and quickly coupled to said launch tube, to allow the aiming and firing of the missile from said control unit, or optionally also to allow guidance of the fired missile. These missile launchers are lightweight and can be transported by one or two users, and be fired supporting them on a tripod or some models even on the user's shoulder. Examples of this type of missile launchers are those marketed by Rafael, under the Spike brand.
    Adjustable shafts are also known adapted to support missile launchers of this type, for example by means of documents US3389637 and GB1223922.
    Neither of these documents anticipates a problem that allows the launching tube to be held in an uncoupled position of the control unit, avoiding fatigue or breakage of the connectors that join both elements during transport, and that also allows a quick coupling of both elements by means of a displacement of one of them guided by the afuste itself, allowing to prepare the afuste for its use of fast way.
    Brief Description of the Invention
    5
    10
    fifteen
    twenty
    25
    30
    The present invention concerns an adjustable flush for single-use single-tube launcher with a reusable control unit that allows locating the target, firing the missile and / or guiding the missile.
    These types of missile launchers are designed to be transported by one or two soldiers, and consist of a single-use launcher tube that contains a self-propelled missile and the aforementioned control unit that contains the optical and / or electronic elements that allow the User locate the target, as well as the missile trigger. Optionally, the control unit may also contain instruments that allow guidance of the missile during its flight to the target.
    Both the launch tube and the control unit have complementary connectors that allow said elements to be transported separately but that, to proceed with their use, the launch tube is mechanically and electrically coupled to the control unit, then becoming in solidarity, allowing a user to hold the missile launcher on his shoulder, or to arrange it on a shoulder, to proceed with the aiming and firing of the missile towards a target.
    After firing, the launch tube without missile can be separated from the control unit and replaced by another new launch tube allowing another shot to be taken.
    This type of missile launcher does not have recoil, because the missile is self-propelled, and they are also provided for the separate transport of the launcher tube and the control unit, for these reasons the mentioned connectors are not very resistant and are not sized to resist prolonged vibrations or large inertial loads. This limitation prevents the transport of the control unit attached to the launcher tube, since the connectors will eventually break down, it being therefore unfeasible to have said missile launcher ready for use mounted on a groove on for example a vehicle, and preventing its rapid use in front of an enemy that is fast approaching.
    Thus, the present invention aims to provide a fitting that allows the control unit and the launch tube to be held in the disarmed position, that is to say, both elements being disengaged, allowing the transport of said aforementioned with said missile launcher in the disarmament position avoiding fatigue. of the connectors, and allowing said to affix a quick union of the launch tube with the control unit through said connectors, then becoming in the armed position, and allowing the missile launcher to be used, by means of a simple and fast operation, allowing So react quickly to a threat.
    5
    10
    fifteen
    twenty
    25
    30
    The aforementioned adjustable afuste includes:
    • a first support that can be fixed to a base, and equipped with a first joint that can be rotated around a vertical axis and to avoid axial displacement in the direction of the vertical axis;
    • a second support attached to the first support by means of at least a second articulation suitable for tilting around a horizontal axis and to avoid an axial displacement in said direction of the horizontal axis;
    • at least one locking element that allows to fix, in a desired angular position, said first articulation and / or second articulation;
    The first articulation, when turning relative to a vertical axis, gives the first support freedom of lateral angular movement. The base on which the first support is fixed can be, for example, a coupling configuration provided in a military vehicle. It is also envisaged that said affix includes vibration absorption devices that reduce the vibrations transmitted to the missile launcher coupled thereto. Such devices may be for example elastomeric elements arranged between the base and the vehicle, or in other locations.
    These elements provide the afuste with two degrees of freedom, allowing the missile launcher attached to said afuste to point in any direction.
    In addition, in a novel way, the proposed setting also incorporates:
    • a guided car attached to the second support by means of glutton elements that allow a guided movement of said guided car with respect to said second support between a disarmament position and an armed position;
    • control unit anchors designed to precisely position and securely and securely fasten the control unit to the flush; Y
    • launcher tube anchors designed to precisely position and securely and securely fix the single-use launcher tube to the shaft;
    the control unit anchors being on the second support and the launch tube anchors on the guided carriage, or vice versa the control unit anchors on the guided carriage and the launch pipe anchors on the second support, allowing a guided displacement of the launch tube anchors with respect to the control unit anchors.
