SINGLE-COMPONENT LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 1998 - IPC

FIELD: single-fuel space-vehicle control systems. SUBSTANCE: engine has fuel decomposition chamber 1 with bottom 2 accommodating fuel distribution unit 3. The latter has porous catalytic material 4 and blind channel 5 made along its axis and provided with side walls 6 tight through maximum one third of its length from chamber bottom. Electric heater 7 is arranged over external surface of fuel distribution unit. Engine also has tight end surface 8, permeable catalytic stack 9, nozzle 10, fuel supply line 11. Permeable shell is placed between heater and porous catalytic material. Side walls of unit 3 are formed by electric heater turns laid in a spaced relation to each other with clearance of 0.02-0.1 mm. Vortex zone formed near bottom 2 provides for thermal damper and natural suppressor of engine instability in operation. Heated gaseous products of fuel decomposition escape through nozzle 10 and build up reactive thrust. EFFECT: improved speed in starting and improved stability and safety of running engine; simplified design. 3 cl, 1 dwg