EP0448898A1 - Dispositif pour tirer une roquette, dans lequel le conteneur de stockage fait fonction de lanceur - Google Patents

Dispositif pour tirer une roquette, dans lequel le conteneur de stockage fait fonction de lanceur Download PDF

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Publication number
EP0448898A1
EP0448898A1 EP90500028A EP90500028A EP0448898A1 EP 0448898 A1 EP0448898 A1 EP 0448898A1 EP 90500028 A EP90500028 A EP 90500028A EP 90500028 A EP90500028 A EP 90500028A EP 0448898 A1 EP0448898 A1 EP 0448898A1
Authority
EP
European Patent Office
Prior art keywords
firing
rocket
firing device
missile
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.)
Ceased
Application number
EP90500028A
Other languages
German (de)
English (en)
Inventor
Rafael Gamez Perez
Leoncio Munoz Bueno
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.)
Instalaza SA
Original Assignee
Instalaza SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Instalaza SA filed Critical Instalaza SA
Priority to EP90500028A priority Critical patent/EP0448898A1/fr
Publication of EP0448898A1 publication Critical patent/EP0448898A1/fr
Ceased legal-status Critical Current

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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
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
    • F41A19/06—Mechanical firing mechanisms, e.g. counterrecoil firing, recoil actuated firing mechanisms
    • F41A19/25—Mechanical firing mechanisms, e.g. counterrecoil firing, recoil actuated firing mechanisms having only slidably-mounted striker elements, i.e. percussion or firing pins
    • F41A19/27—Mechanical firing mechanisms, e.g. counterrecoil firing, recoil actuated firing mechanisms having only slidably-mounted striker elements, i.e. percussion or firing pins the percussion or firing pin being movable relative to the breech-block
    • F41A19/29—Mechanical firing mechanisms, e.g. counterrecoil firing, recoil actuated firing mechanisms having only slidably-mounted striker elements, i.e. percussion or firing pins the percussion or firing pin being movable relative to the breech-block propelled by a spring under tension
    • F41A19/39—Cocking or firing mechanisms for other types of guns, e.g. fixed breech-block types, forwardly-slidable barrel types
    • 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
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G1/00—Sighting devices
    • F41G1/06—Rearsights
    • F41G1/16—Adjusting mechanisms therefor; Mountings therefor
    • F41G1/28—Adjusting mechanisms therefor; Mountings therefor wedge; cam; eccentric

