УСТРОЙСТВО ДЛЯ УДЕРЖАНИЯ МИНОМЕТНОГО СНАРЯДА В СТВОЛЕ МИНОМЕТА И СПОСОБ ЕГО КРЕПЛЕНИЯ К СНАРЯДУ

FIELD: weaponry. SUBSTANCE: the device has a bearing assembly with an edge and a trigger mechanism. The bearing assembly is fastened on the front edge of the plane of the projectile tail fin by means of one or several connecting members. The connecting members have a preset deformable point providing for separation of the projectile from the device at a shot. The method for fastening of the device to the projectile for its holding in the grenade launcher barrel consists in installation of the device on the tail fin of the grenade launcher projectile, fastening of the device on the front edge at least of one plane of the projectile tail fin by means at least of one connecting member installed between the bearing assembly and the front edge the tail fin plane. EFFECT: enhanced reliability of projectile fastening in the barrel of the grenade launcher and reduced negative influence of the device on the aerodynamics of the projectile at its launch. 10 cl, 5 dwg ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß (19) RU (11) 2 282 136 (13) C2 (51) ÌÏÊ F42B 30/10 (2006.01) F41F 3/052 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2004133665/02, 26.06.2003 (72) Àâòîð(û): ÊÓÐÓ Ìàóðè (FI), ÌÀÊÊÎÍÅÍ Àðè (FI) (24) Äàòà íà÷àëà îòñ÷åòà ñðîêà äåéñòâè ïàòåíòà: 26.06.2003 (73) Ïàòåíòîîáëàäàòåëü(è): ÏÀÒÐÈÀ ÂÀÌÌÀÑ ÎÓ (FI) R U (30) Êîíâåíöèîííûé ïðèîðèòåò: 27.06.2002 FI 20021263 (43) Äàòà ïóáëèêàöèè çà âêè: 20.08.2005 (45) Îïóáëèêîâàíî: 20.08.2006 Áþë. ¹ 23 2 2 8 2 1 3 6 (56) Ñïèñîê äîêóìåíòîâ, öèòèðîâàííûõ â îò÷åòå î ïîèñêå: RU 2178138 Ñ2, 10.01.2002. US 5503080 À, 02.04.1996. DE 3918005 À1, 05.04.1990. GB 2251290 À, 01.07.1992. (85) Äàòà ïåðåâîäà çà âêè PCT íà íàöèîíàëüíóþ ôàçó: 27.01.2005 2 2 8 2 1 3 6 R U (87) Ïóáëèêàöè PCT: WO 2004/003454 (08.01.2004) C 2 C 2 (86) Çà âêà PCT: FI 2003/000519 (26.06.2003) Àäðåñ äë ïåðåïèñêè: 119146, Ìîñêâà, à/ 33, ÈíòåðÏàò, ïàò.ïîâ. È.Â.Æóðàâëåâîé (54) ÓÑÒÐÎÉÑÒÂÎ ÄËß ÓÄÅÐÆÀÍÈß ...

УСТРОЙСТВО ДЛЯ УДЕРЖАНИЯ СНАРЯДА В СТВОЛЕ ОРУДИЯ И ОПОРНЫЙ УЗЕЛ

Изобретение относится к устройству для удержания снаряда (2) в стволе (1) орудия, заряжаемого с казенной части, и опорному узлу для удержания снаряда. Устройство содержит опорный элемент (5), с которым закрепляющий элемент соединен с помощью резьбового соединения. Зажимной элемент в виде втулки размещен вокруг закрепляющего элемента. На элементе выполнены пазы для стабилизаторов хвостового оперения снаряда (2). Опорный элемент (5) содержит закрепляющий элемент, с которым он скреплен с помощью резьбового соединения и сверху которого размещен зажимной элемент в виде втулки. Повышается безопасность функционирования миномета. 2 н. и 18 з.п. ф-лы, 6 ил.

УСТРОЙСТВО ДЛЯ УДЕРЖАНИЯ МИНОМЕТНОГО СНАРЯДА В СТВОЛЕ ОРУДИЯ, ЗАРЯЖАЕМОГО С КАЗЕННОЙ ЧАСТИ

Изобретение относится к устройству для удержания минометного снаряда в стволе (2) орудия, заряжаемого с казенной части. Устройство содержит опорный узел (6), снабженный бортовой кромкой (7), закрепленный на хвостовом оперении минометного снаряда (1), соединяющий элемент (8) между опорным узлом и хвостовым оперением минометного снаряда. Соединяющий элемент выполнен с возможностью соединения минометного снаряда и соединяющего элемента с хвостовым оперением минометного снаряда путем механического соединения. В соединении с соединяющим элементом (8) размещен участок, который деформируется при выстреле, позволяя минометному снаряду (1) отделиться от опорного узла (6), и спусковой механизм (17) для поджига основного капсюля (10) минометного снаряда. Механическое соединение между соединяющим элементом (8) и опорным узлом (6) образовано с помощью штифтового соединения 14. Повышается надежность удержания снаряда. 8 з.п. ф-лы, 3 ил.

МЕХАНИЗМ УДЕРЖАНИЯ РАКЕТЫ В ПУСКОВОМ КОНТЕЙНЕРЕ

Изобретение относится к области вооружения. Механизм удержания ракеты в пусковом контейнере включает резьбовое кольцо, фиксирующее его в пусковом контейнере посредством упорной втулки, заслонку, контактирующую свободным концом с задней крышкой контейнера, и пружинное кольцо с радиальными пазами и уступами по месту разъема, устанавливаемое на ракетном двигателе между задним торцем контейнера и выступающей из него торцевой поверхностью. Упорная втулка выполнена в виде кольцевой опоры с радиальными прорезями на торце, в которых шарнирно закреплена верхняя часть заслонки. Уступы разрезного пружинного кольца размещены внутри паза с зазором относительно его боковых стенок, а его внутренний диаметр выполнен из условия обеспечения взаимодействия с дном паза. При использовании изобретения обеспечивается возможность использования механизма удержания ракеты в пусковом контейнере в ракетах с различными типами соплового блока двигателя. 4 ил.

УСТРОЙСТВО ДЛЯ УДЕРЖАНИЯ МИНОМЕТНОГО СНАРЯДА В СТВОЛЕ ОРУДИЯ, ЗАРЯЖАЕМОГО С КАЗЕННОЙ ЧАСТИ

... 1. Устройство для удержания снаряда (1) в стволе орудия (2), заряжаемого с казенной части, содержащее опорный узел (6), снабженный кромкой фланца (7), и закрепленный на хвостовом оперении снаряда (1), причем опорный узел (6) выполнен для удержания снаряда на месте в стволе орудия до выстрела, устройство также содержит соединяющий элемент (8) между опорным узлом и хвостовым оперением минометного снаряда, при этом опорный узел закреплен с помощью механического соединения на хвостовом оперении снаряда с помощью соединяющего элемента (8); участок, который деформируется в момент выстрела и служит для отделения минометного снаряда (1) от опорного узла (6); и спусковой механизм (17) для поджига основного капсюля (10) минометного снаряда, отличающееся тем, что механическое соединение между соединяющим элементом (8) и опорным узлом (6) образовано с помощью штифтового соединения 14. ! 2. Устройство по п.1, отличающееся тем, что штифтовое соединение 14 образовано с помощью штифта 14а. ! 3. Устройство ...

УСТРОЙСТВО ДЛЯ УДЕРЖАНИЯ СНАРЯДА В СТВОЛЕ ОРУДИЯ И ОПОРНЫЙ УЗЕЛ

... 1. Устройство для удержания снаряда в стволе орудия, заряжаемого с казенной части, содержащее опорный узел (5), который закреплен на хвостовом оперении (4) снаряда, включающий опорный элемент (8) с бортовой кромкой (8а), средство для закрепления опорного элемента (8) на хвостовом оперении (4) снаряда, и спусковой механизм в опорном элементе (8) для поджига основного капсюля снаряда для его выстрела, отличающееся тем, что средство для закрепления опорного элемента (8) на хвостовом оперении (4) снаряда содержит закрепляющий элемент (6) в виде втулки, имеющий пазы для стабилизаторов хвостового оперения (4) указанного снаряда, а между пазами зажимы (6а), размещаемые на трубке хвостового оперения (4) снаряда, при этом внешние поверхности зажимов отклонены наружу, по крайней мере, до конца зажимов (6а), закрепляющий элемент (6) и опорный элемент (8) имеют одинаковую резьбу с тем, чтобы при взаимном вращении относительно друг друга их взаимное положение изменялось вдоль оси, зажимной элемент ( ...

Verfahren zur Erhoehung der Treffsicherheit von Raketen oder raketenaehnlichen Geschossen

VORRICHTUNG ZUM VERRIEGELN UND AUSWERFEN VON FLUGKOERPER ENTHALTENDEN BEHAELTERN

VORRICHTUNG ZUM LOESBAREN VERRIEGELN EINES RAKETENGETRIEBENEN FLUGKOERPERS

Einrichtung zur Halterung von Raketen in ihrer Abschussvorrichtung

Apparatus for storing and firing rocket bombs from aircraft

... 935,898. Launching rockets from aircraft. R. A. ROBERT, and P. P. MATGE. Dec. 24, 1959 [Dec. 31, 1958], No. 41205/61. Divided out of 935,897. Class 9 (2). In apparatus for suspending and launching rockets from aircraft as described in Specification 935,897, the tubes 27 housing the rockets are located and supported in a casing 30 by means of spaced transverse partitions, each partition comprising two spaced metal walls 24, 25. The cavity between the walls is filled with a foam material 26 such as a hardened polyurethane composition. Components of the electrical circuits for firing the rockets are embedded in the foam filling.

Rocket launcher latch mechanism

... 924,074. Rocket launchers. MINISTER OF AVIATION. Sept. 14, 1961 [June 14, 1960], No. 20832/60. Classes 9 (2) and 92. A rocket launcher latch comprises a spigot 14 with limbs 20, a pivotable part 12 with a lug 23 and detent 28, and depending lugs 30 attached to which is a channelled plate 31. The spigot 14 is held within a bush 15 of launcher plate 13 by a screw 16 (see Fig. 2). The pivotable part 12 is acted upon to rotate about a pin 24 in a clockwise direction by a rat-trap type spring 27, movement being limited by V shaping as at 21. The rocket is placed in the launcher so that its rear face bears on lugs 30, thereby moving part 12 anticlockwise until detent 28 enters a peripheral groove 34 of the rocket. The electrical connections for firing the rocket are firstly via detent 28, insulated from part 12 by bushing 29, and insulated annular contacts within groove 34 to an insulated contact 35 and secondly via a spring 37 and the latch itself to the launcher plate 13. On firing, the efflux ...

ASSEMBLY COMPRISING A SELF-PROPELLED PROJECTILE AND ITS CASE

1329489 Self-propelled projectile and launching tube therefor SARMAC SA 29 June 1971 [10 July 1970] 30473/71 Headings F3A and F3C An assembly comprises, in one embodiment, a self-propelled, finned projectile 1 Fig. 1, locked in a combined container and launching tube 3 by means of a cap 14 which pushes the fins 9 outwardly so that projections 11 engage in slots 12 in the container wall. When the projectile is fired, the propellant gases readily expel the cap 14 and a closure 5 thereby allowing the fins to move inwardly and release the projectile. In another embodiment, Fig. 12, locking is provided by a resilient ring 32 which is expelled along with the cap 14 and closure 5. In a further embodiment, Fig. 15, the fins 9 are folded forwardly and locking is provided by spring leaves 36. In yet another embodiment, Fig. 17, locking is provided by parts 42. Slots 44 in these parts engage rivets on the fins 9 and allow the parts to fall away in flight. Spring leaves can be used to similar effect (Fig. 16, not shown). In a still further embodiment (Figs. 19 and 20, not shown) the projectile fins are folded laterally around the Venturi. Various modifications are shown in the remaining Figures.

