METHOD OF BLOWING LAUNCH VEHICLE ENGINES WITH NITROGEN AND SYSTEM FOR REALIZATION OF THIS METHOD Russian patent published in 2008 - IPC F02K9/00 B64G5/00 

FIELD: rocketry and space engineering.

SUBSTANCE: in case of non-standard situation before starting of engines, blowing of tail compartments is continued, after which standard blowing is performed; in case of non-standard situation after starting of engines, blowing of fuel line and tail compartments is continued at simultaneous switching-on of emergency oxidizer line blowing, after which standard blowing is performed; in case of inflammation before arising of non-standard situation and after occurrence of non-standard situation, blowing of tail compartments is continued before start of engine plants and simultaneously oxidizer fire line blowing is switched-on; in case of inflammation after arising of non-standard situation and after start of engine plants, blowing of fuel line and tail compartments is continued and simultaneously oxidizer fire line is switched on; in case oxidizer emergency line was switched on, it is changed-over for blowing the oxidizer fire line; in case pressure in oxidizer fire line drops below preset limit, bypass pipe line running from fuel line and tail compartments to oxidizer fire line of launch vehicles and spacecraft on launch complexes during preparation for launch is opened. Proposed method is performed with the aid of nitrogen blowing system of launch vehicle engines whose manifolds are made in form of supply lines 19 and 20, four connecting pipe lines 21 thru 24 and four ring-shaped pipe lines: fuel pipe line 25, tail compartment pipe line 26, oxidizer emergency pipe line 27 and oxidizer fire pipe line 28. One supply pipe line 19 is connected with the aid of connecting pipe lines 21 and 22 with ring-shaped fuel pipe lines and tail compartment pipe line and other supply line is connected with ring-shaped oxidizer emergency pipe line and oxidizer fire pipe line; each ring-shaped pipe line 25 thru 28 is connected with launch vehicle modules A, B, C, D, E by means of supply pipe lines. System is provided with two pneumatic pressure control boards 29 and 30; control board 29 is connected with supply lines 19 and 20 at points between pneumatic valves 4 and 6, 7; 5 and 8,9 before connection of bypass pipe line 1 and with bypass pipe line 1; control board 30 is connected with supply pipe lines 10 thru 13 to unit D of launch vehicle which is farthest from pneumatic valves. All pneumatic valves are normally-closed.

EFFECT: enhanced reliability at preparation stage of launch vehicles and at launching them from launch complexes.

3 cl, 4 dwg, 1 Fig