    5
    10
    fifteen
    twenty
    25
    30
    Therefore, in one embodiment, the second support of the afuste incorporates anchors of control unit in which to fix the control unit of the missile launcher, and also the second support of the afuste incorporates a guided carriage on which pipe anchors are arranged launcher in which to fix the launcher tube of the missile launcher, in a complementary way with the missile control unit fixed directly on the second support. A reverse realization is also contemplated in which the control unit is fixed on the guided car.
    Optionally, it is provided that a coupling element or other guided carriage is also interposed between the launcher element attached to the second support and said second support, thus allowing the afoste to be adapted to different models of missile launchers, or allowing relative movement with respect to the rest of the afuste of any of the two parts that make up the missile launcher.
    Therefore, said guided carriage can move with respect to the rest of the second support in a guided manner, by means of the glutton elements, moving the launcher tube of the missile launcher with respect to the control unit of the missile launcher, between the disarming position, in which both parts they are decoupled, and the position of armed, in which both parts are coupled through the mentioned connectors and ready to be fired.
    It will be understood that a realization in which the launch tube was fixed on the second support, and it was the control unit that is fixed on the guided car would be perfectly feasible, and totally obvious in view of the exposed realization, both of which can be considered Identical and integral embodiments of the proposed invention.
    It is also understood that the anchors can be very different Indole, for example, they can be straps, clamps, pins, screws, or anchors produced by the interaction of complementary geometries such as groove and groove configurations.
    According to a further embodiment, the guided car admits, with respect to the axis defined by the firing direction, a lateral displacement and an axial displacement. These two directions of movement, combined, provide a bolt-type displacement, or L-shaped path, which allows the coupling of the launcher tube with the control unit to occur through a lateral insertion of the connectors, and a sliding of the themselves in the firing direction. However, other coupling paths are also contemplated, such as a U-shaped path, or others.
    Additionally, the lateral displacement of the guided carriage is expected to follow a curved path, which allows the lateral insertion path of the tube connectors
    5
    10
    fifteen
    twenty
    25
    30
    launcher with respect to the connectors of the control unit is more similar to the one to be followed by being carried out manually by the user of the missile launcher.
    According to another example of realization, a lever is connected to the guided carriage, and allows to drive the guided movement by a user by manipulating said lever, which facilitates the user to put the missile launcher in the armed position or in the position of disassembled by manipulating the lever with one hand.
    Optionally said lever protrudes from a lower face of the guided carriage and the second support.
    Additionally, the gluttony elements include the lever attached to the guided carriage, and a cam groove integrated in the second support that defines the travel of the lever.
    Retention means are also provided that allow the position of the guided car to be locked in the disarmament position and / or in the armed position.
    The disarmament position keeps the control unit and the launcher tube physically disconnected and separated, which protects the union connectors of said control unit with the launcher tube against breakage or wear caused by vibrations or shaking, for example during transport on board a vehicle. Therefore, thanks to this afuste, the missile launcher can be transported on board a vehicle fixed to the afuste in disarmament position, without risk of damage, and allowing at the same time to be able to place the missile launcher in an armed position in a few seconds, allowing to react quickly to a threat.
    It will be understood that references to geometric position, such as parallel, perpendicular, tangent, etc. they admit deviations of up to ± 5 ° with respect to the theoretical position defined by said nomenclature.
    Other features of the invention will appear in the following detailed description of an embodiment example.