Definitions

  • the object of this Patent of Invention application relates to an antitank weapon device, comprising a warhead rocket fired from its actual container, disposable upon firing, fitted with the pertinent front and rear covers, optical sight aiming system, firing mechanism, shoulder rest, grip and carrying harness, the above as a whole making up an autonomous weapon system requiring no other means to be used.
  • the device subject of this Patent of Invention application sets forth a series of improvements and original elements on systems designed for a similar use, yielding a light, easy-to-use object provided with all requisite safety measures, both when stored and during use.
  • the launcher-container, 201, Fig. 1 essentially comprises a cylindrical tube with certain reinforcements constructed with resins reinforced with fibreglass, kevlar, carbon, and so forth, or which can even be metallic, housing the rocket, 910, inside so as to make up a single unit, albeit allowing free flight of the rocket 910 upon firing.
  • the rocket, 910 is attached to the launcher-container, 201, by means of the configuration of the front, 921, and rear, 208, covers, and of the protuberanes, 212, that cross through the launcher-container and fit into the relevant housings provided in the rocket stabilizer, 118.
  • Such protuberances, 212 are held by means of the flange, 205, attach the rocket 910 to the launcher-container, 201, and are sheared upon firing.
  • the front, 921, and rear, 208, covers are positioned such that they contact both ends of the rocket, 910, equally assisting in locking the same when sealed with the launcher-container, 201, by means of the adhesive tapes, 234, that are moreover useful to render the system impervious.
  • the front cover, 921, as shown in figure 2 is fitted with supplements, 215, stacked and held in the necessary number with the protuberances, 216, provided therefor, which allow the front tip of the rocket, 910, to rest on the element 214, thereby absorbing the tolerances established between the rocket's, 910, and the launcher-container's, 201, overall length.
  • the rear cover 208, Fig. 4 being close to the area of the protuberances, 212, determining the position of the rocket, 910, needs no setting elements.
  • the front cover, 921 has been fitted with a housing, 240, filled with a dessicant, 230, such as silica-gel or the like, being in contact with the air inside the launcher-container, and preventing the presence of dampness inside the launcher-container, 201.
  • a dessicant such as silica-gel or the like
  • the inside thereof is provided with supports, 242, that together with the cover, 241, allow the sight, 945, to be housed during system storage and transportation.
  • Both front, 921, and rear, 208, covers have an eight-angled outside section preventing the system from rolling on sloped ground. Both covers must be removed before firing, although in the event of firing being effected with the covers on by oversight, neither the marksman nor the system, obviously barring the two lids, would be damaged.
  • the latter can be replaced by the front fragmentary, 929, fig. 3, and fixed rear, 290, fig. 5, covers.
  • the rocket, 910 is attached to the launcher-container, 201, by means of the protuberances, 212, acting as previously set out, and of the detents, 240, provided in the fixed rear cover, 290, for when the cover, 290, is inserted in the launcher-container, 201, and slightly turned clockwise, the detents, 240, are housed inside the slots of the rocket stabilizer, 118, thereby holding the same.
  • Both the protuberances, 212, and the detents, 240, are sheared upon firing, and the cover, 290, flies off.
  • the fixed rear cover, 290 is provided with a housing, 241, filled with a dessicant, 230.
  • Both covers have an outside eight-angled section allowing the system to be supported vertically and preventing it from rolling horizontally on sloped ground.
  • the fragmentary front cover, 929 is stuck to the launcher-container, 201, and the fixed rear cover, 290, is attached to the launcher-container, 201, by means of the adhesive tape, 234, that together with the toric ring, 239, render the system impervious.
  • the aiming system, 945 is made up by the optical sight, 450, and its fixed support, 460, within the launcher-container, 201, Figs. 6A and 6B.
  • the optical sight, 450 is a double magnification sight and its reticle, 465, is permanently illuminated by a tithrium lamp.
  • Such reticle, 465 is marked and numbered according to the type of warhead used, has two stadimetric curves to calculate distance and prediction marks to the right and left of the curves, in order to aim at targets moving crosswise at speeds of 20 and 40 km/hour, Fig. 6C.
  • the sight, 450 is wholly impervious and can be held in the launcher-container, 201, support, 460, in two different positions right-left by means of dovetails, 464, provided in the screws, 461, and of the elements, 462, and 463. Turning the screws, 461, tightens the launcher-container, 201, support, 460, against the optical sight, 450, fixing the same.
