LIQUID-PROPELLANT ROCKET ENGINE OF MULTIPLE START-UP (VERSIONS) Russian patent published in 2009 - IPC F02K99/00 

FIELD: engines and pumps.

SUBSTANCE: invention is related to space rocket engineering and may be used in engine and power installations of perspective facilities of interorbital transportation, intended for ascent of spacecrafts from low parking orbits to different high-energy orbits. In two versions of liquid-propellant rocket engine of multiple start-up, which comprise source of power supply, tanks with liquid fuel and oxidant, systems for supply of liquid fuel and oxidant with pumps, oxidant receiver with electric heater, heat exchanger-gasifier of oxidant, fuel receiver with compressor and engine chamber, as power supply source electrochemical accumulator battery is used with charging-discharging device and electrochemical generator based on battery of fuel elements that operate on main fuel components, besides inlets of fuel and oxidant into electrochemical generator are connected accordingly to receivers of fuel and oxidant via pressure and flow controllers, and electrochemical accumulator battery via charging-discharging device is connected to electric output of electrochemical generator. In the second version of liquid-propellant rocket engine design with multiple start-up in system for supply of liquid fuel and oxidant, there are booster pumps installed with pneumatic drives, inlets of which are connected to appropriate outlets of fuel and oxidant from heat exchanger-gasifier of oxidant, and outlets of pneumatic drives are connected to appropriate inlets of fuel and oxidant into chamber mixing head.

EFFECT: creation of highly efficient liquid-propellant rocket engine of multiple start-up with higher reliability, structural simplicity and reduced cost, with considerable reduction of dimensions and weight of structure and in case of maximum reduction of ascent duration.

2 cl, 4 dwg