    Brief description of the figures
    The foregoing and other advantages and characteristics will be more fully understood from the following detailed description of an exemplary embodiment with reference to the accompanying drawings, which should be taken by way of illustration and not limitation, in which:
    Fig. 1 shows a perspective view of the aftertaste from a first point of view, according to a first embodiment, the affix being mounted and devoid of missile launchers;
    5
    10
    fifteen
    twenty
    25
    30
    Fig. 2 shows a perspective view of the aft shown in Fig. 1 from a second point of view opposite to the first point of view, the set being mounted and devoid of missile launchers;
    Fig. 3 shows a perspective view of the aft shown in Fig. 1 from the first point of view, the aforesaid being exploded and devoid of missile launchers;
    Fig. 4 shows a perspective view of the aft shown in Fig. 2 from the second point of view, the aforesaid being exploded and devoid of missile launchers;
    Fig. 5 shows a perspective view of the aft shown in Fig. 2 from the second point of view, the aft being mounted and provided with a missile launcher in the disassembled position, with the launching tube physically separated from the control unit;
    Fig. 6 shows a perspective view of the aft shown in Fig. 2 from the second point of view, the aft being mounted and provided with a missile launcher in an armed position, with the launch tube attached and connected to the control unit.
    Detailed description of an example of realization
    The present invention relates to an adjustable flush for a light missile launcher 40 with a single-use launcher tube 42 and reusable control unit 41, the control unit 41 being able to locate the target and shoot, and optionally also being the responsible for guiding the missile during its flight to the target. In said missile launcher 40, the launch tube 42 is connected to the control unit 41 by means of mutually complementary and attachable connectors 43 located both in the control unit 41 and in the launch tube 42. Said connectors 43 allow both the mechanical support of the tube launcher 42 attached to the control unit 41, such as the electrical connection between both halves of the missile launcher 40, allowing the ignition of the missile, among other functions thereof, to be controlled from the control unit 41.
    According to a preferred embodiment of the present invention, shown in Fig. 1 with an illustrative non-limiting character, the proposed set 1 consists of a first support 11 articulated with respect to a base 2 by means of a first articulation 10 capable of rotating around a vertical axis EV, giving freedom of horizontal angular rotation, and avoiding an axial displacement in the direction of the vertical axis EV.
    Said first support 11 has a vertical side arm, with an upper end approximately parallel to said vertical axis EV, at which end a second support 21 is articulated, which is articulated by at least a second
    5
    10
    fifteen
    twenty
    25
    30
    articulation 20 suitable for tilting around a horizontal axis EH and to avoid an axial displacement in said direction of the horizontal axis EH, allowing a second degree of freedom of the spindle 1 in a tilting direction.
    At least one locking element 14 is included which allows to fix, in a desired angular position, said first joint 10 and / or second joint 20.
    On said second support 21, control unit anchors 22 are provided for fixing said control unit 41 of the missile launcher 40 to said second support 21 removably, the shape and position of said control unit anchors 22 being complementary to the shape and position of the control unit 41 in operative position (armed or disassembled), or part thereof.
    Said second support 21 also supports a guided carriage 30 which, by means of gluttony elements 32, 33, 34, 35, can be moved relative to the rest of the second support 21 following a path determined by said gluttonic elements 32, 33, 34, 35 The trajectory determined by said glutton elements 32, 33, 34, 35 will depend on the path required for the union and connection of the control unit 41 with the launch tube 42, typically being a bolt-type L path, but contemplating other different paths, for example U-shaped.
    On said guided carriage 30, launching tube anchors 31 are provided for fixing said launching tube 42 to the guided carriage 30 precisely and safely. In the present embodiment, said launch tube anchors 31 consist of adjustable fasteners with quick release that clamp said launch tube 42 against the guided carriage 30.
    In this example, the guided carriage 30 and the gliding 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 provided with lateral guide grooves 34. Two cylindrical shafts 35 parallel to each other and with respect to the direction of firing DD, have their ends inserted in said lateral guidance grooves 34, allowing lateral displacement, with respect to the direction of DD trip, of said two cylindrical axes 35, following the path defined by the lateral guide grooves 34, which in this case are curved. Both cylindrical shafts 35 are connected to each other to keep their distance constant, and preferably have bearings to facilitate their movement along the lateral guide grooves 34.
    On said cylindrical axes 35, the guided carriage 30 is arranged, connected thereto by means of sliding skids provided to slide along said cylindrical axes 35, allowing the axial displacement of the guided carriage 30 in the direction of firing DD.