  • the marksman can aim and fire the system resting the same on his right or left shoulder, as he shall see fit, depending on which of the two positions the sight, 450, has been set in.
  • the optical sight, 450 can be placed inside the housing and supports, 242, provided in the front cover, 921, Fig. 2, right until firing is to take place, whereupon it must be placed in the launcher-container, 201, support, 460.
  • the firing mechanism, 930 has been designed so as to provide efficient action to start the firing sequence, that requires no care during storage, cannot be affected by the presence of electromagnetic fields and has no mechanical or electric energy stored whatsoever.
  • Firing sequence commences when the percussion hammer, 312, strikes the starting cap, 331.
  • the percussion hammer, 312 is essentially a rod guided in an opening provided in a fold of the element, 314, in another half-opening provided in yet another fold of the same element and in an aperture existing in the partition of the element, 301, as can be observed in figure 7 E.
  • Such element, 314, is connected to the loading button, 316, by means of the pins, 315.
  • a pennant catch, 306 is held in the safety position, blocking the percussion hammer's, 312, path towards the starting cap, 331.
  • Figure 7 B shows the mechanism when loaded.
  • Such loading involves pressing the button, 318, that makes the loading safety catch, 312, swing, releasing the aforesaid lock on the element 314.
  • pressing the loading button, 316, and releasing the button, 318, the element 314 slides until the loading safety catch, 321, claw holds on to the second cleft in the element, 314, locking the same.
  • the spring, 313, is compressed between the percussion hammer's, 312, collar and the fold provided in the element 314.
  • the percussion hammer's, 312, collar is still cut off by the shape of the trigger, 309, detail B3.
  • firing takes place in this position, on pressing the trigger 309, its lower fold releases the percussion hammer's, 312, collar, detail D2 and the energy stored in the compressed spring, 313, drives the percussion hammer, 312, to fall upon the pennant safety catch, 306, that was still in the safety position and hence prevents firing.
  • the mechanism can be reloaded pressing the button, 318, to direct the loading button, 316, to its rest position and repeat the aforesaid loading process.
  • Figure 7 C shows how the pennant catch, 306, has turned 90° by means of the cock 307.
  • This pennant safety catch 306 can take up two stable positions, safety or firing because of the rocking spring 308 design.
  • the starting cap, 331 when struck by the percussion hammer, 312, detonates and ignites the fast fuse 337 duly confined by the tube 336 so that gunpowder deflagration is almost instantaneously spread to the element 328.
  • the first fuse, 337 ends in such element where a second fuse, 338, starts and, with the confinement provided by the element 127, spreads the fire to the igniter, 122, figure 7 E.
  • Such igniter has a gunpowder charge, 128, that is ignited by the fuse and that in turn starts combustion of the rocket propellant gunpowder.
  • the fuse, 337, and its confinement, 336, are protected from blows or damage by the casing, 327.
  • the element 328 has two plugs, 329, placed after the fuses have been inserted, blocking the openings provided in the element 328.
  • the whole firing mechanism 930 described is housed within its casing formed by the elements 301, 302 and 303, the gasket 304 and the closing partition 305.
  • Such gasket is designed to project outside the trigger, 309, protecting the same from water or dirt as shown in the details of figure 7.
  • This rubber joint 304, and the toric joints 332, 333, 334 and 335 tightly close the firing mechanism 930.
  • the previously described ignition transmission system is also rendered impervious by providing the confinement 336 over the countershapes of the elements 323 and 328 and the bicones 126, that render the confinement 127 in the elements 328 and 122 safe and impervious. All the sealing joints such as the above, toric joints, bicones, plugs 329, and so forth, are assembled duly covered with a silicon or like sealant.
  • the cover 343 over the mechanism has a twofold objective, on the one hand preventing that the firing mechanism 930 be manipulated until the cover, 343, is removed just before firing, and on the other ensuring that if the cover, 343, can be assembled, the firing mechanism 930 is at rest and the pennant safety catch, is in the safety position and prevents the passage of the percussion hammer, 312.
  • the rib 340 prevents the cover from being mounted if the firing mechanism is not at rest.
  • the rib 347 in addition to preventing the cover from being placed if the pennant safety catch, 306, is not in the safety position, prevents displacement of the pennant safety catch, 306, once the cover, 343, has been placed.
