METHOD FOR PROVIDING FOR SAFETY OF LAUNCHER AT ROCKET FIRING AND ROCKET FOR ITS REALIZATION Russian patent published in 2005 - IPC

FIELD: armaments, in particular, short-range rockets and method for firing them.

SUBSTANCE: rocket acceleration is provided by the low-thrust first-stage booster engine separated in the trajectory after completion of its operation. At an unauthorized premature action of the first-stage low-thrust booster engine its separation begins in the transport-launching pack. To this end, the cavity formed by the outer surface of the first-stage booster engine and the inner surface of the nozzle funnel and the membrane of the main booster engine is filled with combustion products of the charge of the separation chamber, the cut of the safety band at the fastened joint of the first-stage low-thrust booster engine and the main booster engine, the main booster engine with the sustainer stage are separated and moved relative to the first-stage low-thrust booster engine. The combustion products of the charge of the separation chamber are dropped in the cavity formed by the inner surface of the transport-launching pack and the outer surface of the main booster engine, with a subsequent displacement of them by the pressing first-stage low-thrust booster engine and the sustainer stage in the direction of rocket motion. In addition the rocket has a fixing device fastening the main booster engine and the first-stage low-thrust booster engine. The fixing device automatically opens after the exit of the rocket from the transport-launching pack, it represents on annular groove with a weakened section, which is formed on the outer surface of the nozzle exit of the main booster engine. The first-stage low-thrust booster engine is fastened to the main booster engine by split threaded semi-rings, whose outside diameter coincides with the inside diameter of the transport-launching pack, and a trapezoidal gearing is made on their end face on the side of the booster engine, the gearing enters the annular groove on the outer surface of the nozzle exit of the main booster engine. The semi-rings are fixed with the aid of a cylindrical band installed on their outer surface. The band is fixed on the semi-rings by radially arranged cut-off components and positioned in the diametric expansion of the transport-launching pack.

EFFECT: provided safety of the launcher in case of an unauthorized premature operation of the separation chamber of the first-stage low-thrust booster engine at motion of the rocket on the transport-launching pack.

5 cl, 7 dwg