SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2024 - IPC F02K9/82 

FIELD: rocket science.

SUBSTANCE: invention relates to rocketry and can be used in designing solid-propellant rocket engines with command control of thrust in flight. Solid-propellant rocket engine consists of a body, a charge, elastic bag filled with working fluid in the form of an oxidizer connected to a nozzle unit facing the cavity of the supercritical part of the nozzle, adjustable throttles regulating pressure of the working fluid at the inlet to the nozzles. Oxidizer is injected into the supersonic part of the nozzle. Pressure at the inlet of the nozzles is provided by the pressure of combustion products on the surface of the movable deformable wall; besides, the wall itself is made of non-metallic materials.

EFFECT: invention makes it possible to reduce the weight of the engine structure, while simultaneously providing an increase in the total thrust pulse due to the injection of the oxidizer into the supercritical part of the nozzle and maintaining good tightness of moving parts in comparison with similar in terms of weight and dimensions engines on solid fuel.

1 cl, 2 dwg