MONOPROPELLANT LIQUID ROCKET THRUSTER AND METHOD OF STARTING IT Russian patent published in 1997 - IPC

FIELD: space engineering; engines of attitude control, stabilization and correction systems. SUBSTANCE: engine includes decomposition chamber 1 inside which spiral heater 3 and nozzle 4 are arranged. Spiral heater is wound on sleeve 2. Centrifugal injectors 5, 6 and 7 are arranged in chamber in tiers. Propellant supply pipe lines 8 feeding propellant from manifold-regulator 9 through holes in chamber bottom are brought independently to each injector. In starting the engine, it is warmed up by heater to temperature at which successive initiating of decomposition of propellant fed through injectors of first tier may take place. Propellant is fed through manifold-regulator to first tier of injectors only and is injected into chamber head. Supply of propellant to injectors of second tier from manifold-regulator is effected at interval of time required for formation of front of decomposition of propellant injected through injectors of first tier. Heat generated in front facilitates heating and decomposition of propellant injected through injectors of second tier. Supply of propellant through injectors of third tier is effected similarly but duration of interval is determined by time required for formation of front of decomposition of propellant fed by injectors of second tier. EFFECT: increased flow rate of engine decomposition chamber; enhanced reliability of engine starting. 3 cl, 2 dwg