REACTIVE ENGINE, METHOD FOR SHOOTING WITH ROCKET AMMUNITION AND ROCKET AMMUNITION Russian patent published in 2017 - IPC F02K9/86 F42B15/00 

FIELD: weapons and ammunition.

SUBSTANCE: jet engine includes a housing, a cantilever bar, a hollow central body, a means for controlling the movement of the hollow central body when the nozzle is opened, and means for moving the hollow central body to close the nozzle at a predetermined point of time by providing the predetermined resultant of pressure forces of the gaseous combustion products of propellant to the central body. The housing has a front part, a combustion chamber adapted to accommodate the propellant charge, and a nozzle. The cantilever bar is fixed in the front part of the housing with a free end portion and protrudes outward from the nozzle. The hollow central body is movable along the cantilever bar in the direction of the effluent of the gaseous combustion products of the propellant to open the nozzle and move in a direction reverse to the mentioned one to close the nozzle. The hollow central body covers the cantilever bar along its lateral surface. The means for controlling the movement of the hollow central body when the nozzle is opened is located on the cantilever bar inside the hollow central body. Another invention of the group relates to a rocket ammunition comprising a head part, the above mentioned jet engine connected to the head part on the side of the front part of its housing and a stabiliser. When firing with the rocket ammunition comprising the mentioned jet engine from a mobile launcher with a launch tube, the gaseous combustion products of the propellant are applied to the hollow central body to open the nozzle in the launch tube, allowing the mentioned products to flow out of the open nozzle to create a driving force acting on the rocket ammunition. The position of the hollow central body in the open nozzle is adjusted depending on the charge temperature of the propellant. Simultaneous supply of gaseous products of propellant combustion inside the hollow central body is provided. The nozzle is closed by means of the hollow central body at a predetermined moment of time by providing the predetermined resultant of pressure forces of the gaseous combustion products of the propellant to the hollow central body.

EFFECT: increasing accuracy of shooting, preventing the impact of a jet of powder gases on the shoote and its barotrauma when the initial velocity of the rocket ammunition is increased.

18 cl, 4 dwg