Percussion mechanism for rocket or other projectile launching weapons

... 832,436. Firing mechanisms for rocket launchers. ANSTALT FUR DIE ENTWICKLUNG VON ERFINDUNGEN UND GEWERBLICHEN ANWENDUNGEN ENERGA. Dec. 9, 1957 [Jan. 18, 1957], No. 38252/57. Class 92 The firing mechanism of a rocket launching weapon comprises a striker 16 on a hammer 15 pivoted at 22 and swung rearwardly after firing by the propulsive gases of the rocket against the action of a percussion spring 26, the hammer being held in the cocked position by a cocking sear 17 and a safety sear 18. A lock 20 pivoted at 40 has a latch portion 21 projecting into the barrel for securing the rocket in the barrel and is urged into this position by a spring 46. Withdrawal of the lock 20 from the barrel is effected either manually or automatically, on firing, by the hammer as shown in Fig. 5 or by the introduction of a rocket into the barrel, the arrangement being such that withdrawal of the lock brings the safety sear 18 into its active position. By operating a lever F the safety sear 18 is moved into inactive ...

ARRANGEMENT TO THE SUPPORT OF A MORTAR PROJECTILE IN THE COURSE OF A WEAPON AND A PROCEDURE FOR THE ATTACHMENT OF A SUPPORTING MEMBER AT A MORTAR PROJECTILE

In a launcher tube arranged holding device for rockets

Mechanism for the mounting plate of a rocket provided with guidance wings

Device for the attachment of a projectile in a housing

ASSEMBLY COMPRISING A SELF-PROPELLED FINNED PROJECTILE AND ITS CASE

Projectile automoteur et son tube de lancement.

Arme de lancement pour projectiles autopropulsés.

Arme de lancement pour projectiles autopropulsés.

Mécanisme de percussion pour arme de lancement.

Arme de lancement pour projectiles autopropulsés.

Engin de combat équipé d'au moins une fusée suspendue

Arme pour le lancement d'un projectile autopropulsé et projectile pour cette arme.

Mécanisme de percussion

Arme pour le lancement de projectiles autopropulsés

Abschussvorrichtung für Raketengeschosse an Flugzeugen

Abschussvorrichtung für Raketengeschosse

Dispositif de lancement de fusée

Raketengeschoss mit Abschussvorrichtung für dasselbe.

Installation lance-roquettes à tubes de lancement

Abschussvorrichtung für Geschosse, z.b. Raketengeschosse

Starteinrichtung für rückstossgetriebene Flugkörper

An einer Startvorrichtung aufgehängte Rakete

Abschussvorrichtung mit einem Satz von Raketengeschossen

Vorrichtung zum Haltern eines raketengetriebenen Geschosses auf einer Startplattform

Ensemble comprenant au moins une roquette et un élément de support auquel cette roquette est suspendue

Behälter mit einem Geschoss

Lösbare Verriegelungsvorrichtung zum Sichern von in Raketenwerfern aufgehängten Raketen

Einrichtung zur Befestigung einer Rakete in einem Behälter

Vorrichtung zum Einstellen der Schussweite einer Rakete in einer Abschussvorrichtung

Aus der Hand abfeuerbares Abschussgerät für Raketen

Raketenwerfer mit mindestens einem Abschussrohr

VORRICHTUNG ZUM FESTHALTEN VON RAKETEN IN EINER ABSCHUSSVORRICHTUNG.

Ensemble comprenant un projectile empenné autopropulsé et son arme de lancement

Haltevorrichtung für eine Rakete in einem Abschussrohr

Kupplungsglied zum Verbinden eines Flugkörpers mit einer Abschuss- und Lenkeinrichtung

Roquette destinée à êntre incorporée dans une grappe de roquettes montée sur un engin de lancement

Vorrichtung zum Festhalten und Zünden eines Raketengeschosses in der Ladekammer eines Magazin-Raketenwerfers

Automatische Feuerwaffe mit Mitteln zur Steuerung der Munitionszufuhr

Vorrichtung zum Festhalten einer Rakete in einem Abschussrohr

Vorrichtung zum Festhalten einer Rakete in einem Abschussrohr

Ensemble comprenant une arme d'infanterie et sa munition

Betätigungsvorrichtung, insbesondere zur Auslösung eines Zündgenerators

Haltevorrichtung für Raketen in einem Abschussrohr

Vorrichtung zur Verriegelung eines mindestens einen Flugkörper beinhaltenden Behälters mit einer Abschusseinrichtung

Ensemble comprenant un projectile autopropulsé empenné et son étui

Clamp holding rocket in launching barrel - has locking lever releasing clamp by rocket gas stream force

The rocket is held in its launching barrel by a spring loaded holder. This holder is rotated from clamping position into releasing position. The holder prevents rocket moving forwards or backwards within the barrel. The holding device rests against a stop in the clamping position. A locking lever (20) with the stop (22) is moved into releasing position when the rocket (25) is launched. This ensures that the holding device (8) is held in clamping position as long as the locking lever (20) is in its blocking position. The locking lever (20) projects into the gas stream of the rocket (25). The force of this stream actuates the locking lever.

BANDAGE DEVICE TO CONNECT COMPARTMENTS

DEVICE FOR BUTTING DISCONNECTING UNITS AND COMPARTMENTS

СТЕНД ДЛЯ ОГНЕВЫХ И ЛЕТНЫХ ИСПЫТАНИЙ РАКЕТ

Стенд для огневых и летных испытаний твердотопливных ракет включает фундамент и поворотные направляющие с установленной на них ракетой. На ракете установлены два разъединяемых бандажа, один возле сопла твердотопливного двигателя, второй в районе центра масс с закрепленными на бандажах бугелями, которые перемещаются по направляющим и монтированными на фундаменте в районе первого бандажа через поворотный шарнир, а в районе второго бандажа - через перестанавливаемую стойку фиксирующую ракету в поднятом положении. На первом бандаже с помощью пиротехнического элемента закреплен упор, который контактирует через тензодатчик с кронштейном поворотного шарнира, который взаимодействует с соответствующим узлом фундамента.

INTALLATION DE TELECOMMANDE POUR UN DISPOSITIF DE RETENUE DE TUBES LANCE-ENGINS

INSTALLATION DE TELECOMMANDE POUR UN DISPOSITIF DE RETENUE DE TUBES LANCE-ENGINS MONTES SUR UN BLINDE. POUR LES TUBES LANCE-ENGINS 2, 3, IL EST PREVU DES PATTES DE SERRAGE 4, 7 ACTIONNEES HYDRAULIQUEMENT ET AUXQUELLES SONT ASSOCIES DES CYLINDRES 13, 14, 15, 16 A UN VERIN 12 ACTIONNE PAR UN LEVIER 11.

IMPROVEMENTS WITH THE ROCKET LAUNCHERS

Improvements with the machines missiles

Material of shooting for motorized projectiles

Improvements brought to the means for the launching of self-propelled projectiles, in particular of projectiles with reaction

Patent FR2183842B1

HYDRAULIC CYLINDER AND PISTON LOCK

LOW-SHOCK SEPARATION DEVICE

The present invention relates to a low-shock separation device including a housing (10) having an upper end and a lower end opened and a housing space (11) formed therein, a cylinder (20) coupled to an upper end of the housing (10) and having an upper hole (25) and a lower hole (27) communicating with the upper hole (25) and having a cross section wider than the upper hole (25), a piston (40) having an insertion groove (41) formed in the lower hole (27) of the cylinder (20) and opening toward the lower end of the housing (10), a pressure cartridge (50) partially inserted into the upper hole (25) of the cylinder (20) to shield the upper end of the upper hole (25), a bolt (60) inserted into the lower hole (27) through the lower end of the housing (10) to shield the lower end of the lower hole (27), and a shock absorber ring (70) disposed between the bolt (60) and the piston (40) and compressed and deformed when the piston (40) moves in the direction of the bolt (60) due to a high pressure ...

DEVICE FOR LOCKING AND RELEASING MISSILE

본 발명은 미사일을 운용중에는 확실하게 구속하면서도 발사시에는 신속하고 확실하게 구속해제토록 한 미사일 구속 및 해제 장치에 관한 것으로, 미사일의 후단부에 돌출형성된 한쌍의 구속돌기와, 발사관의 내주면에 고정설치되며 상기 구속돌기가 삽입되는 구속홈이 미사일의 진행방향을 향하게 형성된 한쌍의 고정부재와, 이들 각 고정부재의 구속홈을 미사일 진행방향으로 관통하여 상기 구속돌기의 중심에 형성된 구속나사공에 체결되어 미사일을 진행방향으로 구속하는 구속나사와, 상기 고정부재에 회동가능하게 결합되며 미사일의 노즐 중심을 향해 연장되어 미사일의 추력에 의하여 후방으로 회동되는 해제용 회동부재와, 이 회동부재에 후단부가 고정결합되어 상기 구속나사의 움직임을 구속하는 구속핀으로 구성된다. 이러한 구조에 의하여 미사일은 구속돌기와 구속홈에 의하여 반경방향 및 후방으로의 유동이 구속되고 구속나사와 구속핀에 의하여 미사일 진행방향으로 구속되어 운용중에는 미사일을 유동없이 확실하게 구속할 수 있다. 한편, 발사시에는 구속핀이 고정된 회동부재가 미사일의 추력에 의하여 구속나사로부터 이탈되고 구속나사가 고정부재로부터 이탈되어 미사일의 구속해제가 신속하고 확실하게 이루어지게 되어 발사시 발사대의 충격 및 진동이 방지되고 발사 안정성이 높고 발사 오차가 최소화되는 것이다. The present invention relates to a missile restraint and release device that allows the missile to be restrained quickly and surely during launch while being firmly restrained during operation. The pair of restraint protrusions protruding from the rear end of the missile are fixed to the inner circumferential surface of the launch tube. A pair of fastening members into which the constraining projections are inserted is formed in a direction of the missile, and the constraining grooves of each of the fixing members are fastened to a constraining screw hole formed at the center of the constraining projection by passing through the constraining grooves in the missile traveling direction. A constrained screw that constrains in the forward direction, a pivoting member that is rotatably coupled to the fixing member, extending toward the nozzle center of the missile, and pivoting backward by the thrust of the missile; and a rear end fixedly coupled to the pivoting member. It is composed of a restraint pin to restrain the movement of the restraint screw. With this structure, the missile is constrained in the radial and rearward direction by the constraining protrusion and the constraining groove, and is constrained in the missile progression direction by the constraining screw and the constraining pin, so that the missile can be ...

Self-contained canister missile launcher with tubular exhaust uptake ducts

A self-contained missile canister (10) includes a cylindrical shell (12) having a plenum or manifold at the breech end for receiving and deflecting missile exhaust gases. A plurality of tubular exhaust ducts (36) or uptake tubes route exhaust gases from the plenum to locations near the missile exit end of the canister. Protrusions on the missile, such as guide rails or aerodynamic control fins, extend from the missile body at locations lying between the exhaust ducts. The tubular exhaust ducts resist the exhaust pressure in hoop tension, so are lightweight. Ablative material may line the exhaust ducts. The exhaust ducts may be supported by longitudinally disposed support beams, preferably I-beams. In one embodiment, each I-beam supports two exhaust ducts.

