CONTROLLED SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2008 - IPC F02K9/92 F02K9/86 

FIELD: aircraft engineering; rocketry.

SUBSTANCE: invention can be used in guided flying vehicles. Proposed controlled solid-propellant rocket engine has combustion chamber, nozzle, solid propellant charge, pressure pickup built into combustion chamber carried electronic computer, thrust control unit with actuating mechanism and hydraulic damping unit. Combustion chamber is furnished with igniter installed in its bottom and temperature pickup. Hydraulic damping unit contains nozzle, flow rate meter, electromagnetic valve installed on pressure line of pipeline, pneumohydraulic accumulator, part of which is filled with liquid coolant and other part, with solid propellant, and liquid coolant pressure pickup. Travel pickup is installed on rod of actuating mechanism of thrust control unit. Engine is furnished with two control subsystems. First subsystem includes thrust control unit actuating mechanism, pressure and temperature pickups fitted in combustion chamber housing and travel pickup installed on rod of thrust control unit actuating mechanism. All pickups of first subsystem are connected with electronic computer of vehicle. Second subsystem includes pneumohydraulic accumulator of hydraulic damping unit and liquid coolant pressure and hydraulic damping unit flow rate pickups. Liquid coolant pressure pickup and hydraulic damping unit flow rate pickup are connected with electronic computer of flying vehicle.

EFFECT: provision of thrust control of solid-propellant rocket engine and reliable switching off.

2 dwg