SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2017 - IPC F02K9/10 

FIELD: engines and pumps.

SUBSTANCE: engine contains a body with bottoms, a channel charge fastened to the body and equipped with a combustion surface compensator in the form of an annular slit located at the front bottom, a nozzle. The charge channel is blind, and the annular slit is inclined. The charge is equipped with a second combustion surface compensator formed by a portion of the charging channel above the nozzle and a partially burning end face of the charge at the rear bottom. The surface of the channel between the combustion surface compensators is fastened to the armour cover. In this case, the cover is connected to the inner surface of the body by means of flexible cords, arranged evenly along the circumference in a plane equally spaced from the ends of the armoured section of the channel. Each cord is placed in a protective shell.

EFFECT: invention makes it possible to increase the effective summary by a factor of 1,5-2 due to the creation of conditions for excluding the ignition of part of the surface of the charge channel during the entire engine operating time while maintaining the overall dimensions of the engine and achieving the possibility of using high-energy fuels, existing in the industry, without changing the quantitative and qualitative composition thereby increasing the effectiveness of their use.

2 cl, 2 dwg