  • the cover 343 is attached to the launcher-container by means of the adhesive tape 344, figure 1, and the seal, 345, placed over the adhesive tape, 344, allows us to know whether someone has manipulated the firing mechanism.
  • the latter is fitted with a grip, 250, and a rest for the marksman's shoulder, 240, fig. 8.
  • both the grip, 250, and the shoulder rest, 240 must be folded on the launcher-container, 201, and when firing, both must be placed at right-angles to the launcher-container, 201.
  • the grip essentially comprises its support, 251, and the actual grip, 252, attached to the support by means of the pin, 254.
  • the support's, 251, claws, 253, are useful to set the grip, 252, in the firing position, attained by pulling the same.
  • the shoulder rest, 240 comprises a rest, 242, support, 241, and an adjustment harness, 243.
  • the rest, 242 is joined to the support, 241, by means of the pin, 244.
  • the adjustment harness, 243 useful for fitting to the marksman's shoulder, is joined to the rest, 242, and the support, 241.
  • Pulling the rest, 242 releases the support, 241, claws, 245, that establish the same in the transport position, driving it to a position perpendicular to the launcher-container, i.e., a firing position.
  • Both the grip, 250, and the shoulder rest, 240, can be folded up again pushing them again towards the launcher-container.
  • the system is carried by means of the weapon carrying harness, 922, fig. 1, adjustable by means of its buckle 219.
  • All the aforesaid mechanisms and supports are attached to the outside of the launcher 201, by means of the adhesive tapes 203, 204 and 238, and by the flanges 202, 205 and 237, anchored in the braces 209 and 210, which are drawn by means of their respective screws 235 and 236, fig. 1.
  • the missile or rocket, 910, fig. 9, essentially comprises a hollow charge warhead 912, a rocket motor 913, a connecting ramrod 107, and a fuse 990.
  • the warhead, 912, body holds the explosive, 129, and case thereof, 103, which may be tapered or have any other non-straight-line generatrix revolution shape.
  • the multiplier, 105, and its support, 131, are housed therewithin.
  • the tip of the nose, 102 is provided with a toothed star, 101, whose shape, material and treatment thereof prevent slipping on the target and therefore determine due operation of the warhead even when very small angles are involved.
  • the rocket motor, 913 comprises a propellant 130, with its support, 114, a rocket motor 117 and a stabilizing element, 118, with tip-up fins, 119, that rotate about the pins 121 driven by the springs 120 when the rocket 910 leaves the launcher-container 201.
  • the stabilizing element, 118 also acts as last nozzle, 117, expansion, and is provided with holes, 140, and slots, 141, allowing the rocket, 910, to be attached to the launcher-container, 201, by means of the protuberances 212, or of the slots, 240, provided in the fixed rear cover 290, figs. 1, 4 and 5.
  • Rocket plugging and ignition takes place by means of igniter, 122, as previously described for the firing mechanism.
  • the connecting ramrod, 107 is useful for connecting the warhead, 912, to the rocket motor, 913, and to house the fuse, 990.
  • Such fuse, 990 is an impact fuse whose detonator, 001, is located in a rotor, 002, that holds the detonator, 001, out of line with the rest of the warhead's, 912, pyrotechnical sequence, until the fuse has been loaded.
  • the fuse has a loading time safety contrivance and a three-blade fall safety contrivance.
  • safety contrivances are complemented with the core safety contrivance, elements 109-110 and system spring 111.
  • core safety contrivance blocks the rotor, 002, and prevents loading of the fuse, 990.
  • the spring 111 Upon firing, when the rocket missile 910 leaves the launcher-container 201, the spring 111, ejects the elements 109 and 110 outside the connecting ramrod housing 107 as a whole, and the rotor, 002, is released, thereby allowing the fuse, 990, to be loaded.
  • the fuse, 990 is enveloped by a mass, 133, whose pointer, 132, strikes the percussion hammer, 003, when the rocket falls upon the target.
  • the device is essentially an antitank weapon and a hollow charge warhead rocket has been described, the patent does not restrict the type of warhead to be used, that could be of the hollow charge antitank, hollow charge antitank and antipersonnel, smoke and fire, inert warhead for instruction purposes, and so forth.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Toys (AREA)
EP90500028A 1990-03-23 1990-03-23 Dispositif pour tirer une roquette, dans lequel le conteneur de stockage fait fonction de lanceur Ceased EP0448898A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP90500028A EP0448898A1 (fr) 1990-03-23 1990-03-23 Dispositif pour tirer une roquette, dans lequel le conteneur de stockage fait fonction de lanceur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP90500028A EP0448898A1 (fr) 1990-03-23 1990-03-23 Dispositif pour tirer une roquette, dans lequel le conteneur de stockage fait fonction de lanceur

