FIELD: space equipment.
SUBSTANCE: invention relates to space engineering and can be used in development of single-component liquid-propellant rocket engines included in low-traction power plants of satellites for orbital maneuvering. Method for controlling mass flow rate of fuel in engine is carried out as follows: engine valve 1 is supplied and removed supply voltage with frequency from range of 15–25 Hz, duration of voltage supply is determined by provision of required mass fuel consumption during engine operation mode, which is required for task performance. Also, change of mass flow rate of fuel into engine decomposition chamber is performed by setting duty ratio of pulses of voltage supply to valve taking into account its dynamic characteristics at actuation to opening and closing from range
where Kpf is filling factor of voltage pulses to valve; f – pulse frequency of voltage supply to valve; τst – time of armature valve starting; τopen time of valve actuation during opening; τrel is time of anchor releasing from valve core stop; τclos – time of valve actuation at closing; 
– average mass flow rate of fuel at engine operation mode; m is mass flow rate of fuel through fully open valve at the same fuel pressure at engine inlet as at engine operating mode. When each voltage pulse is supplied to valve 1 along capillary 3 at high speed within boundaries of internal channel of outlet part of supply tube 2, a portion of working medium is injected, which further enters into decomposition chamber 4.
EFFECT: invention enables to control mass flow rate of fuel (per unit time), including extremely low, into engine at both constant and variable pressure of fuel at inlet while providing stable and efficient operation of engine.
1 cl, 5 dwg