DEVICE AND METHOD FOR CURBING MISSILE

PROBLEM TO BE SOLVED: To provide a method and device for curbing a missile that has compact and thin structure, and can be installed in narrow space. SOLUTION: The curbing device is composed of a curbing latch 7 that is engaged to a hook 4 of a missile 3, a main restriction lever 9 that is engaged to the curbing latch 7, and a shear pin 10 that passes through the restriction latch 7. In this case, the curbing latch 7 is directly fixed by the main curbing lever 9 and the shear pin 10, thus allowing the missile 3 to be subjected to main and sub curbing by the main curbing lever 9 and the shear pin 10, respectively. When the missile 3 is to be fired, the main curbing lever 9 is released from the curbing latch 7, and the curbing latch 7 is rotated by the fire motion of the missile 3 for shearing the shear pin 10. COPYRIGHT: (C)2001,JPO ...

ОПОРНЫЙ УЗЕЛ ДЛЯ УДЕРЖАНИЯ СНАРЯДА В СТВОЛЕ ОРУДИЯ, ЗАРЯЖАЕМОГО С КАЗЕННОЙ ЧАСТИ, И СПОСОБ ЕГО КРЕПЛЕНИЯ

Изобретения относятся к опорному узлу (6) для удержания снаряда (1) в стволе орудия, заряжаемого с казенной части орудия и способу его крепления. Опорный узел (6) содержит опорный элемент (8) с бортовой кромкой (7) и спусковой механизм для поджига основного капсюля минометного снаряда (1), а также содержит соединяющее средство (10) для закрепления соединяющего элемента (8) на хвостовом оперении (4) минометного снаряда (1). Соединяющее средство (10) для закрепления опорного элемента (8) на хвостовом оперении (4) минометного снаряда (1) содержит, по крайней мере, одну упругую деталь (13, 20, 30), выполненную для закрепления на хвостовом оперении (4) минометного снаряда (1) с помощью упругих усилий. Повышается надежность удержания снаряда. 2 н. и 4 з.п. ф-лы, 7 ил.

СТОПОРНОЕ УСТРОЙСТВО НАПРАВЛЯЮЩЕЙ РАКЕТНОЙ ПУСКОВОЙ УСТАНОВКИ

Изобретение относится к области ракетной техники и может быть использовано при создании противоградовых ракетных комплексов. Сущность изобретения заключается в том, что стопорное устройство направляющей ракетной пусковой установки содержит размещенные на срезе казенной части направляющей и боковой поверхности соплового блока ракеты стопорные элементы. Первый стопорный элемент содержит передний и задний упоры, между которыми образован сквозной канал, куда заключен стопорный палец, размещенный на боковой поверхности соплового блока ракеты. Стопорный палец фиксирует ракету в канале направляющей и срезается передним упором при пуске ракеты. Реализация изобретения позволяет упростить конструкцию стопорного устройства, снизить трудозатраты при его эксплуатации, а также повысить надежность и эффективность работы. 2 з. п. ф-лы, 5 ил.

ЭЛЕКТРОМЕХАНИЧЕСКОЕ СТОПОРНОЕ УСТРОЙСТВО РЕАКТИВНЫХ СНАРЯДОВ

Изобретение относится к устройствам, обеспечивающим эффективную работу боевых машин реактивных систем залпового огня. Электромеханическое стопорное устройство реактивных снарядов включает два пластинчатых стопора, соединенных между собой регулировочным болтом с гайками. На корпусе казенной части трубы направляющей слева и справа от пластинчатых стопоров размещают дополнительно два электромагнита, подпружиненные сердечники которых блокируют пластинчатые стопора в исходном состоянии, препятствуя их разжатию штифтом реактивного снаряда. Команду на утапливание сердечников и освобождение пластинчатых стопоров при достижении реактивным снарядом необходимого стартового усилия на электромагниты подают от бортовой сети с датчика, измеряющего это усилие, который размещают на одном из пластинчатых стопоров. Повышается эффективность боевого применения боевых машин реактивных систем залпового огня. 1 ил.

УСТАНОВКА ДЛЯ СТАРТА МОДЕЛИ РАКЕТЫ

Изобретение относится к области малой ракетной техники. Установка для старта модели ракеты содержит стартовый стол, к которому прикреплен направляющий стержень с поршнем на конце. На поршень надета стартовая труба с посадочным местом под модель. Стартовая труба с установленной моделью ракеты и поршнем образуют замкнутую надпоршневую полость. На стержень навита нить, выполняющая функции демпфирующего устройства при взаимодействии с дном-ограничителем перемещения трубы по стержню. Посадочное место стартовой трубы соответствует внутреннему диаметру соплового блока модели. Направляющий стержень выполнен полым и сообщен с надпоршневой полостью каналом. Стартовая труба соединена со стартовым столом разрывными тарированными элементами. Изобретение позволяет увеличить стартовую скорость модели ракеты при уменьшении нагрузки на стартовую трубу. 3 з.п.ф-лы, 1 ил.

УСТРОЙСТВО ДЛЯ УДЕРЖАНИЯ МИНОМЕТНОГО СНАРЯДА В СТВОЛЕ МИНОМЕТА И СПОСОБ ЕГО КРЕПЛЕНИЯ К СНАРЯДУ

... 1. Устройство для удержания минометного снаряда в стволе миномета, заряжаемого с казенной части орудия, содержащее опорный узел с бортовой кромкой и спусковым механизмом для инициирования основного капсюля минометного снаряда, по крайней мере, один соединительный элемент для крепления опорного узла к, по крайней мере, одной плоскости стабилизатора на хвостовой части минометного снаряда, при этом соединительный элемент выполнен в виде, по крайней мере, одного продольного стержня, размещенного, по существу, вдоль минометного снаряда, один конец которого крепится к опорному узлу, а другой конец стержня соединительного элемента включает удерживающую часть, поперечную к продольной оси минометного снаряда, для установки соединительного элемента на передней кромке хвостового оперения, соединительный элемент содержит, по крайней мере, одну заранее заданную деформируемую точку, позволяющую минометному снаряду отделяться от опорного узла при выстреле. 2. Устройство по п.1, в котором соединительный ...

Vorrichtung zum Lagern eines Flugkörpers in einem Abschussrohr

Transport safety device in rocket launcher - involves locking bolt engaging in start tube recess

The rocket fits into a start tube (1) for launching, and in an area surrounded by the start tube is at least one radially movable locking component (11). In the start tube is at least one recess (12) in which the locking component can engage. The locking arrangement (14) works with a spring (18) so that the point (13) of the locking component (11) stands outwards over the periphery of the rocket. When the rocket is introduced into the start tube, the locking component together with its point is pushed backwards. The locking arrangement (14) has a pyrotechnical power component (19) which, when initiated, causes the point of the locking component to be drawn in so far that the engagement of the locking component in the recess of the start tube is nullified. The locking component (11) is a bolt, and the recess (12) in which it engages is a radial hole. USE/ADVANTAGE - To improve the fixture of a military rocket in its launching or start tube.

Improvements in suspension devices for releasably holding the rear ends of rockets

... 769,139. Suspending and launching rockets from aircraft. BREVETS AERO-MECANIQUES SOC. ANON. May 3, 1955 [May 20, 1954], No. 12830/55. Class 9 (2). Rockets 4 are suspended beneath an aircraft wing 1 by means of slidable tail units 3 and 'holding devices P carried by a retractable support 5 and provided with locking means adapted to be released by the thrust of the propellant gases. The device P, Fig. 3, comprises pivoted jaws 6 engaging the flared end of the rocket and carrying transverse pins 8 engaged (in hooks 9 'to lock the jaws. The hooks 9 extend from a slidable member 10 held by a spring 11. The jaws 6 are pivoted on a sleeve 12 slidable in an extension 5a of the support 5, resilient means 13. eg. Belleville washers, being arranged around the sleeve 12 to urge it -rearwardly in the tube 5a. Within sleeve 12 is a tubular rotatable element 15 carried by a control lever 16 and having a finger 17 engaged in a helical groove in the hub of member 10. On the lever 16 is a cam 19 which closes ...

An improved safety device for securing a torpedo in a torpedo tube

581,880. Torpedo tubes. PAINE, H. SCOTT-, and GWILLIAM, V. C. E. MARTEN-. June 7, 1939, No. 16745. [Class 9 (ii)] A torpedo 11 is held in the launching tube 10 by a spring-urged stop-pin 16 movable in a transverse guide in a casing 13 mounted on the tube. Slidably mounted in the longitudinal part of the casing 13 is a plate 18 passing through a slot 17 in the stop-pin and having a cam-slot 30, 31, 32 co-operating with a pin 29 secured between the two limbs of the stop-pin. When loading the tube, the stop-pin is operated by means of a hand-lever 25. The plate 18 forms a link in a Bowden-wire connection between the firing lever and the firing mechanism of the torpedo tube, and the portion 31 of the cam-slot ensures that the stop-pin is withdrawn before the firing mechanism is released. The part 30 of the cam-slot ensures that the firing mechanism cannot be actuated if the stop-pin has been manually withdrawn by means of the lever 25. The mechanism may be used in conjunction with the combined mechanical and electrical firing arrangement described in Specification 581,881.

Holding device for a rocket in a launcher tube

ROCKET LAUNCHER

ARRANGEMENT FOR SUPPORTING A MORTAR SHELL INTO BARREL OF WEAPON AND A METHOD FOR ATTACHING A SUPPORT MEMBER TO A MORTAR SHELL

Arrangement for supporting shell into breech-loading weapon barrel

The invention relates to an arrangement for supporting a shell into the barrel of a breech-loading weapon. The arrangement comprises a support piece (6) that is provided with an edge flange (7) and is to be fastened to a tail of the shell. The support piece further comprises a firing mechanism for firing the actual primer of the shell. The arrangement further comprises a connecting means (8) between the support piece (6) and the shell tail (4), the connecting means being arranged to fasten to the shell and to the support piece (6) and thus to fasten the support piece with a mechanical connection to the shell tail (4). The connecting means (8) comprises at least one shank part (9) having a first end and a second end, the first end of the shank part being arranged to fasten to the connecting means (8) and the second end to the shell tail (4). The fastening between the first end of the shank part and the shell is arranged to yield in a firing situation, thus enabling the detachment of the ...

ASSEMBLY COMPRISING A SELF-PROPELLED FINNED PROJECTILE AND ITS CASE

DETENT AND FIRING MECHANISM FOR AN OPEN BREECH HIGH RATE AUTOMATIC ORCKET LAUNCHER

DISPOSITIF DE MISE EN PLACE ET DE FIXATION D'UN CONTENEUR POUR MISSILE SUR SON AFFUT

ROCKET RETENTION AND IGNITION ASSEMBLY

Mobile missile launch system and method thereof

The present invention relates to launching system, more particularly relates to mobile launching system for missiles. The mobile missile launch system comprising a vehicle ( 14 ) having a chassis structure adapted to carry the launch system; a mounting frame ( 16 ) comprising predetermined truss framework mounted onto the chassis structure; plurality of sliding mechanisms mounted at rear end of the mounting frame ( 16 ); plurality of canisters ( 43 ) mounted onto said beam ( 22 ) and plurality of missiles ( 11 ) ensconced within the canisters ( 43 ); plurality of containers ( 42 ) enclosing said canisters ( 43 ) and are connected to the saddles ( 32, 34 ) for linear movement; plurality of resting units ( 27 ) abutting to rear end of the canisters ( 43 ) and are adapted to move linearly to transfer reaction forces from said missiles ( 11 ) to ground.

Light Trigger

A firearm has a trigger shield configured as a protective loop surrounding a first and second switch of the firearm. Each switch actuates the function of the firearm when activated by a finger to start the firing process. The first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop. Further, the firearm has an emitter mounted on the trigger shield that propagates a light beam to a receiver mounted on an opposite side of the trigger shield. When a finger depresses one of the switches, his/her finger is blocking the light beam and the firearm will not activate and when the finger is moved away from the light beam, the firearm discharges.