    The guided carriage 30 has a lever 32 attached to its lower face and protrudes down 5 through a cam groove 33 made in the second support 21. The interaction between the lever 32 and the cam groove 33 defines the path of the guided carriage 30, between the assembly position, in which the launch tube 42 is coupled to the control unit 41, and the disarmament position, in which said components of the missile launcher 40 are decoupled and separated, allowing safe transport of the missile launcher 40 without risk 10 that the transport vibrations damage the connectors 43. Obviously the path defined by the lever 32 and the cam groove 33 must be contained within the freedom of movement allowed by both the lateral guide grooves 34 and by cylindrical axes 35.
    权利要求:
    Claims (9)
    [1]
    5
    10
    fifteen
    twenty
    25
    30
    1. - Adjustable gun for light missile launcher of single-use launcher tube equipped with a reusable control unit that allows to locate the target, fire the missile and / or guide the missile, including said adjustable gun:
    • a first support (11) attachable to a base (2), equipped with a first joint (10) capable of rotating around a vertical axis (EV) and to avoid axial displacement in the direction of the vertical axis (EV);
    • a second support (21) attached to the first support (11) by at least a second joint (20) suitable for tilting around a horizontal axis (EH) and to avoid an axial displacement in said direction of the horizontal axis (EH) ;
    • at least one locking element (14) which allows to fix, in a desired angular position, said first joint (10) and / or second joint (20);
    characterized in that the flute (1) also incorporates:
    • a guided carriage (30) connected to the second support (21) by means of glutton elements that allow a guided movement of said guided carriage (30) with respect to said second support (21) between a disarmament position and an armed position;
    • control unit anchors (22) designed to precisely position and to securely and securely fix a control unit (41) of a missile launcher (40) to the shaft (1); Y
    • launching tube anchors (31) designed to precisely position and securely and securely fix a single-use launch tube (42) to the spindle (1);
    the control unit anchors (22) and the launcher tube anchors (31) being attached one on the guided carriage (30) and the others on the second support (21), allowing a guided displacement of the launch tube anchors ( 31) with respect to the control unit anchors (22).
    [2]
    2. - Flush according to claim 1 characterized in that said guided displacement of the guided carriage (30) includes, with respect to the axis defined by the firing direction (DD), a lateral displacement and an axial displacement in the firing direction (DD).
    [3]
    3. - Flush according to claim 2 characterized in that the lateral displacement of the guided carriage (30) follows a curved path defined by lateral guide grooves (34).
    [4]
    4. - Flush according to claim 2 or 3 characterized in that the axial displacement in the firing direction (DD) of the guided carriage (30) follows a straight path defined by a pair of cylindrical axes (35) parallel to the firing direction ( DD).
    [5]
    5. - Flush according to claim 3 and 4 characterized in that the cylindrical axes (35) are moved laterally guided by the lateral guide grooves (34).
    [6]
    6. -Adjust according to claim 2, 3, 4 or 5 characterized in that the guided car has a lever (32) connected thereto which allows driving the guided movement by a user.
    [7]
    7. - Flush according to claim 6 characterized in that the lever (32) protrudes through a lower face of the guided carriage (30) and the second support (21).
    [8]
    8. - Set according to claim 6 or 7, characterized in that the guide elements include the lever (32) attached to the guided carriage (30), and a cam groove (33) integrated in the second support (21) defining the path of the lever (32).
    [9]
    9. - Affix according to any one of the preceding claims, characterized in that 15 retaining means allow to block the position of the guided carriage (30) in the position
    Disarmament and / or assembly position.
    类似技术:
    公开号 | 公开日 | 专利标题
    ES2292888T3|2008-03-16|REMOVABLE SPEARGUN.
    US7401431B2|2008-07-22|Trigger actuated stabilization device
    ES2321982T3|2009-06-15|CYLINDER BLOCK FOR THE RECOVERY OF GASES AND PORTABLE WEAPON.