Publications (1)

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EP0448898A1 true EP0448898A1 (fr) 1991-10-02

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EP90500028A Ceased EP0448898A1 (fr) 1990-03-23 1990-03-23 Dispositif pour tirer une roquette, dans lequel le conteneur de stockage fait fonction de lanceur

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2060489A2 (es) * 1991-11-28 1994-11-16 Instalaza Sa Sistema de arma de combate.
CN107776458A (zh) * 2017-09-29 2018-03-09 北京航天发射技术研究所 一种起竖保温舱及其密封防雨方法
RU2732562C1 (ru) * 2019-12-09 2020-09-21 Российская Федерация в лице Министерства обороны РФ Механизм стопорения передней крышки контейнера

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE530433A (fr) *
FR499103A (fr) * 1917-06-30 1920-01-31 Norton Byers Taylor Obus de rupture
CH342501A (fr) * 1957-02-18 1959-11-15 Brevets Aero Mecaniques Fusée d'ogive à percuteur pour projectile explosif
US2916141A (en) * 1955-08-19 1959-12-08 Emmanuel Kaye Means for the storage of goods
FR1328459A (fr) * 1962-04-18 1963-05-31 Soc Tech De Rech Ind Roquette à propulseur largable
FR1436333A (fr) * 1965-05-22 1966-04-22 Contraves Ag Caisson de transport pour petites roquettes
BE664669A (fr) * 1965-05-31 1966-09-16
DE1428642A1 (de) * 1964-12-28 1968-11-28 Dynamit Nobel Ag Befestigung von Raketen in ihrer Abschussvorrichtung
GB1206945A (en) * 1966-09-23 1970-09-30 British Aircraft Corp Ltd Launchers for missiles
FR95452E (fr) * 1954-10-22 1971-01-15 Soc Tech De Rech Ind Perfectionnements aux projectiles a réaction.
FR2100377A5 (fr) * 1970-07-10 1972-03-17 Sarmac Sa
EP0022756A2 (fr) * 1979-07-06 1981-01-21 Förenade Fabriksverken Couvre-bouche pour armes à feu tubulaires
GB2086013A (en) * 1980-10-14 1982-05-06 Serat Weapon system

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE530433A (fr) *
FR499103A (fr) * 1917-06-30 1920-01-31 Norton Byers Taylor Obus de rupture
FR95452E (fr) * 1954-10-22 1971-01-15 Soc Tech De Rech Ind Perfectionnements aux projectiles a réaction.
US2916141A (en) * 1955-08-19 1959-12-08 Emmanuel Kaye Means for the storage of goods
CH342501A (fr) * 1957-02-18 1959-11-15 Brevets Aero Mecaniques Fusée d'ogive à percuteur pour projectile explosif
FR1328459A (fr) * 1962-04-18 1963-05-31 Soc Tech De Rech Ind Roquette à propulseur largable
DE1428642A1 (de) * 1964-12-28 1968-11-28 Dynamit Nobel Ag Befestigung von Raketen in ihrer Abschussvorrichtung
FR1436333A (fr) * 1965-05-22 1966-04-22 Contraves Ag Caisson de transport pour petites roquettes
BE664669A (fr) * 1965-05-31 1966-09-16
GB1206945A (en) * 1966-09-23 1970-09-30 British Aircraft Corp Ltd Launchers for missiles
FR2100377A5 (fr) * 1970-07-10 1972-03-17 Sarmac Sa
EP0022756A2 (fr) * 1979-07-06 1981-01-21 Förenade Fabriksverken Couvre-bouche pour armes à feu tubulaires
GB2086013A (en) * 1980-10-14 1982-05-06 Serat Weapon system

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2060489A2 (es) * 1991-11-28 1994-11-16 Instalaza Sa Sistema de arma de combate.
CN107776458A (zh) * 2017-09-29 2018-03-09 北京航天发射技术研究所 一种起竖保温舱及其密封防雨方法
CN107776458B (zh) * 2017-09-29 2020-03-03 北京航天发射技术研究所 一种起竖保温舱及其密封防雨方法
RU2732562C1 (ru) * 2019-12-09 2020-09-21 Российская Федерация в лице Министерства обороны РФ Механизм стопорения передней крышки контейнера

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