Light Trigger

A firearm has a trigger shield configured as a protective loop surrounding a first and a second switch of the firearm, each switch actuates the function of the firearm when activated by a finger to start the firing process, and the first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop. The firearm has at least three receivers on the protective loop and at least three beam windows on the protective loop aligned with the three receivers. Further, the firearm has an emitter outside of the protective loop, the emitter propagates a beam of light to a beam splitter, and the beam splitter propagates three beams of light one beam to each of the three beam windows, the three beams of light are incident on one of the respective receivers. Also, when a finger activates one of the switches, the firearm activates, and when the finger breaks one of the beams of light, the firearm discharges. 1. A firearm , comprising:a trigger shield configured as a protective loop surrounding a first and a second switch of the firearm, each switch configured to actuate the function of the firearm when activated by a finger to start or stop the firing process, the first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop;at least three receivers on the protective loop; an emitter outside of the protective loop, the emitter configured to propagate a beam of light to a beam splitter, and the beam splitter propagates three fire beams of light, one fire beam to each of the three beam windows, the three beams of light incident on one of the respective receivers;', 'wherein when a finger activates one of the switches, the firearm activates, and when the finger breaks one of the fire beams of light, the firearm discharges., 'at least three beam windows on the protective loop aligned with the three receivers;'}2. The firearm of claim 1 , wherein the finger moves to block or ...

Light Trigger

A firearm has an emitter that propagates a light beam to a receiver and at least two finger position beams that propagate horizontally along the firearm on either side of a switch that provides detection of a position of a finger when the finger blocks and unblocks the finger position beam. Further, when only one finger position beam is blocked, this indicates improper positioning of the finger placing the firearm into a non-dischargeable condition. 1. A firearm , comprising:an emitter that propagates a light beam to a receiver;at least two finger position beams that propagate along the firearm on either side of a switch that provides detection of a position of a finger when the finger blocks and unblocks the finger position beam;wherein when only one finger position beam is blocked, this indicates improper positioning of the finger placing the firearm into a non-dischargeable condition.2. The firearm of claim 1 , wherein the finger moves to block or unblock the light beam by flexion or extension.3. The firearm of claim 1 , wherein the trigger is mounted on a shield.4. The firearm of claim 1 , wherein the emitter is in alignment with the receiver and a beam emitted from the emitter is incident upon the receiver.5. The firearm of claim 1 , wherein the shield may vary in shape claim 1 , vertical or horizontal orientation claim 1 , width claim 1 , and slope.6. The firearm of claim 1 , wherein the trigger comprises one or more of a shield claim 1 , a switch claim 1 , an emitter claim 1 , and a receiver. This application claims priority to and is a divisional of U.S. Pat. No. 10/962,320 entitled Light Trigger and filed on December , , which is incorporated herein by reference in its entirety.An optical firearm trigger is disclosed, revealing means and methods of initiating discharge of a firearm without the use of a mechanical trigger. In this manner the grip of the firearm will not change due to the mechanical loading required to pull the trigger further alleviating the ...

Light Trigger

A firearm has a trigger shield that is a protective loop surrounding a first and second switch of the firearm and the switches actuate the function of the firearm when activated by a finger to start the firing process. The first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop. The protective loop is vertically aligned having the first and second switches on respective shorter sides of the protective loop. The firearm further has a first emitter mounted on the trigger shield that propagates a first light beam to a first receiver mounted on an opposite side of the trigger shield and a second emitter mounted on the trigger shield that propagates a second light beam to a second receiver mounted on an opposite side of the trigger shield. When a finger depresses one of the switches, his/her finger is blocking the light beam and the firearm will not activate and when the finger is moved away from the light beam, the firearm discharges. 1. A firearm , comprising:a trigger shield configured as a protective loop surrounding a first, second, third, and fourth switch of the firearm, the switches configured to actuate the function of the firearm when activated by a finger to start the firing process, the first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop, the protective loop is vertically aligned having the first and second switches on respective shorter sides of the protective loop, the third switch is on a third side and the fourth switch is on a fourth side of the protective loop and the third and fourth switches are on the longer sides of the protective loop;a first emitter mounted on the trigger shield that propagates a first light beam to a first receiver mounted on an opposite side of the trigger shield;a second emitter mounted on the trigger shield that propagates a second light beam to a second receiver mounted on an opposite side of the ...

333Light Trigger

A firearm has a trigger shield configured as a protective loop surrounding at least one switch and the at least one switch actuates the function of the firearm when activated by a finger to start the firing process. The firearm further has at least one receiver, at least one position beam emanating horizontally that determines a position of a finger by the finger blocking or not blocking the position beam, and at least one emitter that propagates a beam of light, the beam of light incident on the at least one receiver. Further, when a finger activates the switch, the firearm activates, and when the finger breaks the beam of light, the firearm discharges.

LOW-SHOCK SEPARATION DEVICE

A low-shock separation device is characterized in that an internal locking structure is unlocked and a bolt is separated by operating a specific part of components thereof using high pressure that is generated by combustion of powder. 1. A low-shock separation device comprising:a housing having open top and bottom and an internal receiving space;a cylinder disposed in the receiving space through the top of the housing and having a top hole and a bottom hole communicating with the top hole and larger in cross-sectional area than the top hole;a housing cap fitted in a space between the housing and the cylinder and closing the top of the housing;a piston disposed in the bottom hole of the cylinder;a pressure cartridge partially inserted in the top hole and closing an upper end of the top hole; anda bolt partially inserted in the bottom hole through the bottom of the housing, closing a lower end of the bottom hole, and kept in the bottom hole by a holder,wherein a passage attenuating a collision between the cylinder and the housing cap is formed by filling a space between the cylinder and the housing cap with high pressure gas, and the passage is formed when the cylinder is moved toward the pressure cartridge by high pressure that is generated when the pressure cartridge is operated.2. The device of claim 1 , wherein the passage has a first passage formed around a side of the cylinder and a second passage having a first end communicating with the top hole of the cylinder and a second end extending from a top to a side of the piston to communicate with the first passage of the cylinder.3. The device of claim 2 , wherein the first passage is formed at a position where the first passage can communicate with the second passage when the cylinder is moved.4. The device of claim 1 , comprising a deformable portion formed on the housing cap claim 1 , restricting movement of the cylinder before the pressure cartridge is operated claim 1 , and primarily absorbing shock by ...

Light Trigger

A firearm has a trigger shield configured as a protective loop surrounding a first and second switch of the firearm. Each switch actuates the function of the firearm when activated by a finger to start the firing process. The first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop. Further, the firearm has an emitter mounted on the trigger shield that propagates a light beam to a receiver mounted on an opposite side of the trigger shield. When a finger depresses one of the switches, his/her finger is blocking the light beam and the firearm will not activate and when the finger is moved away from the light beam, the firearm discharges.

WEAPON TUBE AND PARTICULARLY TORPEDO TUBE STRUCTURE

Disclosed is a weapon tube and particularly a torpedo tube structure including a system for holding the weapon in a storage position in the tube, including a clamping mechanism which is connected to the structure and can be moved by an actuator between a closed position for locking an interface part of the weapon in order to lock the weapon in position in the structure and an open position for releasing the interface part and therefore the weapon, the structure includes an elastic unit for soliciting the clamping mechanism in the closed position. 123145662134. A weapon tube , including a weapon () holding system () in the storage position in the tube () , including a clamping mechanism () connected to the structure and movable by actuating means () , between a closed position for blocking an interface part () of the weapon in order to block the latter in position , and an open position for releasing this interface part () and therefore the weapon () , comprising elastic means () for stressing the clamping mechanism () in the closed position.249139. The structure according to claim 1 , wherein the clamping mechanism () includes a closing cylinder () of the clamp and wherein the elastic means () are associated with this cylinder () to push it into the closed position of the mechanism.3139. The structure according to claim 2 , wherein the elastic means comprise a helical spring () placed behind the cylinder () to push the latter.410. The structure according to claim 1 , wherein the actuating means comprise an unlocking lever () that can be manipulated by an operator.5911124. The structure according to claim 2 , wherein the closing cylinder () is associated with a withdrawal chamber () and is connected (at ) to the expulsion of the tube to guarantee the opening of the clamping mechanism () during firing of the weapon.6624. The structure according to claim 1 , wherein the interface part () of the weapon () includes a member fastened thereon and provided with a spherical ...

MUNITIONS INTERFACE ADAPTER

A munitions interface adapter including a rail adapter body. A plurality of mounting shoes may be coupled to the rail adapter body, and configured to mechanically couple the rail adapter body to a munitions rail of an installed munitions interface. A fire control connector may be configured to communicatively couple with an installed munitions fire control system. An adapter control interface may be included for adapting fire control signals from the installed munitions fire control system to an adapted munitions fire control signals. One or more adapted munitions deployment fixtures may be positioned on the rail adapter body. The one or more adapted munitions deployment fixtures are configured to retain and deploy one or more adapted munitions. 1. A munitions interface adapter comprising:a rail adapter body;a plurality of mounting shoes coupled to the rail adapter body, and configured to mechanically couple the rail adapter body to a munitions rail of an installed munitions interface;a fire control connector configured to communicatively couple with an installed munitions fire control system;an adapter control interface for adapting fire control signals from the installed munitions fire control system to an adapted munitions fire control signals; andone or more adapted munitions deployment fixtures positioned on the rail adapter body, the one or more adapted munitions deployment fixtures configured to retain and deploy one or more adapted munitions.2. The munitions interface adapter according to claim 1 , wherein the installed munitions interface includes an AGM-114 guided missile interface.3. The munitions interface adapter according to claim 2 , wherein the installed munitions interface includes one or more of ah M299 launcher and an M310 launcher.4. The munitions interface adapter according to claim 1 , wherein the plurality of mounting shoes are configured to slidingly receive the rail adapter body on a rail system of the installed munitions interface.51. The ...

Mobile rocket launcher and method of rocket launcher

FIELD: engines and pumps. SUBSTANCE: system of a mobile launcher comprises a vehicle (14) with a chassis, adapted for transportation of the launcher; a positioning frame (16), representing a strutted-truss structure, installed on the vehicle chassis; several sliding mechanisms installed in the rear section of the positioning frame (16); several containers (43) with enclosed rockets (11), installed on a girder structure (22); several containers (42), which contain the specified containers (43) and which are connected with the seat-shaped location beds (32, 34) for realisation of linear displacement; several start supports (27), adjacent to the rear ends of the containers (43) and arranged with the possibility of linear displacement for transfer of reactive forces from rockets (11) onto earth. EFFECT: mobility of a start complex, rapidity of its deployment, reduced hazard of complex detection. 18 cl, 25 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 493 529 (13) C2 (51) МПК F41A F41A F41F F41F 23/34 23/42 3/04 3/052 (2006.01) (2006.01) (2006.01) (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2011138716/11, 11.01.2010 (24) Дата начала отсчета срока действия патента: 11.01.2010 2 4 9 3 5 2 9 (56) Список документов, цитированных в отчете о поиске: EP 1710530 A2, 11.10.2006. WO 9917989 A1, 15.04.1999. GB 2096287 A, 13.10.1982. US 3924511 A, 09.12.1975. JP 9210595 A, 12.08.1997. FR 2531200 A1, 03.02.1984. RU 2343390 C1, 10.01.2009. RU 2092400 C1, 10.10.1997. (73) Патентообладатель(и): ДИРЕКТОР ДЖЕНЕРАЛ, ДИФЕНС РИСЁЧ ЭНД ДЕВЕЛОПМЕНТ ОРГАНИЗЕЙШЕН (IN) C 2 C 2 (45) Опубликовано: 20.09.2013 Бюл. № 26 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 31.10.2011 (86) Заявка PCT: IN 2010/000018 (11.01.2010) (87) Публикация заявки РСТ: WO 2010/113171 (07.10.2010) Адрес для переписки: 197101, Санкт-Петербург, а/я 128, "АРСПАТЕНТ", пат. пов. М.В. Хмаре, рег.№ 771 R U (54) МОБИЛЬНАЯ РАКЕТНАЯ ПУСКОВАЯ УСТАНОВКА ...