    ES2612909T3|2017-05-19|Trigger control equipment for a light firearm
    ES2734714T3|2019-12-11|Device for installing accessories in a firearm
    ES2640243T3|2017-11-02|Automatic weapon with auxiliary trigger in the folding stock that allows the weapon to be fired in bullpup configuration
    ES2689074T3|2018-11-08|Artillery projectile with a piloted phase
    ES2585603B1|2017-01-19|Adjustable afuste for single-use launcher tube light missile launcher
    ES2544496T3|2015-09-01|Gun storage tank for a submarine
    US10663255B2|2020-05-26|Sight adapter for handheld mortar system
    US9459075B1|2016-10-04|Elevated sight
    ES2809551T3|2021-03-04|Adapter for the placement of at least one additional equipment in a self-loading firearm and self-loading firearm equipped with the same
    ES2311757T3|2009-02-16|HANDLE FOR FIREARM.
    ES2576729T3|2016-07-11|Device to support a grenade in a barrel of a backload weapon
    ES2788637T3|2020-10-22|Firearm stand
    KR101511055B1|2015-04-10|Accessory fixing device of fire arm
    ES2276278T3|2007-06-16|BARRICADE BREAKER.
    ES2730550T3|2019-11-11|Loader arrangement for a rifle and a rifle with such a loader arrangement
    KR101394326B1|2014-05-13|Sighting device for a firearm
    WO2016038229A1|2016-03-17|Accessory for the installation, positioning and fixing of a telescopic sight or any other aiming accessory on an air rifle or firearm
    ES2326064B1|2010-07-13|ACCESSORY VISOR DEVICE FOR FIREARMS.
    ES2565694B1|2017-01-20|Modular adjustable gun for guns and modular adjustable gun kit
    ES2658387B1|2018-10-03|ELECTRONIC POINT DEVICE FOR PROJECTILE LAUNCHER
    US20070137630A1|2007-06-21|Ball nock arrow release system
    US5902952A|1999-05-11|Anti tip-off device
    同族专利:
    公开号 | 公开日
    EP3112796A1|2017-01-04|
    EP3112796B1|2018-03-14|
    ES2671800T3|2018-06-08|
    ES2585603B1|2017-01-19|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3389637A|1966-06-15|1968-06-25|Bolkow Gmbh|Firing and guiding mechanism for jetpropelled missiles launched from launcher tubes|
    US3754497A|1970-08-06|1973-08-28|Sarmac Sa|Transporting and firing chest for self-propelled projectiles|
    GB2238917A|1989-09-06|1991-06-12|Souriau Electric Gmbh|Connector arrangement|
    GB2304473A|1995-08-16|1997-03-19|Whitaker Corp|Umbilical cord for projectile launching device|
    US2913960A|1956-03-07|1959-11-24|Harvey Herbert|Light weight t-20 shoulder stock for 3.5 inch rocket launcher|
    US3999460A|1975-12-03|1976-12-28|Skliris Lewis E|Rocket launching mechanism|
    EP0221783B1|1985-10-31|1990-04-18|British Aerospace Public Limited Company|Clamping mechanisms|
    GR980100049A|1997-02-19|1998-10-30|Buck Werke Gbmh & Co|Arrangement for multiple launches of missiles from the shoulder|CN107388893B|2017-09-01|2019-04-19|西北工业大学|A kind of pencil rocket bullet emitter|
    法律状态:
    2017-01-19| FG2A| Definitive protection|Ref document number: 2585603 Country of ref document: ES Kind code of ref document: B1 Effective date: 20170119 |
    2021-10-15| PC2A| Transfer of patent|Owner name: PLESIUM, SL Effective date: 20211008 |
    优先权:
    申请号 | 申请日 | 专利标题
    ES201530950A|ES2585603B1|2015-07-01|2015-07-01|Adjustable afuste for single-use launcher tube light missile launcher|ES201530950A| ES2585603B1|2015-07-01|2015-07-01|Adjustable afuste for single-use launcher tube light missile launcher|
    EP16382275.2A| EP3112796B1|2015-07-01|2016-06-15|Swiveling mount for a lightweight missile launcher having a single-use launch tube|
    ES16382275.2T| ES2671800T3|2015-07-01|2016-06-15|Adjustable afuste for single-use launcher tube light missile launcher|
    [返回顶部]