METHOD FOR LAUNCHING MISSILE FROM TRANSPORT CONTAINER AND DEVICE FOR ITS IMPLEMENTATION Russian patent published in 2008 - IPC F42B15/00 

FIELD: weapons.

SUBSTANCE: group of inventions concerns area of missile equipment. It can be used for the missiles launched from transport containers. The method of missile launch from the transport container includes starting missile engine, clearing the elastic cutting ring keeping a missile in the container by means of moving the missile holdback under the influence of the gases expiring from the engine, on screen of the missile holdback. The missile holdback is supplied with a flange having a nozzle which orifice is locked by a screen; and moving of the missile holdback is performed in plane-parallel after destruction of fixing elements. In the process of movement of the missile holdback influence of gases on the screen is intensified, elastic cutting ring is moved apart radially, and movement of the missile holdback is dampened to its stop. Then screening of the gases expiring of the engine is performed. Device for launching missile from the transport container contains the missile holdback fixed on the container by a ring follower including an elastic sectional ring, distance sleeve and screen. The screen is furmished with cuts, and the missile holdback is supplied with a flange with a nozzle and pushers and a nozzle. The section of a nozzle through passage is blocked by the screen, an external surface of a nozzle is obturated with an elastic element of the container ring follower, the flange is established to cover an elastic ring follower. The pushers are placed from the interior of an elastic ring follower and supplied with slanting ledges spaced apart from the elastic ring follower for not less than volume of its coverage by the flange. The distance sleeve is established to cover a nozzle and executed in the form of a ring with ledges on which the elements fixing the missile holdback are consistently established, located in one plane of cross-section section, while elements dampening the missile holdback located in other plane of cross-section section spaced apart from the first one for a distance of an elastic ring follower not less than volume of its coverage by the flange. The fixing and dampening elements do not coincide in a longitudinal direction and are crossing of surfaces distance sleeve contact with the nozzle and the flange.

EFFECT: provision of decrease in an impulse of a dynamic unbalance of the launching gear.

2 cl, 4 dwg