Non electric explosive bolt and separating apparatus for projectile using the same

The present invention relates to a non-electrical ignition device which comprises a main charge portion for explosion located therein, a bolt body member with a threaded portion on the outer circumferential surface, and a plurality of flame holes positioned on the other end side of the bolt body member to allow the flame in a launch tube to flow inside, so as to be exploded by the flame flowing inside through the plurality of flame holes, to secure the economic feasibility because of the simple manufacturing process and the low manufacturing cost compared to the existing electric explosive bolt, thereby preventing accidental shootings caused by short circuits of electric cables, stably firing the projectile, and allowing the projectile to accurately hit a target.

Locking device

本发明涉及一种锁紧装置，该装置包括底座、螺杆、传动螺母和传动拉杆，底座为倒置的桶状结构，底座的上半部外周壁上均匀间隔设有多个限位槽，限位槽与底座的内腔连通，限位槽内铰接有锁紧组件，螺杆沿底座的轴线方向转动安装在底座的内顶壁，传动螺母旋装在螺杆上，传动拉杆的数量与限位槽的数量相对应，传动拉杆的一端与传动螺母的侧壁铰接，传动拉杆的另一端延伸至相应限位槽并铰接在对应的锁紧组件的中部。本发明结构简单、操作准确性高、锁紧可靠，适于各种具有支撑脚形式的设备配合使用。

Device for keeping of rocket projectile in rocket launcher barrel

FIELD: artillery armament. SUBSTANCE: the device for keeping of rocket projectile in the barrel of the rocket launcher loaded from the breech has a bearing assembly with an edge installed on the projectile tail section. The bearing assembly is provided with an ignition member for initiation of the main primer and fastened to the tail section through a connecting member destructed at a shot. EFFECT: enhanced reliability of keeping of projectile in the rocket launcher barrel irrespective of the position of the barrel proper. 7 cl, 4 dwg ЗЕ ЕЗАЕС ПЧ с» (19) РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ ВИ” 2 178 138 (51) МПК” (13) С2 Е 42 В 30/10, 14/00 (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 99118308/02, 23.01.1998 (24) Дата начала действия патента: 23.01.1998 (30) Приоритет: 24.01.1997 ЕН] 970313 (43) Дата публикации заявки: 20.06.2001 (46) Дата публикации: 10.01.2002 (56) Ссылки: Ч$ 5503080, 02.04.1996. СВ 2251290 А, 02.07.1992. ОЕ 3918005 АД, 05.04.1990. РСТ М/О 93/017439, 15.04.1993. (85) Дата перевода заявки РСТ на национальную фазу: 24.08.1999 (86) Заявка РСТ: Е! 98/00064 (23.01.1998) (87) Публикация РСТ: \/О 98/33018 (30.07.1998) (71) Заявитель: ПАТРИА ВАММАС ОУ (Е) (72) Изобретатель: ТОЙВОНЕН Веса (Е), РЕУНАМЯКЕ Кари (ЕП), ЛЕХТИМЯКИ Мартти ([1) (73) Патентообладатель: ПАТРИА ВАММАС ОУ (Е!) (74) Патентный поверенный: Журавлева Ирина Владимировна (54) УСТРОЙСТВО ДЛЯ УДЕРЖАНИЯ МИНОМЕТНОГО СНАРЯДА В СТВОЛЕ МИНОМЕТА (57) Изобретение относится к артиллерийскому вооружению. Устройство для удержания снаряда в стволе миномета, заряжаемого с казенной части, содержит установленный на хвостовой части снаряда опорный узел с бортовой кромкой. Опорный узел снабжен запальным элементом для инициирования основного капсюля и прикреплен к хвостовой части снаряда через соединительный элемент, разрушающийся при выстреле. Изобретение обеспечивает надежное удержание снаряда в стволе миномета независимо от положения самого ствола. 6 3. п. ф-Лы, ...

Launcher missile fixing universal module

FIELD: weapons and ammunition. SUBSTANCE: invention relates to ammunition holding devices (missiles), and is a launcher missile fixing universal module (LMFUM). The LMFUM in the launcher consists of a metal housing made of two identical halves pivotally connected with each other through a shaft in the bracket and fixed by a locking device. A drive system is mounted inside the housing. The drive system transmits the motion from the handle located on the housing on four clamps having movable legs that allow to hold different diameter missiles in the launcher. The clamps are put forward from the housing to the diameter of a stacked missile, corresponding to the guide line of the clamp sleeve. EFFECT: interchangeable of fixation means of various diameter missiles in the launcher. 5 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 613 205 C2 (51) МПК F41F 3/052 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ 2015130126, 21.07.2015 (24) Дата начала отсчета срока действия патента: 21.07.2015 15.03.2017 Приоритет(ы): (22) Дата подачи заявки: 21.07.2015 (43) Дата публикации заявки: 30.01.2017 Бюл. № 4 (54) УНИВЕРСАЛЬНЫЙ МОДУЛЬ ФИКСАЦИИ РАКЕТ В ПУСКОВОЙ УСТАНОВКЕ R U (57) Формула изобретения Универсальный модуль фиксации ракет в пусковой установке, состоящий из металлического корпуса, отличающийся тем, что в корпусе, выполненном из двух идентичных половин, шарнирно связанных между собой через ось в кронштейне и фиксируемых запорным устройством, установлена система приводов, передающая движение с рукоятки, расположенной на корпусе, на четыре фиксатора, имеющих подвижные лапки, которые выдвигаются из корпуса до диаметра устанавливаемой ракеты, соответствующего риске на втулке фиксатора. Стр.: 1 C 2 C 2 Адрес для переписки: 460005, г. Оренбург, ул. Шевченко, 26, Филиал АО "Военно-промышленной корпорации "Научно-производственное объединения машиностроения" - Конструкторское бюро "Орион", ...

Umbilical Connector with Dual Face Separation

본 발명은 발사장치와 발사체를 연결하되, 보호덮개를 장착한 상태에서 발사 또는 사출 후 보호덮개를 바로 분리해야 하는 경우에 사용되는 2단 분리형 배꼽 연결기에 관한 것으로서, 보호덮개(120)가 구비된 발사체(100)의 전원부와 상기 발사체(100)를 발사하는 발사관(110)의 전원부를 연결하도록 상기 발사체(100)와 발사관(110) 사이에 설치된 배꼽 연결기에 있어서, 상기 보호덮개(120)에 설치되며 양측에 각각 수용홈(22)(23)이 구비된 리셉터클(20)과; 상기 발사체(100)에 설치되고 상기 리셉터클(20)의 제1 수용홈(22)에 수용되어 상기 발사체(100)와 보호덮개(120)를 전원 연결하며, 미는 힘에 의해 상기 리셉터클(20)에 체결되고 당기는 힘에 의해 상기 리셉터클(20)로부터 분리되는 푸시 풀(Push-Pull) 방식의 P-P 플러그(10)와; 상기 발사관(110)에 설치되고 상기 리셉터클(20)의 제2 수용홈(23)에 수용되어 상기 보호덮개(120)와 발사관(110)을 전원 연결하며, 회전에 의해 상기 리셉터클(20)에 체결되고 당기는 힘에 의해 상기 리셉터클(20)로부터 분리되는 트위스트 풀(Twist-Pull) 방식의 T-P 플러그(30);를 포함하는 것을 특징으로 한다. 이에 따라 발사 또는 사출시에 한번 분리가 이루어지고 그 이후에 다시 한번 분리가 이루어지는 2단 분리가 가능하면서도 발사체를 보호하는 보호덮개가 차지하는 공간을 최소화할 수 있게 됨은 물론 진동 환경에서의 구조적 안정성과 안정적인 체결 성능을 확보할 수 있고 조립성이 양호하게 된다. The present invention relates to a two-stage detachable belly connector used to connect the launch device and the projectile, but when the protective cover is to be removed immediately after launching or injection in a state where the protective cover is mounted, In the navel connector provided between the projectile 100 and the projectile 110 to connect the power supply of the projectile 100 with a protective cover 120 and the power supply of the projectile 110 to launch the projectile 100, A receptacle 20 installed on the protective cover 120 and provided with receiving grooves 22 and 23 at both sides thereof; Installed in the projectile 100 and received in the first receiving groove 22 of the receptacle 20 to connect the projectile 100 and the protective cover 120 to the power source, and to the receptacle 20 by a pushing force. A push-pull PP plug 10 separated from the receptacle 20 by a fastening and pulling force; Installed in the launch tube 110 and received in the second receiving groove 23 of the receptacle 20 connects the protective cover 120 and the launch tube 110 to the power supply, and fastened to the receptacle 20 by rotation And a TP plug 30 of a twist-pull type separated from ...

UNIVERSAL ROCKET FIXING MODULE IN THE RUNNER

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2015 130 126 A (51) МПК F41F 3/052 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2015130126, 21.07.2015 Приоритет(ы): (22) Дата подачи заявки: 21.07.2015 (43) Дата публикации заявки: 30.01.2017 Бюл. № 04 (72) Автор(ы): Захаров Максим Геннадьевич (RU), Белов Илья Александрович (RU) A R U A 2 0 1 5 1 3 0 1 2 6 (57) Формула изобретения Универсальный модуль фиксации ракет в пусковой установке, состоящий из металлического корпуса, отличающийся тем, что в корпусе, выполненном из двух идентичных половин, шарнирно связанных между собой через ось в кронштейне и фиксируемых запорным устройством, установлена система приводов, передающая движение с рукоятки, расположенной на корпусе, на четыре фиксатора, имеющие подвижные лапки, которые выдвигаются из корпуса до диаметра устанавливаемой ракеты, соответствующего риске на втулке фиксатора. 2 0 1 5 1 3 0 1 2 6 (54) УНИВЕРСАЛЬНЫЙ МОДУЛЬ ФИКСАЦИИ РАКЕТ В ПУСКОВОЙ УСТАНОВКЕ R U Адрес для переписки: 460005, г. Оренбург, ул. Шевченко, 26, Филиал АО "Военно-промышленной корпорации "Научно-производственное объединения машиностроения" - Конструкторское бюро "Орион", начальнику КБ "Орион" А.Д. Горбачёву (71) Заявитель(и): Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" (RU) Стр.: 1

Open-type propulsion device for rapid launching interceptor of active hard-kill system

