METHOD AND DEVICE FOR CONTROL OVER PRIMARY PARAMETERS OF LIQUID-PROPELLANT ROCKET ENGINES Russian patent published in 2013 - IPC F02K9/56 

FIELD: engines and pumps.

SUBSTANCE: proposed method of control proceeds from maintaining fuel components mass flows via engines by keeping preset pressures at engine block inlets. Note here that fuel gaseous components temperatures in feed lines are measured to very controlled pressures in said lines in compliance with relationship P_i=P₀(T_i/T₀)^0.5; where T_i is change in current temperature of fuel gaseous component, P_i is controlled pressure in fuel line, T₀, P₀ are temperature and pressure whereat engine is tuned to rated thrust and fuel flow rates at service tests. Proposed device comprises cylinders 1 with filler necks 2 for gaseous components (oxidiser and propellant), engines blocks 3, preserving pyro valves 4, electrically controlled valves arranged at outlets of cylinders 1, pressure reducers 6 with pressure adjusted by varying tension of springs 7 and actuators, and control system composed of electrical drives 9. Fuel pressure gage 10 and temperature gage 11 are arranged at reducer outlets, in the lines at throttling unit inlets.

EFFECT: higher accuracy of maintaining major performances of rocket engines.

2 cl, 1 dwg