본 발명은 능동파괴체계의 대응탄의 발사를 위한 개방형 추진장치에 사용되는 점화기에 있어서 점화 약통 내의 점화제의 연소 속도를 빠르게 하여 시간 지연 없이 화염을 방출시킬 수 있도록 함으로써 대응탄의 급속 발사를 도모할 수 있는 개방형 추진장치를 제공한다. 본 발명에 따른 개방형 추진장치용 점화기는 탄자(20)가 장전되는 발사관(30), 탄자(20) 후미에 충전된 추진제, 추진제를 연소하기 위한 점화기(40) 및 탄자(20)가 발사되기 전에는 발사관(30) 후방이 밀폐되어 있다가 탄자(20) 발사 시 추진제 연소 가스에 의해 발사관(30) 후방이 개방되도록 발사관(30) 후단부에 장착된 파열판(60)을 포함하는, 능동파괴체계의 대응탄의 급속 발사를 위한 개방형 추진장치에 있어서, 점화기(40)는 점화기 몸체; 점화기 몸체와 결합되어 내부에 점화제가 충전된 점화 약통; 점화기 몸체(41)의 내부에 배치되어 전기신호에 의해 점화제(45)를 착화하기 위한 착화기(43); 착화기(43)의 후단으로부터 점화 약통(42) 내부를 향하여 점화기(40)의 길이방향을 따라 설치되어, 100∼9000m/s의 연소속도를 갖고 화약(44b, 44e)을 포함하는 점화 도선(44); 을 포함하는 것을 특징으로 한다. In the igniter used in the open propulsion system for the firing of a counterpart of an active destruction system, the present invention promotes rapid firing of a counterpart by allowing a flame to be released without time delay by increasing the combustion speed of the ignition agent in the ignition container. Provides an open propulsion device that can The igniter for the open propulsion device according to the present invention is a launching tube 30 to which the tanza 20 is loaded, a propellant charged to the rear of the tanza 20, the igniter 40 for burning the propellant and the launching tube 20 before the launching of the tanza 20. Corresponding to the active destruction system, which includes a rupture plate (60) mounted at the rear end of the launch tube (30) such that the rear is sealed and the rear of the launch tube (30) is opened by the propellant combustion gas when the bullet (20) is fired. In the open propulsion device for rapid firing of the bullet, the igniter 40, the igniter body; An ignition cylinder coupled to the igniter body and filled with an ignition agent therein; An igniter 43 disposed inside the igniter body 41 to ignite the igniter 45 by an electrical signal; An ignition lead provided along the longitudinal direction of the igniter 40 from the rear end of the igniter 43 toward the inside of the ignition chamber 42 and having the ...

GUIDELINES FOR LAUNCHING ROCKETS

ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß (19) RU (11) 2004 126 064 (13) A (51) ÌÏÊ F41F 3/042 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÇÀßÂÊÀ ÍÀ ÈÇÎÁÐÅÒÅÍÈÅ (21), (22) Çà âêà: 2004126064/02, 25.08.2004 (43) Äàòà ïóáëèêàöèè çà âêè: 20.02.2006 Áþë. ¹ 5 (72) Àâòîð(û): Êóçíåöîâ Âëàäèìèð Ìàðêîâè÷ (RU), Æóêîâ Âëàäèìèð Ïåòðîâè÷ (RU), ×åðíóøêèí Âàëåðèé Âàñèëüåâè÷ (RU), Àáèäàðîâ Âèêòîð Âàñèëüåâè÷ (RU), Ñåõèí  ÷åñëàâ Àëåêñååâè÷ (RU) A R U A 2 0 0 4 1 2 6 0 6 4 Ôîðìóëà èçîáðåòåíè Íàïðàâë þùåå óñòðîéñòâî äë çàïóñêà ðàêåòû, ñîäåðæàùåå êîðïóñ â âèäå òðóáû, óñòðîéñòâî çàêðóòêè ðàêåòû ïî êðåíó, óãëóáëåíèå â âèäå íèøè íà âíóòðåííåé ïîâåðõíîñòè òðóáû, îïîðû, êîíñîëüíî çàêðåïëåííûå íà êîðïóñå ðàêåòû â âèäå ïëàñòèí÷àòûõ ïðóæèí, êîíòàêòèðóþùèõ ñ âíóòðåííåé ïîâåðõíîñòüþ òðóáû, îòëè÷àþùååñ òåì, ÷òî ïåðåäíèå êðîìêè ïëàñòèí÷àòûõ ïðóæèí âûïîëíåíû ñî ñêîñîì â ñòîðîíó çàäíåé êðîìêè è ñî ñêðóãëåíèåì ïî âñåé äëèíå, ïðè ýòîì íà ñâîáîäíûõ êîíöàõ ïðóæèí âûïîëíåíû ðàäèàëüíûå îòãèáû â ñòîðîíó êîðïóñà ðàêåòû, à ïî ïåðèìåòðó íèøè ñî ñòîðîíû âíóòðåííåé ïîâåðõíîñòè òðóáû âûïîëíåíû óñòóïû, çàïîëíåííûå óïðóãèì ìàòåðèàëîì. Ñòðàíèöà: 1 RU 2 0 0 4 1 2 6 0 6 4 (54) ÍÀÏÐÀÂËßÞÙÅÅ ÓÑÒÐÎÉÑÒÂÎ ÄËß ÇÀÏÓÑÊÀ ÐÀÊÅÒÛ R U Àäðåñ äë ïåðåïèñêè: 300001, ã.Òóëà, Ùåãëîâñêà çàñåêà, ÃÓÏ "Êîíñòðóêòîðñêîå áþðî ïðèáîðîñòðîåíè " (71) Çà âèòåëü(è): Ãîñóäàðñòâåííîå óíèòàðíîå ïðåäïðè òèå "Êîíñòðóêòîðñêîå áþðî ïðèáîðîñòðîåíè " (RU)

Hydraulic horizonality control method of launch platform

본 발명은 수평 제어장치에 관한 것으로 특히 차량 및 발사 플랫폼의 수평을 제어하기 위한 유압식 수평제어장치로서, 유압 동력을 발생하는 유압 동력장치와; 발사 플랫폼의 전방, 중앙, 후방의 양 측면에 장착되어 발사 플랫폼을 지지 및 이동시키는 지지잭과; 상기 지지잭에 대응되도록 위치하여, 상기 지지잭의 작동상태 판단 및 지지잭의 움직임을 제어하는 지지잭용 유압다지관과; 상기 발사 플랫폼의 전방 및 후방에 장착되어 전방 및 후방측의 기울기 상태를 출력하는 전방 및 후방 울기센서 상자와; 상기 두 기울기센서 상자에서 출력되는 신호를 근거로 발사 플랫폼의 기울기 및 변형상태를 예측하고, 상기 지지잭용 유압다지관을 제어하여 각 지지잭의 수평제어를 수행하는 주 제어기;를 포함한다. The present invention relates to a horizontal control device, in particular a hydraulic horizontal control device for controlling the horizontal level of the vehicle and the launch platform, the hydraulic power unit for generating hydraulic power; A support jack mounted at both front, center, and rear sides of the launch platform to support and move the launch platform; A hydraulic jack for the support jack, positioned to correspond to the support jack, for controlling the operation of the support jack and the movement of the support jack; Front and rear crying sensor boxes mounted on the front and rear of the launching platform to output inclination states of the front and rear sides; It includes a main controller for predicting the inclination and deformation state of the launch platform based on the signals output from the two inclination sensor box, and controls the hydraulic jack for the support jack to perform horizontal control of each support jack.

Locking device of a self-propelled projectile inside its launch box

Rocket holding device

UNLOCKABLE CONNECTION DEVICE BETWEEN TWO OBJECTS FOR USE IN PARTICULAR IN THE SPACE FIELD.

La liaison déverrouillable entre deux objets tels qu'un satellite (10) et un engin spatial (12) est assurée par un dispositif qui comprend une liaison à clef rotative (60). Le déverrouillage de cette liaison est assuré par la rotation d'une bague (54) portant la clef (60). Cette rotation est elle-même induite par le déplacement axial d'une tige (44) portant la bague (54), commandé par un ressort (50). Ce ressort est libéré par un système initiateur (86), pyrotechnique ou autre.

Missile retainer for launch tube

The retainer has two circular section projections on the rear of the missile. Two support tongues (21,22) are fixed to the internal surface of the launch tube and positions in two retaining grooves corresponding to the projections extending in a predetermined direction. A first retaining throat (23) is of circular section and the other (24) has an axis of elongation extending radially. The radial size of the throat is greater than the diameter of the respective projection while the perpendicular size is equal to the diameter.

Mechanism used to retain rockets in their launching device until they are fired

Patent FR2088692A5

Rocket projectile and launching device for it

SHOOTING DEVICE FOR RECURRENT DEFENSE MUNITION

L'invention a pour objet un dispositif de tir (1) pour une munition (2) de défense rapprochée, munition comportant un étui rigide (6) renfermant au moins un projectile (7), étui solidaire d'un culot (8) solidarisable par un moyen de liaison à une embase (3) du dispositif de tir comportant des moyens de mise à feu de la munition. Ce dispositif (1) est caractérisé en ce qu'il comporte un tube (10) coiffant la munition (2) après fixation de cette dernière sur l'embase (3), tube pouvant être lui-même rendu solidaire de l'embase par un moyen d'attache (11), tube portant par ailleurs un bipied (15) articulé permettant l'orientation en site du dispositif (1). The invention relates to a firing device (1) for an ammunition (2) for close defense, ammunition comprising a rigid case (6) containing at least one projectile (7), case integral with a base (8) solidarisable by means of connection to a base (3) of the firing device comprising firing means of the ammunition. This device (1) is characterized in that it comprises a tube (10) covering the munition (2) after attachment of the latter to the base (3), which tube can itself be secured to the base by an attachment means (11), the tube further bearing an articulated bipod (15) allowing the orientation of the device (1) in elevation.

DEVICE FOR MECHANICAL AND ELECTRIC COUPLING FOR LOADS, PARTICULARLY MILITARY

L'INVENTION CONCERNE UN DISPOSITIF D'ACCOUPLEMENT MECANIQUE ET ELECTRIQUE POUR CHAGES, NOTAMMENT MILITAIRES. UN TEL ACCOUPLEMENT EST CONSTITUE PAR LA COMBINAISON DE MOYENS D'ACCROCHAGE, DE CALAGE ET DE LIAISON ELECTRIQUE AGENCES DE TELLE SORTE QUE LE VERROUILLAGE DES MOYENS D'ACCROCHAGE ENTRAINE SIMULTANEMENT ET AUTOMATIQUEMENT SANS QU'IL SOIT BESOIN DE FAIRE APPEL A DES OPERATIONS DE REGLAGE, LE CALAGE DANS TOUTES LES POSITIONS DE LA CHARGE PORTEE PAR RAPPORT A LA CHARGE PORTEUSE AINSI QUE LEUR LIAISON ELECTRIQUE. UNE PLURALITE DE CHARGES PEUVENT AINSI ETRE RENDUES SOLIDAIRES LES UNES DES AUTRES EN VUE DE LEUR EMPORT SOUS UN AERONEF ET ETRE ENSUITE EJECTEES UNE PAR UNE EN COMMENCANT PAR CELLE QUI EST LA PLUS ELOIGNEE DE CET AERONEF. L'INVENTION S'APPLIQUE AU LARGAGE DE PROJECTILES EN CHAPELET. THE INVENTION CONCERNS A MECHANICAL AND ELECTRICAL COUPLING DEVICE FOR CHAGES, IN PARTICULAR MILITARY. SUCH A COUPLING IS CONSTITUTED BY THE COMBINATION OF HITCHING, SHIMMING AND ELECTRICAL CONNECTION MEANS SUCH AS THE LOCKING OF THE HITCHING MEANS DRIVES SIMULTANEOUSLY AND AUTOMATICALLY WITHOUT THE NEED FOR ADJUSTMENT OF OPERATIONS , TIMING IN ALL POSITIONS OF THE CARRIED LOAD IN RELATION TO THE CARRIER LOAD AS WELL AS THEIR ELECTRICAL LINK. A PLURALITY OF LOADS CAN THUS BE MADE IN PART OF ONE OF THE OTHERS WITH A VIEW OF THEIR CARRIAGE UNDER AN AIRCRAFT AND THEN BE EJECTED ONE BY ONE STARTING WITH THE ONE THAT IS FAREST FROM THIS AIRCRAFT. THE INVENTION IS APPLIED TO THE RELEASE OF ROSARY PROJECTILES.

Device for ensuring electrical connection in weapon, has connector consisting of male plug attached to cradle, female plug attached to arming mechanism so that connection is interrupted when arming mechanism is pushed back

The device has a connector (10) consisting of a male plug (11) and a female plug (12). The male plug is attached to fixed cradle (3), and the female plug is attached to arming mechanism (2) of the weapon, so that electrical connection is interrupted when arming mechanism is pushed back. Male plug includes two contact pins (20a, 20b) whose free length, i.e. out of plug, is greater or equal to length of socket (15a, 15b).

Device for holding and launching rocket bombs from aircraft

LAUNCHING TUBE STRUCTURE AND NAVAL PLATFORM COMPRISING AT LEAST ONE SUCH STRUCTURE

Rocket Launcher Improvements

MACHINE STOPPING AND RELEASING APPARATUS

Rocket projectile holding and ignition device

UNLOCKABLE CONNECTION DEVICE BETWEEN TWO OBJECTS FOR USE IN PARTICULAR IN THE SPACE FIELD.

MISSILE EJECTION SYSTEM AND LAUNCH CASE

Rocket erecting system

本申请涉及火箭发射地面支持领域，尤其涉及一种火箭起竖系统，由于在竖直方向有起竖摇臂前搭接台和起竖支撑纵梁后搭接台作为定位基准，在前后方向有起竖挡块作为定位基准，因此本申请仅需要在垂直倒车的方向进行调整即可，从而降低了火箭转运装置和地面起竖发射装置的对接要求。另外，本申请的对接是通过前锁紧销和后锁紧销实现的起竖架和起竖摇臂的固定连接，而不是回转轴的对接连接，因此本申请中前锁孔和后锁孔的尺寸可以设置的较回转对接的对接孔的尺寸大，从而进一步降低火箭转运装置和地面起竖发射装置的对接要求。

Fletched projectile

Rocket holding device

Missiles

Advanced rocket-propelled projectile launch pad

Launching device for a missile propelled by a sabot

ELECTRIC FIRE ASSEMBLY OF PYROTECHNIC ARTICLES USING A SPARK IGNITION DEVICE

ENSEMBLE DE MISE A FEU ELECTRIQUE D'ARTICLES PYROTECHNIQUES, COMPRENANT AU MOINS UN DISPOSITIF D'ALLUMAGE ET AU MOINS UN CHARGEMENT PYROTECHNIQUE. SELON L'INVENTION, LE DISPOSITIF D'ALLUMAGE COMPORTE AU MOINS DEUX ELECTRODES CONNECTEES A UNE SOURCE ELECTRIQUE A HAUTE TENSION PERMETTANT LA FORMATION D'UNE ETINCELLE ENTRE CES DEUX ELECTRODES, QUI SONT SITUEES AU VOISINAGE D'UN ELEMENT DE SURFACE DU CHARGEMENT. PREFERENTIELLEMENT LE DISPOSITIF D'ALLUMAGE COMPREND UNE ELECTRODE CENTRALE ET UNE ELECTRODE PERIPHERIQUE DANS LAQUELLE PENETRE LE PROPULSEUR MUNI D'UN BLOC DE PROPERGOL COMPORTANT UNE PERFORATION TRANSVERSALE. APPLICATION A L'ALLUMAGE DES BLOCS DE PROPERGOL ET AU LANCEMENT DES ENGINS AUTOPROPULSES. PYROTECHNIC ARTICLES ELECTRIC FIRE ASSEMBLY, INCLUDING AT LEAST ONE IGNITION DEVICE AND AT LEAST ONE PYROTECHNIC CHARGING. ACCORDING TO THE INVENTION, THE IGNITION DEVICE INCLUDES AT LEAST TWO ELECTRODES CONNECTED TO A HIGH VOLTAGE ELECTRIC SOURCE ALLOWING THE FORMATION OF A SPARK BETWEEN THESE TWO ELECTRODES, WHICH ARE LOCATED IN THE VICINITY OF A SURFACE ELEMENT OF THE LOADING. PREFERENTIALLY THE IGNITION DEVICE CONSISTS OF A CENTRAL ELECTRODE AND A PERIPHERAL ELECTRODE IN WHICH THE PROPELLER FITTED WITH A PROPERGOL BLOCK CONTAINING A TRANSVERSAL PERFORATION. APPLICATION TO THE IGNITION OF PROPERGOL BLOCKS AND TO THE LAUNCHING OF SELF-PROPELLED MACHINES.

SYSTEM FOR LOCKING A MUNITION IN AN ALVEOLE

Il est caractérisé en ce qu'il comprend des moyens 8, 8', 8'' pour déplacer au moins deux verrous 13, 14 disposés en regard l'un de l'autre et les amener en position de verrouillage sur des surfaces d'appui 17, 18 ménagées sur un cadre d'appui 5 qui est disposé dans ladite alvéole, et des moyens 28 pour verrouiller lesdits verrous dans leur position de verrouillage. Application notamment aux lanceurs de missiles verticaux. It is characterized in that it comprises means 8, 8 ', 8' 'for moving at least two bolts 13, 14 arranged opposite one another and bringing them into the locking position on surfaces of. support 17, 18 provided on a support frame 5 which is arranged in said cell, and means 28 for locking said bolts in their locking position. Application in particular to vertical missile launchers.

Missile Restraint and Release Device

본 발명은 미사일을 운용중에는 확실하게 구속하면서도 발사시에는 신속하고 확실하게 구속해제토록 한 미사일 구속 및 해제 장치에 관한 것으로, 미사일의 후단부에 돌출형성된 한쌍의 구속돌기와, 발사관의 내주면에 고정설치되며 상기 구속돌기가 삽입되는 구속홈이 미사일의 진행방향을 향하게 형성된 한쌍의 고정부재와, 이들 각 고정부재의 구속홈을 미사일 진행방향으로 관통하여 상기 구속돌기의 중심에 형성된 구속나사공에 체결되어 미사일을 진행방향으로 구속하는 구속나사와, 상기 고정부재에 회동가능하게 결합되며 미사일의 노즐 중심을 향해 연장되어 미사일의 추력에 의하여 후방으로 회동되는 해제용 회동부재와, 이 회동부재에 후단부가 고정결합되어 상기 구속나사의 움직임을 구속하는 구속핀으로 구성된다. 이러한 구조에 의하여 미사일은 구속돌기와 구속홈에 의하여 반경방향 및 후방으로의 유동이 구속되고 구속나사와 구속핀에 의하여 미사일 진행방향으로 구속되어 운용중에는 미사일을 유동없이 확실하게 구속할 수 있다. 한편, 발사시에는 구속핀이 고정된 회동부재가 미사일의 추력에 의하여 구속나사로부터 이탈되고 구속나사가 고정부재로부터 이탈되어 미사일의 구속해제가 신속하고 확실하게 이루어지게 되어 발사시 발사대의 충격 및 진동이 방지되고 발사 안정성이 높고 발사 오차가 최소화되는 것이다.

Ammunition holding mechanism in the launcher station

FIELD: weapons and ammunition. SUBSTANCE: ammunition holding mechanism in the launcher station (LS) includes the lock unit made in the form of the ring groove in the LS and the split spring ring, installed in the annular groove on the ammunition body. The split spring ring is made in the form of the lock with n-gripping protruberances and it is enclosed by the holder with n-radial grooves through which the gripping protruberances contact the ring groove in the LS. The retention mechanism includes m-interlocking units, installed one after the other. EFFECT: reduction of launching disturbances and reliability increase of ammunition and LS undocking, when starting. 7 cl, 6 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 619 483 C1 (51) МПК F41F 3/052 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ 2015156275, 25.12.2015 (24) Дата начала отсчета срока действия патента: 25.12.2015 (72) Автор(ы): Девяткин Сергей Леонидович (RU) (73) Патентообладатель(и): Открытое акционерное общество "Институт прикладной физики" (RU) Дата регистрации: (56) Список документов, цитированных в отчете о поиске: RU 2242697 C1, 20.12.2004. RU Приоритет(ы): (22) Дата подачи заявки: 25.12.2015 2284000 C1, 20.09.2006. US 3398639 A1, 27.08.1968. US 3811360 A1, 28.11.1972. (45) Опубликовано: 16.05.2017 Бюл. № 14 2 6 1 9 4 8 3 (57) Формула изобретения 1. Механизм удержания боеприпаса в пусковой установке (ПУ), включающий замковый узел, выполненный в виде кольцевой проточки в ПУ и разрезного пружинного кольца, установленного в кольцевой проточке на корпусе боеприпаса, отличающийся тем, что разрезное пружинное кольцо выполнено в виде фиксатора с n-захватными выступами и охвачено обоймой с n-радиальными пазами, через которые захватные выступы контактируют с кольцевой проточкой в ПУ, при этом сам механизм удержания включает m-замковых узлов, установленных друг за другом. 2. Механизм по п. 1, отличающийся тем, что ...

Arrangement for supporting mortar shell into barrel

The invention relates to an arrangement for supporting a mortar shell into the barrel of a mortar weapon by using a separate support piece fixed to the tail of the mortar shell. In the arrangement the support piece is attached to the tail of the mortar shell with a mechanical joint provided by a separate connecting element (7), the connecting element being manufactured of such material and constructed in such a way that it fractures when the charge of the mortar shell is fired, allowing the mortar shell (1) to detach from the support piece (8).

Shorting and radiation protection device for rocket

Abstract of the Disclosure The invention disclosed is a safety device for preventing premature firing of a rocket due to radiation directed at the aft-end of the rocket. The safety device which is attached to the aft-end of a rocket comprises an electrical contact ring which is electrically connectable to the rocket igniter, a shielding means, also electrically connected to the igniter! for shielding the igniter and firing circuit from electromagnetic radiation, insulating means between the electrical contact ring and shielding means and electrical switch means connected between the shielding means and the elec-trical contact ring.

Device for mechanical and electrical coupling of loads, particularly military loads

Armoured vehicle rocket launcher mounting remote control

The remote-control is for the mounting of a rocket-launching tube on the turret of an armoured vehicle. It has hydraulically-operated holding claws (4-7) for the tube (2,3), with pressure-equalisation equipment for their rams (18,19), while inside (10) the vehicle (9) is a master cylinder (12). The rams have mechanically-operated non-return valves for the following rams, and a pressure-relief valve, a pressure-equalisation vessel, and further non-return valves are mounted between the hydraulic pipes (13-16).

System for locking a projectile in a cell

MECHANICAL AND ELECTRIC COUPLING DEVICE FOR LOADS, NOTES MILITARY

Patent FR2210281A5

Shock isolation system

Device for firing projectiles on board airplanes and airships

Missile restraint

본 발명은 미사일 구속장치에 관한 것이다. 일반적으로 미사일을 운반하는 과정에서는 발사관에 삽입하여 구속 조립함으로써 외력으로부터 미상일을 보호하는 것이 요구된다. 본 발명은 미사일이 후미에 한쌍의 진원형 단면을 가지는 한쌍의 돌출부를 돌출 형성하고, 발사관의 내주면 일측에는 진원형 단면의 구속홈이 형성된 브래키트를, 타측에는 발사관의 반경 방향으로 상기 진원형 단면의 구속홈의 직경보다 큰 장축을 가지며 이에 직교되는 방향으로 상기 진원형 단면의 구속홈의 직경과 같은 단축을 가지는 장원형 구속홈이 형성된 브래키트를 고정 설치하여 양측 구속홈에 각각 돌출부를 끼우는 것에 의하여 미사일을 발사관에 조립함에 있어서는 별도의 쉼을 삽입하지 않고서도 간편하게 구속 조립할 수 있으면서도 발사시에는 구속이 신속하게 해제되며, 초기 힘을 받지 않아 발사관의 변형을 확실하게 방지할 수 있도록 한 것이다.

Patent FR2183842A1

Self-contained canister missile launcher with tubular exhaust uptake ducts

A self-contained missile canister includes a cylindrical shell having a plenum or manifold at the breech end for receiving and deflecting missile exhaust gases. A plurality of tubular exhaust ducts or uptake tubes route exhaust gases from the plenum to locations near the missile exit end of the canister. Protrusions on the missile, such as guide rails or aerodynamic control fins, extend from the missile body at locations lying between the exhaust ducts. The tubular exhaust ducts resist the exhaust pressure in hoop tension, so are lightweight. Ablative material may line the exhaust ducts. The exhaust ducts may be supported by longitudinally disposed support beams, preferably I-beams. In one embodiment, each I-beam supports two exhaust ducts.

SYSTEM FOR SUSPENSION OF CYLINDRICAL ELEMENTS IN CONTAINERS IN PARTICULAR MISSIL SUSPENSION SYSTEMS FOR MISSILER UNDERWATER

Rocket plane

Light trigger

An optical firearm trigger is disclosed, revealing means and methods of initiating discharge of a firearm without the use of a mechanical trigger. In this manner the grip of the firearm will not change due to the mechanical loading required to pull the trigger further alleviating the hold, or squeeze, on the firearm during discharge. It further relates to firearm safety as it provides methods and means to prevent reflexive, unintentional trigger pull by the shooter. No personalization or additional security is incorporated in the firearm by this disclosure.

Safety device for electrically fired projectile launching tube

Patent FR2408812B1

REMOTE CONTROL INSTALLATION FOR A MACHINE LAUNCHER TUBE RETAINER

Light trigger

A firearm has a trigger shield configured as a protective loop surrounding at least one switch and the at least one switch actuates the function of the firearm when activated by a finger to start the firing process. The firearm further has at least one receiver, at least one position beam emanating horizontally that determines a position of a finger by the finger blocking or not blocking the position beam, and at least one emitter that propagates a beam of light, the beam of light incident on the at least one receiver. Further, when a finger activates the switch, the firearm activates, and when the finger breaks the beam of light, the firearm discharges.

Locking arrangement for singly and sequentially releasing ballistic missiles

Launching device for rocket projectiles with electric ignition capsule

Throwing system for smoke candles and explosive devices

A mobile missile launch system and method thereof

A MOBILE MISSILE LAUNCH SYSTEM AND METHOD THEREOF5The present invention relates to launching system, more particularly relates to mobile launching system for missiles. The mobile missile launch system comprising a vehicle (14) having a chassis structure adapted to carry the launch system; a mounting frame (16) comprising predetermined truss framework mounted onto the chassis structure; plurality of10 sliding mechanisms mounted at rear end of the mounting frame (16); plurality of canisters (43) mounted onto said beam (22) and plurality of missiles (11) ensconced within the canisters (43); plurality of containers (42) enclosing said canisters (43) and are connected to the saddles (32, 34) for linear movement; plurality of resting units (27) abutting to rear end of the canisters (43) and are adapted to move linearly to transfer reaction forces from15 said missiles (11) to ground.FIGURE 21a - 21c20

Improvements to rockets that must be able to be adapted by clusters to a launch vehicle, in particular to an aerodyne

Device for supporting mortar grenade in pipes

Arrangement for positioning and securing a transport and launch container containing a ready-to-launch missile on a stationary launch pad

Ignition of pyrotechnic devices

Systems and techniques for launching a payload

This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.

Missile container and apparatus for securing a missile container to a support pad

1326982 Mounting for a missile; missile containers P LE CHEVALIER and J BLANGIS 21 April 1971 [22 April 1970] 10600/71 Headings F3A and F3C A support pad for a missile container having shoes 1, 2, Figs. 1 and 2, is provided with V- shaped slideways 3, 4 and flat slideways 5, 6, and has locking members 7, Fig. 5, each of the latter holding a respective shoe to the pad. The locking members 7 each pivot about a respective shaft 8 and are moved into the locking position shown by a screw 9, for example, which is carried by the respective slideway. A stud 12 on the pad facilitates the rocking of the respective member 7. One end of the container is provided with resilient members 11, Fig. 7, each of which is interposed between a screw 10 and a locking member 7 so as to allow for differential expansion between the container, which may be made of light alloy, and the pad, which may be made of steel. The placing of the container on the pad is facilitated by removable guide arms 13, Fig. 2. The shoes 1, 2 may be covered with a coating of synthetic plastics material or a layer of zinc to protect against corrosion and electrolytic effect.

DEVICE FOR TRANSFERRING AND SIMULTANEOUSLY CUTTING STILL UNHAVENED BLOCKS OF CONCRETE.

Light Trigger

A firearm has a trigger shield that is a protective loop surrounding a first and second switch of the firearm and the switches actuate the function of the firearm when activated by a finger to start the firing process. The first switch is on a first side of the protective loop and the second switch is on a second side of the protective loop. The protective loop is vertically aligned having the first and second switches on respective shorter sides of the protective loop. The firearm further has a first emitter mounted on the trigger shield that propagates a first light beam to a first receiver mounted on an opposite side of the trigger shield and a second emitter mounted on the trigger shield that propagates a second light beam to a second receiver mounted on an opposite side of the trigger shield. When a finger depresses one of the switches, his/her finger is blocking the light beam and the firearm will not activate and when the finger is moved away from the light beam, the firearm discharges.

Separation device for propulsion system of missile and missile launching system having the same

본 발명은 발사 장비로부터 미사일을 사출시 미사일을 추진기관으로부터 분리시키기 위한 장치에 관한 것으로, 미사일의 후미에 고정되는 커버 플레이트; 상기 미사일의 발사를 위한 추진기관이 구비된 발사관; 상기 추진기관의 전방에 형성되는 고정 플레이트; 상기 고정 플레이트와 커버 플레이트에 삽입되어 체결되며, 상기 미사일의 발사시 상기 추진기관의 추진력에 의하여 상기 커버 플레이트로부터 이탈됨으로써 상기 커버 플레이트를 상기 고정 플레이트로부터 분리시킬 수 있게 구성되는 잠금유닛; 및 상기 잠금유닛을 상기 발사관에 고정시킬 수 있게 구성되는 연결부재를 포함한다. The present invention relates to a device for separating the missile from the propulsion engine when ejecting the missile from the launch equipment, the cover plate is fixed to the rear of the missile; A launch tube having a propulsion engine for launching the missile; A fixed plate formed at the front of the propulsion engine; A locking unit inserted into and fixed to the fixing plate and the cover plate, the lock unit being separated from the cover plate by the propulsion force of the propulsion engine when the missile is launched to separate the cover plate from the fixing plate; And a connecting member configured to fix the locking unit to the launch tube.

Separation device including restraint bolts design with breaking groove and support guide

본 발명은 발사관 또는 발사대에 비행체를 고정하기 위한 구속해제장치에 있어서, 발사관의 내측으로 돌출되어 형성되는 발사관돌기, 비행체의 외측으로 돌출되어 형성되는 비행체돌기, 상기 발사관돌기와 상기 비행체돌기를 발사방향으로 관통하여 체결되는 구속볼트를 포함하며 상기 구속볼트는 취약부를 포함하는 것을 특징으로 하는 구속해제장치에 관한 것이다. The present invention relates to a constraint releasing device for fixing a flight body to a launching tube or a launching platform, the constraining device comprising: a launching tube protrusion formed to protrude inward of the tube, a flight protrusion protruding outward from the flight body, And a restraining bolt fastened through the retaining bolt, wherein the restraining bolt includes a weak portion.

Further training in armament materials and their ammunition

Long Range Hand Grenade

APPARATUS FOR RETAINING A MACHINE IN A LAUNCHING TUBE

Rockets carried in clusters by a launching machine and in particular an aircraft

Device for detecting absence of mechanical barrier for a missile and missile comprising such a device

- Le dispositif (1) de détection d'absence de barrière mécanique pour un missile (M), comporte une tige (5) contrainte par un premier élément élastique (7) et pourvue d'une extrémité libre (5a) apte à venir au contact de la barrière mécanique (2), une came (8) contrainte par un second élément élastique (9), la tige (5) et la came (8) étant configurées de sorte que la tige (5) puisse prendre l'une ou les autres des positions suivantes : une position entrée initiale dans laquelle la tige (5) est maintenue en position stable entre la came (8) et la barrière mécanique (2), une position sortie dans laquelle est amenée la tige (5) sous l'action de la came (8) par un déplacement dans le sens (E) de l'extrémité libre (5a) en l'absence de la barrière mécanique (2), et une position entrée terminale dans laquelle est amenée la tige (5) sous l'action du premier élément élastique (7) après libération du déplacement de la tige (5) par la came (8), la tige (5) étant complètement entrée dans le missile (M) dans cette position entrée terminale de manière à ne plus présenter un danger pour son environnement ou une gêne pour le bon fonctionnement du missile (M).

Trigger device for rocket launch tubes or the like.

Weapon launching tube structure, and naval platform comprising at least one structure of said type

A weapon launching tube structure, and in particular a torpedo launching tube structure, includes a tube inside which weapon guiding slides are mounted at regular intervals around the weapon. The slides are made from a single slide blank obtained by an extrusion process.

Light Trigger

A firearm has an emitter that propagates a light beam to a receiver and at least two finger position beams that propagate horizontally along the firearm on either side of a switch that provides detection of a position of a finger when the finger blocks and unblocks the finger position beam. Further, when only two finger position beams are blocked, this indicates proper positioning of the finger placing the firearm into a dischargeable condition.

Apparatus for detention of guided missile

본 발명은 발사관 내에 장입된 유도탄을 구속하기 위한 장치에 관련된 것으로, 발사관의 내벽에 설치되며, 상기 발사관 내에 장입된 유도탄과 접촉될 수 있도록 형성되는 유도탄 구속 장치에 있어서, 상기 유도탄에 전원을 공급하는 배꼽 연결기가 고정되는 브라켓(bracket)과 상기 브라켓을 지지하며 소정 각도로 경사지게 형성되는 지지부를 포함하는 배꼽 분리부, 및, 상기 배꼽 분리부의 지지부에 형성된 경사와 동일한 각도로 경사지게 형성된 결합홈을 따라 상기 배꼽 분리부가 미끄럼 운동을 수행할 수 있도록 상기 배꼽 분리부와 결합되는 결합부와, 상기 유도탄이 발사되기 전에 상기 발사관 내에서 상기 유도탄의 움직임을 구속할 수 있는 적어도 하나의 핀이 조립 및 설치되며, 상기 적어도 하나의 핀을 지지할 수 있는 형상으로 형성되는 구속부가 형성되는 하우징을 포함하는 것을 특징으로 한다. The present invention relates to a device for restricting a guided car charged in a launching tube, the guiding carbon restraining device being installed on an inner wall of a launching tube and being contactable with the guided car charged in the launching tube, A navel separating part including a bracket for fixing the navel connecting part and a supporting part for supporting the bracket and inclined at a predetermined angle; At least one pin capable of restraining the movement of the guided car in the launch tube is assembled and installed before the guided car is fired, And a restricting portion formed in a shape capable of supporting the at least one pin, It characterized in that it comprises a housing formed.

Missile longitudinal support assembly

A shock resistant missile longitudinal support assembly provides axial support to a canisterized missile while allowing the missile to translate under shock in any radial direction relative to the longitudinal axis of the canister.